,i I Conf e SpacePower Subsystem Automation Technology
Transcript of ,i I Conf e SpacePower Subsystem Automation Technology
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,i I Conf e
F
JNASA-CP-221319820013380 NASA renee Publication 2213
SpacePowerSubsystemAutomationTechnology
k ._ : _..
..... .. . ....
Proceedings of a workshop held atMarshall Space Flight Center, Alabama
October 28-29, 1981
f_l_A
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NASA Conference Publication 2213
SpacePowerSubsystemAutomationTechnology
James R. Graves, CompilerGeorge C. Marshall Space Flight CenterMarshall Space Flight Center, Alabama
Proceedings of a workshop held atMarshall Space Flight Center, Alabama
October 28-29, 1981
N_ANationalAeronautics
andSpaceAdministration
ScientificandTechnicalInformationBranch
1982
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CONTENTS
Page
FOREWORD.................... . ........................... iii
CONFERENCEAGENDA ....................................... I
WORKSHOPASSIGNMENTS .................................... 3
IMPROVE SPACECRAFT AFFORDABILITY THROUGH AUTOMATION ..... 5Richard F. Carlisle
WORKSHOPPURPOSE ......................................... 9J. P. Mullin
POWERSYSTEM COMPONENTMODELING PROGRAM................. 15Lou Slifer
RECENT ADVANCES IN'AUTOMATION COMPONENTSTECHNOLOGY ..... 35Bob Finke
AUTOMATION TECHNOLOGY FOR POWERSYSTEM MANAGEMENT ....... 57Ron Larson
SPACECRAFT SYSTEM/POWER SUBSYSTEM INTERACTIONS. ......... 69Chris Carl
TECHNICIAL ISSUES IN POWERSYSTEM AUTONOMYFORPLANETARY SPACECRAFT .................................... 87
Fred C. Vote
MARTIN MARIETTA POWERSYSTEM AUTOMATION EXPERIENCE ...... 119Fred Lukens
iii
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Page
AIR FORCE REQUIREMENTS FOR POWER SYSTEM AUTOMATION ...... 137Dave Massie
POWER SYSTEM AUTOMATION REQUIREMENTS FOR EARTH ORBIT .... 155J. R. Lanier, Jr.
AMPS PROGRAM STATUS AND OBJECTIVES ...................... 163Arthur D. Schoenfeld
"STRAWMAN" TECHNOLOGY ISSUES AND SPECIFIC OBJECTIVES .... 177Jim Graves
REPORT OF WORKSHOP GROUP NO. 1 .......................... 189Sidney W. Silverman
REPORT OF WORKSHOP GROUP NO. 2 .......................... 193Floyd E. Ford
REPORT OF WORKSHOP GROUP NO. 3 .......................... 199Howard Weiner
REPORT OF WORKSHOP GROUP NO. 4 .......................... 205Wayne Wagnon
ATTENDANCE LIST ......................................... 211
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SPACE POWER SYSTEM AUTOMATION WORKSHOP
MARSHALL SPACE FLIGHT CENTER
OCTOBER 28 - 29, 1981
BLDG 4610 ROOM 5025
AGENDA
WEDNESDAY/OCTOBER 28
8:30 - 8:45 - INTRODUCTION .......... JIM MILLER
8:45 - 9:00 - OPENING REMARKS ......... DICK CARLISLE
9:00 - 9:15 - POWER SYSTEM AUTOMATION PLANS. JERRY MULLIN
9:15 - 9:45 - PO_R SYSTEM COMPONENTMODELING PROGRAM ........ LOU SLIFER
9:45 - 10:15 - RECENT ADVANCES IN AUTOMATIONCOMPONENTS TECHNOLOGY ..... BOB FINKE
10:15 - 10:45 - AUTOMATION TECHNOLOGY FORPOWER SYSTEM MANAGEMENT .... RON LARSON
10:45 - 11:15 - SPACECRAFT SYSTEM/POWER SUB-SYSTEM INTERACTIONS ...... CIIRIS CARL
11:15 - 11:45 - TECHNICAL ISSUES IN POWER SYSTEMAUTONOMY FOR PLANETARY SPACE-CRAFT ............. FRED VOTE
11:45 - 12:15 - POWER SYSTEM AUTOMATIONEXPERIENCE AT MARTIN ...... FRED LUKENS
12:15 - 1:15 - LUNCH
1:15 - 1:45 - AIR FORCE REQUIREMENTS FORPOWER SYSTEM AUTOMATION .... DAVE MASSIE
1:45 - 2:15 - PO_R SYSTEM AUTOMATIONREQUIREMENTS FOR EARTH ORBIT. ROY LANIER
2:15 - 3:00 - AMPS PROGRAM STATUSAND OBJECTIVES .......... ART SCHOENFELD
3:00 - 3:30 - STRAWMAN IDENTIFICATION OFTECHNOLOGY ISSUES AND SPECIFICAUTOMATION OBJECTIVES ..... JIM GRAVES
3:30 - 4:00 - GROUP DISCUSSION ........ JIM MILLER
5:30 - 7:00 - DINNER AT THE ELEGANT STEAK ROOM
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THURSDAY/OCTOBER 29 (ROOMS AS INDICATED)
8:00 - i2.00 - WORKSHOP DISCUSSIONS WORKSHOP CHAIRMAN
o TECHNOLOGY ISSUES IDENTIFICATION
GROUP i (Bldg. 4487- Rm. A-204) SID SILVERMAN
GROUP 2 (Bldg. 4487 - Rm. A-214) FLOYD FORD
o SPECIFIC AUTOMATION OBJECTIVES
GROUP 3 (Bldg. 46i0 - Rm. 5025) HOWARD WEINER
GROUP 4 (Bldg. 4487 - Rm, 238) WAYNE WAGNON
12:00 - i:00 - LUNCH
BLDG. 4610 - ROOM 5025:
i:oo - 2:30 - TECHNOLOGY ISSUES REPORT WORKSHOP CHAIRMAN
2:30 - 4:00 - SPECIFIC OBJECTIVES REPORT WORKSHOP CHAIRMAN
4:00 - WRAP UP AND TURN IN WORKSHOP RESULTS JIM MILLER
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WORKSHOP ASSIGNMENTS
TECHNOLOGY ISSUES SPECIFIC OBJECTIVES
GROUP 1 GROUP 2 GROUP 3 GROUP 4BLDG. 4487, ROOM A-204 BLDG. 4487, ROOM A-214 BLDG. 4610, ROOM 5025 BLDG. 4487, ROOM B-238
SID SILVERMAN/CHAIRNAN FLOYD FORD/CHAIRMAN HOWARD WEINER/CHAIRMAN WAYNE WAGNON/CHAIPdIA_N
DICK CARLISLE FRED VOTE JERRY MULLIN RON LARSON
MATT IMIIAIdURA JOHN LEAR CHRIS CARL FP_D LUKENS
BILL BRANNIAN CHARLIE SOLLO JIM WILLIAMS ART SCHOENFELD
DAVE PETERSON JOE NAVARRO KENT DECKER RON GIVEN
BOB GIUDICI MIKE GLASS GEORGE VON TIESENHAUSEN IRVING STEIN
ROY LANIER DON ROUTH JACK MACPHERSON C. S. CROWELL
JOHN ARMANTROUT WAYNE HUDSON JOE VOSS DAVE MASSIE
DOUG TURNER DON WILLIAMS LU SLIFER DICK GUALDONI
LT. ED GJERMUNDSEN
Oo
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IMPROVE SPACECRAFT AFFORDABILITYTHROUGH AUTOMATION
BYRICHARD F. CARLISLE
MANAGER, SPACECRAFT SYSTEMS OFFICEOAST
Introduction
The goal of the bpacecraft Technology Automation task is to reducethe spacecraft life cycle cost, extend expected spacecraft opera-tional life, and improve performance.
Life cycle cost includes the cost of non-recurring design, manu-facturing and test, launch, and on-orbit operation includingmaintenance, repair, and redundance management. The operationcost to meet ten year satisfactory performance adds considerablespacecraft complexity with respect to redundancy management andfault tolerant design. Spacecraft sel_ management by automationcan offer considerable operation costs benefits. The more complexthe spacecraft, the larger the benefit of automation whetherimplemented on board the spacecraft or on the ground.
The technology development schedule has a severe sense of urgencybased on current NASA planning that requires a technology readi-ness for a potential FY 1986 phase C/D major new start for an Earthorbiting vehicle that will establish a long term United Statesprominance in space.
Spacecraft Automation Technology Approach
The approach planned by OAST is to establish a long term automationobjective with phased technology outputs_ The long term objectiveincludes a high degree of automation that will require minimuminvolvement of man. A short term, low risk objective is to
automate the present manned involvement thus reducing theroutineground operational support. This can be a major early cost savingseven if the initial application is automated on the ground. Thedecision to transfer these functions to the spacecraft will
probably be made based on economics and/or the availability ofhardware.
The planned OAST FY 1982 Spacecraft Automation Technology task iscomprised of three major tasks. JPL will study a total spacecraftperformance requirement and prepare an automation technologyplanat the spacecraft level. This plan will be based on a revlew ofthe baseline automation of the existing Voyager spacecraft. Itwill expand to a strawman generic future spacecraft automationdesign. The task will trade-off such things as: central vsdistributed control, alternative spacecraft automation architec-ture, heirarchial command and control ground rules, interfacesbetween spacecraft subsystems and mission rules to establishpriorities when conflicts occur in the spacecraft command andcontrol system.
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If there were sufficient funds available, it would be desirableto conduct subsystem automation technology tasks in each of thespacecraft systems as part of the spacecraft automation task.With limited funds, we plan to initially develop the automationdesign for only the power subsystem in parallel with the broadspacecraft task. Task 2, the power system automation task willbe performed by MSFC. The details of Tasks 1 & 2 are somewhat afunction of the output of this workshop. Task 3 will be thedevelopment of generic automation technologies.
It is highly desirable that the power system automation taskachieve both a long term objective and a near term benefit. Itis envisioned that this can be successfully accomplished from anorderly and systematic growth of a power system automation tech-nology development program that is compatible with a parallelspacecraft system automation program. Other systems, in turn, canbenefit from the efforts in the power system automation task.
The degree of power system automation can increase with time.There is little urgency to eliminate_manned involvement com-pletely. The DoD has an autonomy requirement with respect tosecurity and/or survivability. The degree of autonomy (operationwith no involvement of man) required with respect to time in-creases the complexity and cost of the orbiting spacecraft in anon-linear way. Therefore, the affordability benefit of auto-mation is significantly impacted by the degree of autonomy. Thetechnology to enable, and the cost-benefits of automation, willbe determined by future trade-off studies.
I expect that the spacecraft and power systems automation taskswill continue for several years. The two tasks must establish atechnology interface between them. Orderly periodic interactionsmust occur between the two tasks. This interaction will resultin the definition of interfaces between the two programs and theseinterfaces will in somecases become design constraints on eitheror both programs. These constraints must be reviewed and modifiedin the best interest of the spacecraft systems in order that thiscoordinated program can provide the technology to support anoptimized spacecraft design.
Later this morning you will hear a presentation by Chris Carl thatwill describe JPL's background and experience in spacecraftautomation. He will a]so discuss the current spacecraft auto-mation approach and will establish the initial spacecraft/powersystem automation interaction. I expect the spacecraft systemautomation task will eventually involve a spacecraft systemsimulation. I also expect the power system automation technologyoutput will result in a power system automation simulation thatcan be integrated into the spacecraft system simulation and canbe implemented in a MSFC power system breadboard.
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You will hear also this morning from Ron Larsen, who will discussgeneric automation technology. He will describe degrees ofautomation from simple preprogramming to the orderly sequencingof man's logic process that will enable the capturing" of thecomplex methodology of decision making involving interactive non-linear functions. He will discuss the technique of capturing theexperience of experts and the mathematics and methodology ofinterrelating this experience into the control of complex mecha-nisms. He will introduce you to the generic technology ofautomation software development. The initial generic automationtask is planned to bel focused on the experience of a "batterysystems engineer" as applicable to the on-orbit management of abattery system.
In summary, the Spacecraft Systems Automation Technology tasksconsist of three parallel tasks; spacecraft automation to estab-lish the total spacecraft philosophy; power system automationtechniques compatible with the system philosophy and near termbenefits; and, generic automation technology to develop auto-mation methodology and automation software design.
I am pleased to see the interest illustrated by the collectiveexperience I know you represent. I want to assure you that yourrecommendations will be seriously evaluated and considered. I amcertain in the next two days you are going to make a significantimpact on our program. I am pleased to be here with you and amanxious to see how you will advise us.
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WORKSHOP PURPOSE
o IDENTIFY TECHNOLOGY ISSUES RELATIVE TO SPACE
POWER SYSTEM AUTOMATION DEVELOPIV_NT
o ESTABLISH SPECIFIC AUTOmaTION OBJECTIVES RELATIVE
TO SPACE POWER SYSTEM AUTOmaTION DEVELOPmeNT
J. P° Mullin
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10/28/81o MSFC AUTOMATION M]_ETING
MAJOR NASA THRUSTS
o NOW - GET SHUTTLE OPERATIONAL
o NEXT - ESTABLISH 'PERMANENT' MANNED LEO PRESENCE
_S____TT THRUST_
( WORK TECHNOLOGY 1
TOWARD START IN /
J. P. Mullin
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10/28/81
M_FC AUTOIIATIONMEETING
SPACE POWER THRUSTS
o FOR THE PAST FIVE YEARS PROGRAM DIRECTED TOWAP_ CRITICAL
TECHNOLOGIES NEEDED FOR HIGH POh_R IN LEO/AMAJOR SPACE
STATION REQUIREMENT
- HIGH P0_R LOW COST SOLAR ARRAYS-LARGE CELLS, CONCENTRATORS
- HIGH CAPACITY LONG LIFE ENERGY STORAGE - FUEL CELL -
ELECTROLYSIS, NiH2 BATTERY
- HIGH PO_R CO_ONENTS - TRANSISTORS, CAPACITORS, TRANSFOP_RS,
SWITCHES
- _qDERSTANDING OF PLASMA INTERACTIONS - PIX I & II, NASCAP
- THERMAL COMPONENTS - HEAT PIPES, RADIATORS
- ENERGY _IANAGE_NT
TH_EBIGGEST DEFICIENCY It_
CAL ENERGY _NAGEMENT
J. P. Mullin
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10128181
OAST ENERGY M_NAGEMENT BACKGROUND
o APSM PROGRAM (AUTOMATED PO_R SYSTEM MGT)
o 1975 - 1981/$2M
o CO_ARED AUTOMATED BASELINE VERSION OF PLANETARY S/C (V075) POWERSYSTEM - NO THERMAL
o AUTOMATED VERSION PROVIDED
- 50%_ OPERATIONS COST
- 50%>SPECIFIC POWER
- _- 40%< CAPITAL COST
- IMPROVED FAULT TOLERANCE!FLEXIBILITY
o lAPS FLIGHT PROGRAM - REQUIRED ON BOARD AUTOMATION OF ION THRUSTER ENGINEER
o AMPS PROGRAM
o IN PROCESS NOW
o ESTABLISH UTILITY - LIKE CAPABILITY TO MANAGE HIGH CAPACITY LEO ENERGY
SYSTEM - ELECTRICAL & THERMAL/ARBITRARY 250 kW REFERENCE SYSTEM
o IdAJOR OAST - WIDE AUTOMATION THRUST ADOPTED FY82
o AMPS UNDER REVIEW FOR COORDINATION WITH OVERALL OAST THRUST
J. P. Mullin
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10/28/81
PURPOSE
o IDENTIFY TECHNOLOGY ISSUES IN LEO ENERGY MANAGEMENT
o RANK CRITICAL TECHNOLOGY NEEDS-BARRIERS
o RECOMMEND TECHNOLOGY OBJECTIVES
o COMMENT ON STRAWMAN
o INVOLVE AUTOMATION AS WELL AS POWER TECHNOLOGISTS
J. P. Mullin
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POWERSYSTEMCOMPONENTMODELINGPROGRAM
(MODELING/AUTOMATION/AUTONOMY)
PRESENTATIONTO:
SPACEPOWERSYSTEMAUTOMATIONWORKSHOP
L.SLIFER
10/28/81
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ANALYTICALMODELING
RECOMMENDATION:
1, DEVELOP AC MODELS FOR POWER SUBSYSTEM COMPONENTS
2, SYNTHESIZE ANALYTICAL MODEL FOR POWER SYSTEM
3, DEFINE NECESSARY PARAMETERS FOR ELECTRONICSIMULATION OF AC SOLAR ARRAY MODEL
RATIONALE:
VERY LITTLE AC DATA AVAILABLE FOR COMPONENTS AND SYSTEM
EXISTING DATA NEEDS REVIEW_ REVISION_ REFINEMENT ANDUPDATING
GUIDELINES NEEDED FOR ACCURATE ELECTRONIC SIMULATION
_LECTRON_C ARRAY SIMULATION IS NEEDED - ONLY KNOWN WAY TOINCLUDE LARGE ARRAYS IN GROUND TESTS
PAYOFF:
SAFEGUARD AGAINST BUS INSTABILITY
AVOID HARMFUL INTERACTION BETWEEN ARRAY AND FILTER COMPONENTSAT OUTPUT
DEFINE SOURCE IMPEDANCE AT LOAD BUS
SUPPLEMENT INADEQUATE DC ARRAY SIMULATORS WITH MORE ACCURATEAND REALISTIC AC SIMULATION
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STATEOFHEALTHMONITORING
RECOMMENDATION:
1, DEVELOP IMPROVEDTECHNIQUES FOR ON-BOARD MONITORINGANDCONTROL OF POWER SYSTEM AND ITS COMPONENTS
SOFTWARE/HARDWARETECHNIQUESTO MINIMIZEIMPACTON DATA HANDLING AND COMMAND SYSTEMGROUND OPERATIONS
IDENTIFY REQUIRED STATE OF HEALTH DIAGNOSTICMEASUREMENTSDEVELOP SENSING TECHNIQUESAND SENSORS FOR DETECTING
PARTIAL FAILURESDEGRADATION
2, DEFINE TECHNIQUES FOR REDUCING COMPLEXITYOF MANAGING DEGRADEDSYSTEM/COMPONENTSFROM GROUND
RATIONALE:
EXISTING ON-BOARD SENSORS/MEASUREMENTSINADEQUATEFOR ACCURATEDEFINITIONOF STATE OF HEALTHGROUND MONITORINGAND ANALYSIS IS INADEQUATEAND EXPENSIVEGROUND CONTROL IS COMPLEX AND.SLOW TO RESPONDINADEQUACIESAFFECT MISSION PLANNING AND FLIGHT OPERATIONSREAL EFFECTS OF ENVIRONMENTON SYSTEM ARE NOT KNOWN
PAYOFF:\
LOWER GROUND SUPPORT COSTIMPROVED RESPONSE IN COMPENSATINGFOR PARTIAL FAILURE/DEGRADATIONIMPROVEDDESIGN CAPABILITYIMPROVEDMISSION OPERATIONSLOWER POWER SYSTEM COST AND WEIGHTSIMPLIFICATIONIN C & DH SYSTEM
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oo
SPACESYSTEr.!
i I _ i,
PRE-LAUNCH_ SPACEANDLAUNCH SEGMENT
__:OPERATIONS ,.f?,.// ,_-_
y,A-.
OPERAT!ONS! CONTROL-I COMMUNICATIONS'" DATA F DATA I" :l - -'--T]lJ r .... :-'" I111 : ...... -- .......... , , , , H
.GROUNDSEGMENT
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DEVELOPMENTSINAUTOMATION/AUTONOMY
CHARACTERIZEDBYDELIBERATEPROGRESS
WITHNEEDWITHCOMPLEXITY/SOPHISTICATION
BASEDONMODELS
KNOWLEDGEOFCOMPONENTPERFORMANCECHARACTERISTICSSYNTHESIZEDSYSTEMCHARACTERISTICS
IMPROVED/INCREASEDASMODELSIMPROVED
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0
POWERSYSTEMAUTOMATIONEXAMPLES
SPACECRAFTSHUTDOWN- 1 YR.TIMER
UNDERVOLTAGELOCKOUT
ARRAYORIENTATION
SOLARREACQUISITION
SHUNTREGULATORTO CONTROLBATTERYCHARGEVOLTAGE
TWO-STEPREGULATORFORCONTROL/PROTECTION
SEQUENTIALSHUNTREGULATION
MULTI-STEP(V/TCURVES)TO ADJUSTFORTEMPERATURE
THERMOSTATSTO CONTROLUNDEROVER-TEMPERATURECONDITIONS
AUTOMATICSWITCHINGBETWEENREDUNDANTCOMPONENTS/SYSTEMS
STANDARDPOWER:REGULATORUNIT(%RTIAL)
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_IICDCELLDISCHARGECURVES
CAPACITY
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r_o
j_ t- _r'.T'rr-ov !,_ -,,-_ _" F- ",
i,55
].,50
Tr',',_Dr'r_ r,-rID__nr_.t_J,.!_,.,,_(oc)
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STANDARDPOWERREGULATORUNIT
PEAKPOWERTRACKING - AUTOMATIC(LOADDEPENDENT)
VOLTAGELIMIT - V/TSELECTIONBY COMMAND
CURRENTLIMIT - I SELECTIONBY COMMAND
STANDBY - AUTOMATICIN ECLIPSE
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4_
SOLARARRAY POWEROUTPUT
o
>-
j , i ,. J .......
ARRAYVOLTAGE
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DEGREESOFAUTOMATION
ROUTINEOPERATIONS
CONTROLSEQUENCING
ROUTINGMAINTENANCE
BATTERYCHARGINGBATTERYRECONDITIONING
FAILUREHANDLING
TOLERANCEDETECTIONISOLATIONRECONFIGURATION
FAULTHANDLING
FAULTTOLERANCEFAULTDETECTION
SELF-TESTINGMODELUPDATE
FAULTCORRECTION
RECOVERYRECONFIGURATION
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POWERSYSTEMAUTONOMY
SAFE-HOLDAUTONOMY
UNDERVOLTAGELOCKOUT
AWAITGROUNDCOMMANDTIMED(ON-BOARDCLOCK)RESTART
LOWVOLTAGE/HIGHCURRENTSAFING
AWAITGROUNDCOMMANDS
PARTIALLYOPERATIONALAUTONOMY
FUSINGOFINSTRUMENTS/SYSTEMELEMENTSLOADSHEDDING
OPERATIONALAUTONOMY
FAULTDETECTIONANDISOLATIONPLUSRECOVERY
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CRITICALELEMENTSINAUTOMATION
KNOWNPERFORMANCECHARACTERISTICS(MODEL)
SENSEPERFORMANCELEVELS(MONITOR)
COMPARETOREFERENCES(HEALTH& WELFARE)
ANALYZEDIFFERENCES(DIAGNOSTICCAPABILITY)
DETERMINEACTION(DECISIONCAPABILITY)
TAKEACTION(IMPLEMENTATIONCAPABILITY)
UPDATE(ITERATIONCAPABILITY)
GROUNDSTATIONBACKUP(OVERRIDE)
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ANALYTICAL M O D E L I N G PROGRAM -
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BACKGROUND
OBJECTIVE- DEVELOPMENTOFRELIABLEPOWERSYSTEMS
PROBLEM - DESIGNSNOTPERFECT
- HARDWARENOTPERFECT
- SOFTWARENOTPERFECT
- OPERATIONSNOTPERFECT
SOLUTION- IDENTIFYANDSOLVEPROBLEMSBEFORETHEYBECOMECRITICAL
- PREDICTIONANDPREVENTIONOFPROBLEMS
- VERIFICATIONOF OPERATIONALADEQUACY
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REQUIREMENT- VERIFICATION
ALL-UPTEST
UNWIELDYCOSTLYTOOMANYVARIABLES/CONFIGURATIONSFURTHERCOMPLICATEDWITHON-ORBITCHANGEOUTS
SIMULATION
MUSTBEREALISTICMUSTADEQUATELYMODELWHATISSIMULATED
ANALYSIS
SIMPLE- TRACTABLEADEQUATE- CAPTUREIMPORTANTFEATURESAUTOMATIONOFSOMEPRE_LAUNCHOPERATIONS|ll i
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FIRSTPHASE- REQUIREMENTSDEFINITION
STEP1
REVIEWCURRENTAPPROACHES
EARTHORBITINGSYSTEMMODELSINTERPLANETARYSYSTEMMODELSGENERALANALYTICALPROGRAMS
DETERMINEPROS(CAPABILITIES)ANDCONS(LIMITATIONS)
IDENTIFYAREASFORIMPROVEMENT
ESTABLISHREQUIREMENTSFOR"IDEAL"MODEL
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STEP2
IDENTIFYPRELIMINARYREQUIREMENTSFORCOMPONENTMODELS
DETERMINEADEQUACYOFCOMPONENTMODELS
REGULATION
SHUNTLIMITERMODELSSWITCHINGREGULATORMODELSSOLARARRAYSWITCHINGUNITMODELS
GENERATIONANDSTORAGE
SOLARARRAYMODELSBATTERYMODELS
DISTRIBUTION
EQUIPMENTCABLES
DETERMINELIMITATIONS/UNCERTAINTIESINEACHMODEL
SPECIFYREQUIREDIMPROVEMENTS
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STEP3
IDENTIFYTESTINGREQUIRED
COMPONENTSDEVICES
DETERMINESEQUENCE
TESTINGANALYSIS
DEFINEPROCEDURESFORCOMPREHENSIVEPOWERSYSTEMMODELDEVELOPMENT
i ill i|ii, iICONTINUETOSECONDPHASE
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SUMMARYANDCONCLUSIONS
i, ITISIMPORTANTTOSCOPE"THEAUTOMATIONPROBLEM"
WHATISTOBEAUTOMATED?
WHATDEGREEOFAUTOMATIONISDESIRED?NEEDED?JUSTIFIED?POSSIBLE?
2. EXPERTISE(KNOWLEDGE)ISBASICTOAUTOMATIONANDMODELINGISAN INTEGRALPART,
CONSISTENCYOFUNDERSTANDINGADEQUACYOFMODELABILITYTOAUTOMATEDEGREEOFAUTONOMY
3, AUTOMATIONSYSTEMWILLALSO,BEIMPERFECT,
REQUIRESOVERRIDECAPABILITYREQUIRESRETENTIONOFHISTORY/STATUS/HEALTHANDWELFARE
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RECENTADVANCES
IN
AUTOMATIONTECHNOLOGY
R, C, FINKE
10/28/81
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THE IONAUXILIARYPROPULSIONSYSTEM(IAPS)EMPLOYSA SOPHISTICATED
AUTONOMOUSSPACEPOWERSYSTEM,THE IAPSCONTAINS9 INTERACTIVEPOWER
SUPPLIES,SOMEOF WHICHAREHIG_VOLTAGE,SOMEOF WHICHARE RAISEDTO
HIGHCOMMONMODEPOTENTIAL,ALLSUPPLIESAREVOLTAGEPROGRAMMABLEBY
TIMETAGGEDON-BOARDCOMPUTERCOMMAND,DURINGTHETWO-YEARFLIGHTOF
THE IAPS,THEPOWERSYSTEMWILLAUTOMATICALLYACCOMMODATEFOROUTAGES,
ARCING,DEGRADATIONOF THELOADANDTRANSIENTPHENOMENA,ALLNECESSARY
COMMANDSTO OPERATETHE IAPSARESTOREDIN RAM,BACKEDUP BY PROM,
GROUNDCOMMANDCANMODIFYTHERAMPROGRAMAS THENEEDARISES,
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D= TAPS D_AG_IOSTI(Zs_BSYSTE:YI Z_STR_'IENTA"ri OM
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co IAPSMODULES
...,_----SOLARCELLDETECTOR
UARTZCRYSTALMICROBALANCEI
POTENTIALPROBE
ION COLLECTOR , GIMBALt BEAMSHIELDUNITj 2 SCD+ RADIATOR
2 SCD+I_,ADI-Z lAPSMODULE
SPACECRAFT_
ION COLLECTOR2 SCD+ RADIATOR r I
J _ INTERCONNECT
ION COLLECTOR
ION COL'LECTOR ,QUARTZCRYSTALMICROBALANCE /
-X IAPSMODULE
_S_iG_'_2 SCD+RADIATORL_
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/
O OBJECTIVES:
o DE_MONSTI_ATE THRUSTER SYSTEM PERFORMANCE ANDDURABILITY IN SPACE;
©MEASURE THRUSTER SYSTEM IN-FLIGHT PERFORMANCE
o MEASURE PRINCIPAL THRUSTER-SPACECRAFT INTERACTIONS
• DEVELOP COMMERCIAL SOURCE FOR THRUSTER SYSTEM
• TRANSFER TECHNOLOGY AND INVOLVE USERS
@ MISSION MODEL
o 10{)0 kg, GEOSTATIONARY COMMUNICATIONS SATELLITE
• 7 YRS N-S STATIONKEEPING (1X/DAY) TO -0.01 °
• 4 8-cm THRUSTERS CANTED 45 o TO N-S
• IMPLIES 2557 CYCLES OF 2.76 hrs FULL THRUST OPERATION
(= 7055 TOTAL hrs) FOR EACH THRUSTER
• DUAL THRUSTER OPERATION
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_ flqIIIARYMISSIONOPERATINGPRO(::IIF0
INITIALOIECKOUT
*-----]{ ! -10L _I_IU__OIILY..._ THRUSTERDURATIONOff/OFFCY TXIg.ISTEA/I
DATA COHFI_INGANDREFININGIN.4kI:ES ))_I__ _ _ wmmm_ m im
o 1o _
THRUSTEROPERATINGTIME,MONTHSI Ou41 11_ruster Operation S Glmbal Evllumtlcm
2 Cathode I_lntealmce _ Neutralizer Off. Ikll Thrvstllr Op4rlltlon
11 Idle Y Change OrbitAl Altll_vde
4 Throttled Thrust
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-----
rEL..£:'::'IIoN~L.INe2KbPS
------1III
12-11I
, ..1..----1I cONP:/rEE.
AL.T£~NAT~ I .;J,D/-::ATED I IB£JNG-CO..;$,u;<!";l To PS~-/ J
L J
~ sic =::.O/"i-:=R..(STC)AT.s(/NNYVA~.c
COU/VE£ " 70
r---'-I 5'£.0
r---/--lev'r'F£R..~N£J1"*:::.... ,.
I
.3ZKgp~ (/.02.';' MLJ/'S
II lL - -1
MAIL. TAPES
IL - _---1
~ S/c COr.JT;2ACTOI2
r---L------,I II
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4_rO
PEUREQUIREMENTS(TS-200,REV,A)
A. INPUT VOLTAGE RANGE: 50 VDC TO 90 VDC
B. MAXIMUM INPUT rOWER: 200 W DC
_. PEU EFFICIENCY: "_ 75%
D. PEU SIZE (MAXIMUM): 17.0'INCHES (LENGTH)BY 9.0 INCHES (WIDTH)BY 4.5 INCHES (IIEIGHT)
E. PEU WEIGHT: _ 16.6 POUNDS
F. PEU SUPPLY OUTPUTS PER TABLE 3-I. TS-200
G. PEU TELEMETRYOUTPUTS PER TABLE 3-2, TS-200 (5 V FULL SCALE)
H. PEU SUPPLY OUTPUTS, DC SUPPLIES,RIPPLE: < 10% PEAK
I. PEU SUPPLY OUTPUTS SHALL HAVE INTERNAL OVERLOAD PROTECTION
J. PEU SHALL PROVIDE SCREEN OVERLOAD OUTPUT TO DCIU
K. PEU PULSER OUTPUTS TO BE > 5 KV INTO 1200 _f OR I00 K OHM LOAD
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PEUBLOCKDIAGRAM
70 V INPUT
'| 96 VAC DIST BUS | MAIN 1
UNE CONT LOAD-- REGULATOR AC DIST H_TER
INVERTER . MA
I _ .,_ov - ko.T _,._E To
SUPPLY E'
CONI"RO_L _X' l NEb'TRALIZE,
HEATER TRO P_R
. MA X X*
:o.HF..AT[R TOo
¢ONTI(_L_ ACaLERAI_R _ -300 V
lO LOADi
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IAPS- S/C INTERFACE
o POWERBUS
o ONE COMMANDCHANNELPERT/S
o ONETELEMETRYCHANNELPERT/S
0 ONETELEMETRYCHANNELFORDIAGNOSTICS
o T/SFUNCTIONSCONTROLLEDBYTIMETAGGED
COMMANDSFROMS/C
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SYSTE, F#XD J jE
10676-19
DCIU
SPACECRAFT
TELEMET.RY- CONTROLLER RAM HAMMING~ AND GIMBALCODE ERRORCORRECTION
TELEMETRY ,_
< m
NINE
SER,AL _ I D,G,TAL VOLTAGE-COMMANDJ-- UART :' ON/O_FPROQRAMMABL_(TIME- I 18o2 COMMAND :) POWERTAGGED) CMOS ANALOG SUPPLIES
i /_P COMMAND TIME
I WATCHDOG _TIMER _ ::'
114_ APRIL 1981(33
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O'_
IA_S CO_ROLPHILOSOPHY PA4QU_t__E_S_
10816--8
OEXECUTE ALL NORMAL ,THRUSTER FUNCTION_ ONSINGLE COMMAND
®MAINTAINTHRUSTERON DESIRED OPERATINGPOINT
©PERFORMFAILUREWORKAROUNDS
• AUTOMATIC(TEMPERATURESENSORS)
o GROUND-ENABLED(CATHODEHARDSTARTING)
o-PROVIDE T/M AND S/C INTERFACE
APRIL 1981
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CO_-__OL PH,_LOSOPHY APPROACH
10816--9
o STATE D[AG_RAM: OPERATING MODES
e THRUSTEH MONITOR
o MODE MAINTENANCE
o FAULT/FAILURE SERVICE
o MODE-THANSITIONPACKAGES
e EXECUTIVE
= COMMAND AND T/M PROCESSING
o HOUSEKEEPING FUNCTIONS
APRIL 19,$1
,,,,j
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FULL THRUST NEUTRALIZER BEAM-ON STATSSREDUCED THRUST OFF
t_!
STEADY STATE "_ MINIMUM BEAM STANDBY
STANDBY .--] STANDBY IDLE STATES
SYSTEMMAINTENANCE
CATHODE_ [ _ DISCHARGE
_r MAINTENANCESTATES
DK NKMAINT MAINT
.......H NO-CATHODE-ON
ANTI-FREEZE OFF CONDITIONING STATESAPRIL 198,1
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10816--11
EXECUTIVE
e COMMAND PROCESSING
e T/M UPDATE
®RAM REFRESH
eTIME MAINTENANCE
oWATCHDOG TIMER RESET
I--_ THRUSTER MONITOR
1-SECOND -_INTERRUPT --_ eBEAM-CURRENT CONTROL
•FAU'T/FAILURERECOVERY _OFT_.JARE
I HIERARCHY
i MODE MANAGER I
ITRANSITION TASKS
e MODE TRANSITIONS
• FAULT RECOVERY
IAPPLICATION ROUTINES
APRIL 1981
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o'1o
THRUSTER MO JTOR
10816--12
e DETECT FAULT/FAILURE CONDITIONS
. SET FLAGS FOR TRANSITION ROUTINES
* INVOKE RECOVERY ROUTINES
e CONTROL BEAM CURRENT
* ADJUST DISCHARGE CURRENT TO GIVE:
-- NOMINAL THRUST' 5 mN (1.13 mlb)
-- REDUCED THRUST 4.5 mN (1.00 mlb)
APRIL 1981
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10816--14
FAULT/FAILURE j RECOVERY
DV OR NV TEMP SENSOR AUTOI',IAIIC TIblE-BASED STARTUPFAILURE WORKAROUNDS; FIXED SETPOINT
VAPORIZER OPERATION
DK OR NK HARDSTART EXTENSIVE HARDSTART ALGORITHMS;SHUTDOWN TO MAINTENANCE STATE
DK OR NK EXTINCTION AUTOMATIC RELIGHT AND STATE RECOVERY
DISCHARGE OR NEUTRALIZER AUTOMATIC ANTIFLOODING ROUTINESFLOODING
VD, VDK, OR VNK INSTABILITY TEMP OR FIXED SETPOINT VAPORIZEROR TELEbIETRY FAIEURE OPERATION
IDK OR INK TELEMETRY IGNITION TEST ON VOLTAGEFAILURE
GRID SHORT OR HIGH IA AUTOMATIC HIGH VOLTAGE RECYCLE
EXCESSIVE HIGH VOLTAGE SHUTDOWN FOR GROUND RESTARTRECYCLINGEXCESSIVE POWER HIGH VOLTAGE TURNOFF + AUTOMATICCONSUMPTION RECOVERY ROUTINELOW BUS VOLTAGE SHUTDOWN AND RESET FOR GROUND
RESTART
LOSS OF LOGIC CONTROL SHUTDOWN VIA WATCHDOG TIMER ANDRESET FOR GROUND RESTART
RAM BITFLIP PERIODIC HAMMING CODE TEST AND REFRESH
APRIL Ig81
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OFF TO F_EL T_UST
10816--15
HEAT CATHODES MAINTAIN ATAND : _ IGNITION IGNITE
VAPORIZERS "" TEMPERATURE _ CATHODES3MIN
|l
WAIT RUN 3 MIN TURN ON3 MIN - - ANTIFLOOD < AT HIGH "-
CURRENT DISCHARGE
!BEAM ADJUST __
ON _. ANTIFLOOD .. _, DISCHARGECURRENT
APRI L 1981
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10816--2
IA
¢cz
0
50V t _ _ _-
5P;_ 0 FULL THRUST/lOOmA BEAM ON t , _
o500mA DK IGN;TION
=- / I
o
5ov
oNK IGNITION
_-= 50V i _r_ 317°[ 291°_ A _ _, i
97o 167° 2060 219° 242° 250o T I I l l
=,:_ ! ! i l i I _7o 247o 2,=z°-247° zsz= z_o 247oo
ANTIFLOOD_
• 224° 224°
== 0 PREHEAT zT_o _,_I t ] I _ [ I I ] ]O S 10 |5 20 25 "tO 35 40 ,_
r.,.T1 TIML mua
APRIL 1981
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10816--17
COMPONENT: THERMAL ENVI.rtONMEI-_T'. ,,.
TEST THRUSTER PEU DCIU
Er_: EM:BREADBOARD:
PREQUALIFICATION THERMAL THERMALVACUUM VACUUM AMBIENT
FLIGHT:FLIGHT CHECK-OUT THERMAL FLIGHT: BREADBOARD:
AMBIENT AMBIENTVACUUM
EM: EM:FLIGHT:QUALIFICATION THERMAL THERMAL
VACUUM VACUUM AMBIENTi i i i i |
APRIL 1981
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€ _ONT_-:OL SOFTWARE SUCCESSFULLYIMPLEMENTED IN CONTROLLER
e CONTROLLER SUCCESSFULLY DEMONSTRATEDWITH FLIGHT THRUSTERS
o COMPR_H_,_.Vr_..'"-" -_ "_:_" _ CONTROLLLR CAPABILITYDEMONSTRATED IN EXTENSIVE TESTING
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AUTOMATION
0 REQUIRESDETAILEDKNOWLEDGEOF:
- SYSTEMREQUIREMENTSAND FUNCTION
- SYSTEMELEMENTS
o CHARACTERISTICS
o INTERACTIONS
o CANONLYBE ACCOMPLISHEDAFTERSUFFICIENT
UNDERSTANDINGOF SYSTEMCHARACTERISTICS
EXISTS
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AUTOMATION TECHNOLOGY
FOR POWER SYSTEM MANAGEMENT
Dr. RonaldL. LarsenNASAHeadquartersOctober28, 1981
(.TI
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(._co
POWERSYSTEMCOSTREDUCTIONTHROUGHAUTOMATION
_0 "' ' '
- /70 •
Yeo , ,oo_
MONITORING 60 __ _O_-AND CONTROL
COSTSMS- 1980 40 _4 "f
-/lo I I ,
UNATTENDED OPIEP'ATI_iN(PM[' _o- 1 -i_-O 6 10 16 20 26 30
SATELLITE OPEP,ATi(:_ALLIFE-YEARSRef: TRWPMSStudy
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FUNCTIONSOFANEXPERT
o INTERPRETATION- ANALYSIS OFDATA
o DIAGNOSIS- IDENTIFICATIONOFFAULT
o PREDICTION- FORECASTFUTUREFROMMODEL
o MONITORING- SETOFFALARMS,AVOIDFALSEALARMS
o PLANNING- PROGRAMACTIONSTOACHIEVEGOALS
o DESIGN- PLANNINGTOCREATEOBJECTS
o EXPLANATION- MAKINGUNDERSTANDABLE
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o
EXPERT SYSTEMS
MODELA PERSON'SUNDERSTANDINGOFA SYSTEM
RATHERTHANTHESYSTEMITSELF
Ref:Hayes-Roth,F., "A TutorialonExpertSystems:PuttingKnowledgeto Work,"IJCAI-81
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DEFINING "EXPERT SYSTEMS:'
1 . The field of expert systems investigates methods and techniques for constructing man-machine systems with domain-specific problem-solving expertise
2. Expertise consists of k~owlebge about a domain, understanding of domain problems, and sliill at solving such problems
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A QUICKHISTORY
HEARSAY.I,o_HEARSAY-II ,,,, D,-AGE/HEARSAY-Ill(speechunderstanding) _ HARPY
PROSPECTOR
(geology) _EMYCIN..'_ PUFFROSlEMYCIN(medicine) ,,,, ,, TEIRESIAS
INTERNIST :- • ,, D,_(symbolicmathematics)
SAINT-.-e_, ,,SIN=-=I_ ,,, MATHLAB--I_-.- MACSYMA=>-..._
_" CASN ET---" " EXPERT'="'" "m,--(organicchemistry)
DENDRAL 1-. =,= META-DENDRAL .......
_ _ ! L_ _ _l ---Jr--_-1965 1970 1975 1980
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WHATDOEXPERTSYSTEMSDO?
1. Use expert rules to avoid blind-search
2. Reason by manipulating symbols
3. Grasp fundamental domain principles andweaker general methods
4. Solve complex problems well
5. Interact intelligibly with users
6._ Interpret, diagnose, predict, instruct,monitor, analyze., consult, plan or design
O_Lo
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c_
THEBASICIDEAS1. Knowledge - Facts + beliefs . heuristics
2. Success- Finding a good-enough answer with theresources available
3. Search efficiency directly affects success
4.- Aids to efficiency:
- The quality and generality of knowledge- The rapid eliminationof "blind alleys'"- The elimination of redundant computation- The speed of the computer- The use of multiple sources of knowledge
5. Problem complexity increases with:- Errorful or dynamically changing data- The number of possibilities to be ruled out- The amount of effort required to rule out
a possibility
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]HSIDEliYCIH
0 Problem representation
One or more patients,Context with one or more symptoms,
tree with one or more diseases,with one or more treatments
e Table of operators: If-Then rules
If there is <condition>[and/or <condition>]...
Then there is suggestive ....evidence (.8) of <disease>
0 Control
1. Backchaining2. Exhaustive3. Certainty factor calculus
= for conflict resolution
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COPINGWITHCOMPLEXITY
1I
Small Search SpaceReliable Data and Knowledge
Exhaustive SearchMonotonic Reasoning
Single Line of Reasoning
i ii II
Unreliable Dataor Knowledge Time-Varying Data Big Search Space
I II
Combining Evidence State-triggeredExpectations Hiera rchicalfrom multiple sources
Probability Models Generate and TestFuzzy Models •Exact Models
II
5 9 11I I
I No evaluator for Knowledge BasePartial Solution Single model too weak Too Inefficient
I Fixed Order of Lines of Choice ofMultipleAbst racted Steps Data St ructu re
" ' " Reasoning Compilation
,6 J, I Cognitive Economy10Domain does not admit
Fixed Sequence Diverse Knowledge' ' Sou rces
Abst ract Sea rch SpaceHeterogenous Models
7 Opportunistic SchedulingVariable-Width Search
_Subproblems InteractL
I I I
Constraint PropagationLeast Commitment
i" IGuessing is Needed
-Plausibikeasningopendency-Di rected
li Backt rackin.q
66
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EXAMPLE
BATTERYCHARGECONTROL
1.54VOLTAGEITEMPERATUR'E CHARACTERISTICS
FOR MULTIPLE LEVEL NICKEL-CADMIUM!.52 BATTERY CHARGER
! .50
1.48
1.46G:
_n 1.44 _0, 8F-
1.42 (O. 7
I,-
_) 1.40>J•J 1.38
1.36 . •
REFERENCE
1.34 POINT /NO. 8 @ 1.520 *-0.015 VOLTS AND 0°C _10. 3
_,mV PER LEVEL = 0.020 _0.002 VOLTS
!.32 SLOPE - -2.3:3-+ 0.20 mV/°C NO. 2
1.38 - I0.1I I , I , I i , I ,
-10 0 .10 +20 +30
TEMPERATURE - DEGREES CENTIGRADE
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THE BUNCH-LINE
An Expert System (as a human expert) blends funclamentail knowledge, practitioners' wisdom, and skill
in the controlled application of data, Itnowledge, and tools
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SPACE POWER SYSTEM AUTOMATION WORKSHOP
MARSHALL SPACE FLIGHT CENTER
28/29 OCTOBER 1981
SPACECRAFTSYSTEM/POWERSUBSYSTEMINTERACTIONS
Chris Carl
MANAGER, SPACECRAFT SYSTEMS ENGINEERING SECTION
Jet Propulsion.Laboratory
Pasadena,California
C_
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INTRODUCTION
e TRENDSIN AUTOMATION
e CANDIDATESYSTEMREQUIREMENTSIPOLIClES
e SYSTEMCONSTRAINTSONSUBSYSTEMAUTOMATION
e FAULTPROTECTiON/CORRECTIONEXAMPLES
e CONCLUSIONS
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DRIVERSFOR INCREASEDON-BOARD AUTOMATION
e GROUNDCOSTS
e RES_NSETIMEREQUIREDIS << 2WAYoLIGHTTI_,_,E
e BLINDOPERATIONS
e MISSION-CRITICALACTIVITIESDURINGENCOUNTER
e LONGFLIGHTTIMES
e HIGHLYVISIBLE,ONE-SHOTPROGRA_,_S
i....i
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AUTONOMOUS FEATURES
Vl KINGEXTENDEDMARINERIV-X VIKINGORBITER MISSION VOYAGER GALlLEO
SUNACQUISITION e SUNACQUISITION e IBATTERYFAILI e SUNACQUISITION e SUNACQUISITION
J STARACQUISITION e STARACQUISITION [PROTECTIONI e STARACQUISITION e REDUNDANTINVERTERIe LBAFrERYCHARGEJ SWITCHOVER I
.l ,ou o TPO ,.fR,OU O TPOW,1 . ICHAINSWTCHOVER /CHAINSWITCHOVER e RECVRPROTECT SWITCHOVER e REDUNDANTTRANSMITI'ERSWITCHOVER
e AUTOMATICSEQUENCEe REDUNDANTTRANSMITTERe STOPA/C GASLEAKS e REDUNDANTTRANSMITTER
IV-VII SWITCHOVER e SCIENCEPROTECTION SWITCHOVER o COMMANDLOSS
]POWERSHARE] e COMMANDLOSS e DOWNLINKOFF e BACK-UPAUTOMATIC e [PWRCHECKJ0
, IBATTERYOVERT_,PI MISSIONe ROLLDRIFT e THRUSTERMANAGEMENTe IPOWERSHARE] MODEENTRY e COMMANDLOSS e GYROMANAGEMENT
e PRESSUREREGULATOR e STARTRACKER e [IRS PWR] e COMPUTERERROR1
FAILUREMONITOR PROTECTION e [PWRCHECKJ e TURNSUPPORTe ATTITUDECONTROL e ENGINEMONITOR e THRUSTERMANAGEMENT
POWERCHANGEOVER _ e AACSPROCESSORSWAPe AUTOMATION e GYROMANAGEMENT
e PLATFORMSAFINGe COMPUTERERRUR FUNCTIONMONITOR e COMPUTERERROR
e TEMPERATURECONTROL!LMOIPOWERTRANo_E,_,IC'_n-I e TURNSUPPORT
ee PROPULSIONSAFING
e AACSPROCESSORSWAte SEQUENCERESTART
e AACSHYBICSWAPo SClENCEPROTECTIOk.
e PLATFORMSAFING
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CANDIDATESYSTEMREQUIREMENTS/POLICIES
GENERALREQUIREMENTS
• THESPACECRAFTSHALLOPERATEW/OGROUNDCONTROLFORTBDDAYSW/ODEGRADATION
• BLOCKREDUNDANCY• FUNCTIONALREDUNDANCY• HI RELIABILITYCOMPONENTS
• THESPACECRAFTSHALLOPERATEW/OGROUNDCONTROLFORTBDDAYSWITHLESSTHANTBD% DEGRADATION
• GRACEFULDEGRADATION
• TRANSPARENCYOFAUTOMATEDACTIVITIES
• RELIABLE,TRANSlENT-FREERECONFIGURATIONS• MEMORY"KEEPALIVE"
• AUDITTRAILOFAUTOMATEDACTIVITIES
• STOREACTIVITIES• MEMORYREADOUT• FLAGSET
• GROUNDSYSTEMOVERRIDE
"RESTART• REPROGRAMMING
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_. CANDIDATE SYSTEMREQUIREMENTS/POLICIES
RELIABILITY
• NO SINGLEHARDWAREFAILURESHALLRESULTINLOSSOF MORE THANONE INSTRUMENTOR >.50%OF ENGINEERINGDATA
•BLOCKREDUNDANCY
•FUNCTIONALREDUNDANCY
•LOADMANAGEMENT
•FUNCTIONALINDEPENDENCE
• THECENTRALDECISION-MAKERSHALLBE THEMOSTRELIABLEELEMENT
• PROCESSORSSHALLPERFORMSELF-TESTPRIORTOISSUINGANY COMMANDS
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CANDIDATE SYSTEMREQUIREMENTS/POLICIES
FAULTPROTECTION
• FAULTRECOVERYTOAN UNAMBIGUOUSSTATE
• POWERONRESET
• FAULTSDETECTED/CONFIRMEDBY INDEPENDENTSOURCES
• HIGHRELIABILITYSENSORS
• MULTIPLESENSORS
• VOTING
• FAULTPROTECTIONAT LOWLEVELS
• SENSORSANDSWITCHINGAT LOWESTPRACTICALELEMENT
• FALSEALARMPREVENTION
• HARDWAREISOFTWARETOLERANCESTOBESETAT"UNACCEPTABLE"PERFORMANCE
€J1
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",,,,,I
CANDIDATESYSTEMREQUIREMENTS/POLICIES
SYSTEMSTATES
• SPACECRAFTSTATEPQSITIVELYIDENTIFIABLEFROMTELEMETRY
• STATUSWORDS
• AUTOMATEDACTIVITIESREVERSIBLE
• ANY SPACECRAFTSTATEAC-CESS]BLEANDCOMMANDABLE
SYSTEMTEST
• SYSTEMTESTPLANSSHALLBEPREPAREDEARLYIN_. DEVELOPMENTTOHELPVALIDATEAUTOMATEDROUTINES
• SUBSYSTEMSSHALLHAVEEARLYDEFINITIONOFAUTOMATEDOPERATIONS
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CANDIDATE SYSTEMREQUIREMENTS/POLICIES
SYSTEMTEST
• ALLUNITORBLOCKREDUNDANTELEMENTSSHALLPROVIDEACCESSFORCHECKOUT,CALIBRATIONANDREPROGRAMMING
• TESTPORTFORFAULTINJECTIONANDRESPONSE
• MEMORYACCESSIBILITY
• GROUNDIIN-FLIGHTVISIBILITY
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CANDIDATESYSTEMREQUIREMENTS/POLICIES
SOFTWARE
• TELEMETRYSHALLPROVIDEINFORMATIONTODETERMINETHEOPERATIONALACTIVITYANDSTATUSOFFLIGHTSOFTWARE
• PROTECTIONSHALLBE PROVIDEDAGAINSTWRONGOR INVALIDCOMMANDS
• MULTI-COMMANDS
• HANDSHAKE
• ECHO
• PARITY
• CODEDCOMMANDS
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CANDIDATESYSTEMREQUIREMENTS/POLICIES
MEMORY
- SUBSYSTEMSWITHVOLATILEMEMORIESSHALLASSURETHATDIRECTME/_ORYACCESSIS OPERATIONALAT POWERON RESET
, COMPUTERMEMORY MARGINSSHALLBE PRESERVED
•MEMORY MANAGEMENTDURINGDEVE ,_,TLOP/_-N,AND_I OPERATIONS
•ON-BOARDCOMPUTERMEMORIESVERIFTABLE
• MEMORYREADOUT
• CHECKSUM
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SYSTEMCONSTRAINTSc_
ON SUBSYSTEMAUTONOMY
AUTOMATIONIS NON-INTERACTIVEWITHTHESYSTEMIF IT DOESNOT:
e AFFECTTHESTATEORDATATAKINGOFMORETHANONESUBSYSTEM
e AFFECTTHEDOWNLINKMARGIN,TELEMETRYFORMATORRATE
e AFFECTISTORDERGROUNDPROCESSINGCONFIGURATION
I INCREASECENTRALCOMPUTERPROCESSINGORBUSTRAFFICOVER
ALLOCATIONS
o CHANGESTOREDSEQUENCES
e ALTERATTITUDECONTROLORSTABILITYMARGINS
e INCREASEPOWERDEMANDSABOVEMARGINS
e ALTERTHERMALBALANCE
e IMPACTSYSTEMINTERFACES
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SYSTEMCONSTRAINTSON SUBSYSTEMAUTONOMY
AUTOMATIONIS NON-INTERACTIVEWITHTHESYSTEMIF IT DOESNOT:
e ADVERSELYIMPACTSPACECRAFTSYSTEMLIFETIME,
RELIABILITY,ORPERFORMANCE
e ADVERSELYIMPACTSYSTEMORSUBSYSTEMSAFETY
e RESULTIN SELECTIONOFSYSTEMREDUNDANTRESOURCES
e IRREVOCABLYCHANGESPACECRAFTSTATE
oo
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_o FAULT PROTECTION/CORRECTION EXAMPLESVIKING SHAREMODE CORRECTION
e FUNCTION
TURNOFFLOADSWHENPOWERSUBSYSTEMIS UNABLETOBOOST
OUTOFAN UNINTENDEDSOLARPANEL/BATTERYSHARECONDITION
WHILETHESPACECRAFTIS SUNACQUIRED
e STRATEGY
e COMPUTERCOMMANDSUBSYSTEM(CCS)COUNTSBOOSTPULSES
FROMREDUNDANTSHARE.MODEDETECTORSWITHINPOWERAND
TURNSOFFLOADSIN PAIRSEACHTIMETHATTHENUMBEROF
PULSESINA GIVENTIMEPERIODEXCEEDSA PREDETERMINEDVALUE
e FORMISSIONPHASESOTHERTHANMARSORBITINSERTION,THE
CCSCOMMANDSTHESPACECRAFTTOA SAFESTATEPRIORTO
EXECUTINGTHESHAREMODECORRECTIONRESPONSE
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FAULT PROTECTION/CORRECTION EXAMPLES
VIKING SHAREMODE CORRECTIONt
' SOLAR_RRAY -_
PAI_EL.._ _-51 VDC RAWPO_ERI_US UNREGLr_.TED
r T 'ACS (,_rNARS) +i
Isu_̂mmmsm_LI - j [.SHARE/_ODEPULSES I' _
I ' REGULATED.__BOOSTC_l_ I ! ! SHARE I PaW_ :E_,LE!DISAI3LE j Ba(]ST ! IMCIDE ! r-F,,-
. [ ! ! i(REDUNDAI'_I')
_ ={ [ccs F__ ), iI_.__,..I := _ BAI'I"E_Y BATTERY
z I 2'7.4-_Z._ VDC CHAR_ CHAR_ _+
,_, CI.TT,2,]A/_P CI.TT,Z,]_JVIPI _ _w ' RATI_G RATING T
_ _ CELLS _ CELLS ,,, i_==_ _ _P.-FR _ ,a_l:X"F'R r
C:) €::_, 1a__ RATI'_ RAT!I_
I _.L _L !
+' L_ mm_s+s +
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*" VOYAGER "PWRCHK" EXAMPLE
• FUNCTION-PROTECTSAGAINST:
• INTERNALPOWERFAILURES
• EXCESSLOADPOW_ DEMAND
• STRATEGY-IF INTERNALPOWERFAILURE---
• SWITCHTOREDUNDANTE].EMENTS
• BRINGMISSION-CRITICALSYSTEMS& SEQUENCESBACKO_LINE
• SWITCHTOLOWRFPOWER
t WAITFORGROUNDASSISTANCE
IF EXCESSLOADDE_ND---
e SHEDALLF_NI)F(-CRITICALLOADS(INCLUDINGSC(ENCE}
• TURNONREPLACE_E]_1HEAT_S
• SWITCHTOLOWRFPOWER
• WAITFORGROUNDASS(STANCE
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VOYAGER POWERSUBSYSTEMSIMPLIFIEDBLOCKDIAGRAM
ESSENTIAL
POWER,...1,,__ 2.4kHzSOVRMS AC1I I 30VDCREG DC1 _ CCSA
" _"J RFRCVR CCSBNON-ESSENTIALPOWER AACSGYROS AACSPROC
INVSELECT ASCSHYBK1/2
FDS " TELEMETRY SUBSYSTEMPOWER!, !30'VDC DC2 --MDSTMU SUNpyRoSHUTTERpsuAIB
j I"-" S-BAN_-EXCPYROTU_' ' PRA,., , _j _i S-BANDTWTA PWS
RTGCASETEMP _ ._ _ S-BANDSEL LECP
RTGOUTPUTVOLT _ _ =E S-BANDXMTR PLS SCIENCERTGOUTPUTCURRENT _ _ o_, X-BANDXMTR UVSDCBUSVOLT _ _: _: X-BANDIINTA INSTRUMENTSSHUNTREGCURRENT _ 2! MAG_! z>i X-BANDEXC_I ISSNA, AACSHTRSDC BUSCURRENT ir _I__.i ISSWA2.4kH3INPUTCURRENT PROPHTR MIRIS
CRS2.4kz 2.4kHz CCS2.4kHz-INPUTVOLTAGE PRAANT2.4kHzOUTPUTVOLTAGE A PPS
INVERTERSTATUS T REPLHTRSSHUNTREGVOLTAGESHUNTREGTEMP TOLERANCEBATTERYTEMP DETECTOR
TRIP
cotj.1
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oo
CONCLUSIONS
e DEVELOPSYSTEMREQUIREMENTSANDDEFINESYSTEM
INTERFACES
e DEVELOPRELIABLESENSORS,ALGORITHMSANDEFFECTORS
e DEVELOPVAL!DATIONANDTESTMETHODOLOGY
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TECHNICALISSUESIN POWERSYSTEMAUTONOMY
FORPLANETARYSPACECRAFT
FredC.Vote
ElectricalPowerandPropulsionSection
Jet PropulsionLaboratoryOctober 28, 1981
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Oooo
Agenda
• EVOLUTIONOFSPACECRAFTPOWERSYSTEMREQUIREMENTS
• OVERVIEWOFAUTOMATEDSPACECRAFTPOWERMANAGEMENT(ASPM)PROGRAM
• FUTUREPLANETARYPOWERSYSTEMREQUIREMENTS
• TECHNICAUSYSTEM-LEVELISSUESIN PLANETARYPOWERSYSTEMAUTONOMY
• RECOMMENDEDPOWERSYSTEMAOTOMATIONOBJECTIVES
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Evolutionof PlanetarySpacecraftPowerSystemRequirements
• PLANETARYPOWERSYSTEMREQUIREMENTSHAVEBEENDRIVENBYMISSION/SPACECRAFTREQUIREMENTSANDDURATION
• SPECIFICPOWER
• RELIABILITY
• FAULTRESPONSETIME
• FLEXIBILITY
• AUTONOMY
co
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Power Subsystem Reliability Requirements
REQUIRED MISSION DURATION ROUND TRIP LIGHT TIME AT P W E T
NEPTUNE
URANUS e
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Fault Tolerance of .Power Subsystems
FAULTTOLERANTCOMPUTERS
COMMANDVERIFICATION
,MAINTENANCEOF .....MAXIMUMPERFORMANCE
FUNCTIONAL _REDUNDANCY
POINTFAILURES
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Power Subsystem Flexibility Requirements
7OOGALILEO
600 LOADS
500 "_ELI
O
FLEXIBILITYREQUIRED 400 >MEASUREDASNUMBERSOF
LOADS _ SEPARATETELEMETRYWORDS 300 o> COMMANDSSEPARATECOMMANDS
FORPOWERSUBSYSTEM
_I TELEMETRY:DS
060 64 68 72 76 80 84 88LAUNCHYEAR
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Power Subsystem WithoutOnboard Computation Capability
POWERSOURCE
UNREGULATED
POWERSPACECRAFTCOMMANOCOMMANOSPOWERREGU,.A'rEOAC._ POWERSUBSYSTEM SUBSYS_ANOOCPOWER-USERS
,, 1 _oArACOMMANDS SPACECRAftFROM "I1ZLEMETRYGROUND SUBSYSTEM
i
DATAI _. DATA.RECEIPT
ANALYSIS -ONGROUND ONGROUND
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_0
Power Subsystem WithOnboard Computational Capability
ii u i Ill
ONBOARD !
COMPU'IER POWERANDCOMMAND SOURCE
_ DATA,ICOMMANDS SPACECRAFT'" • IMPROVEDPERFORMANCEFROM "I£LEMETRY • FAULTTOLERANCEGROUND SUBSYSTEM
. • GRACEFULDEGRADATION
,1
DATA | DATARECEIPTII
ANALYSIS r ...... ONGROUNDONGROUND
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OverviewofAutomatedSpacecraftPowerManagement System(APSM)Program
o APSMPROGRAM
6 - YEARPROGRAM(1975-1981)
$I,9M
0 OBJECTIVES
o DEVELOPTECHNIQUESANDDEMONSTRATETECHNOLOGYTOPROVIDERELIABLE
AUTOMATEDPOWERSUBSYSTEMMANAGEMENTFUNCTIONWITHCAPABILITIESOF:
o PROVIDINGACCURATEASSESSMENTOFPOWERSUBSYSTEMPERFORMANCE
o DETECTINGANDCORRECTINGEQUIPMENTFAULTS
o MANAGINGUSERLOADS
o EVALUATETHEPERFORMANCEOFAUTOMATEDPOWERSUBSYSTEMMANAGEMENT
ASAPPLIEDTOTIIESOLARARRAY-BATTERYPOWERSUBSYSTEMUSEDOrlTHE
,_ VO75SPACECRAFT",,4
0 SERVEAS"PILOT"AUTOMATEDPOWERSYSTEM
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CO
APSMApproach
0 DEVELOPUPONA STATE.OF-THE-ARTPLANETARYPOWERSUBSYSTEM
o UTILIZETHEBREADBOARDVO75POWERSUBSYSTEM
0 CONTRACTEDEFFORTFORCONCEPTDEFINITIONANDIMPLEMENTATIOrI
(MARTIrlMARIETTA)
• TESTANDEVALUATIONBYJPL
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VO 75 Power Subsystem
ill
l it
REDUNDANTBATTERYCHARGERS
USERLOADS
INDIVIDUALLYFUSED
REDUNDANTBOOSTREGULATED_ACANDDCPOWERSOLAR UNREGULATED REGULATORAND -ARRAY DCPOWER INVERTERCHAINS ACP()WER DISTRIBUTION
_0
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VO 75 Power SubsystemAutomated Elements
BOOST t REDUNDANTiCONVERTER BATTERIES
REDUNDANT
BATTERY ICHARGERS I
AUTOMATIC USERLOADSCHARGEERMINATION i,,INDIVIDUALLY
FUSED
REDUNDANTBOOSTSOLAR UNREGULATED REGULATORAND REGULATED_AC AND DC POWERARRAY DC POWER INVERTERCHAINS AC POWER DISTRIBUTION
AUTOMATICFAULTDETECTIONANDPOWERCHAINSWITCHOVER
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Candidate Functions for Automation
Function Descriptioni ii
BATTERYCHARGECONTROL • AUTONOMOUSLYBEGINCHARGINGWHENSOCFELLBELOWA PREDETERMINEDLIMIT
• SWITCHTOLOWRATEWHENSOCREACHEDAPREDETERMINEDLIMIT
• PREDETERMINEDLIMITSVARIEDACCORDINGTOTEMPERATUREMODEL
i i i
POWERCHAINFAULTDETECTION • MAINANDSTANDBYBOOSTERREGULATORSCROSSANDSWiTCHOVERWITHCROSS STRAPPEDTOMAINANDSTANDBYINVERTERSSTRAPPING ALLOWINGANYPERMUTATIONOFINVERTERSAND
BOOSTREGULATORSUPONDETECTIONOFA FAULTii
SUBASSEMBLYPERFORMANCE • EFFICIENCIESCALCULATEDVIA INPUTANDOUT-MONITORING PUTVOLTAGESANDCURRENTSFORPOWER
DEVICESSUCHAS INVERTERS,CHARGERS,ETC.
• CELLMONITORINGWITHINBATTERIES
SUBASSEMBLYFAULTDETECTION • DETECTIONTHROUGHCALCULATIONOFREDUCEDANDRECOVERY EFFICIENCY
i-,a
• RECOVERYTHROUGHSUBASSEMBLYREPLACEMENT(BLOCKREDUNDANT)
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0
Candidate Functions for Automation (cont)
Function Descriptioni
i ill
POWERMARGINMANAGEMENT ,,SHAREMODEDETECTIONANDBOOSTCONVERTORTIME-OUTLEADINGTOLOADSHEDDING
LOADEQUIPMENTMONITORING " MONITORLOADVOLTAGESANDCURRENTSTOANDFAULTDETECTION DETERMINEIMPEDANCEOFLOADDEVICES
• IF IMPEDANCEFELLBELOWPREDETERMINEDLIMIT,DEVICEWASREMOVED
i
RELAYSTATUS.MONITORING • MONITOREDPOSITIONSOFALLRELAYCONTACTSINCLUDINGRELAYSFORCELLBYPASS,CROSSSTRAPPING,LOADDISTRIBUTION,ETC.
ii i ill ii i ,
DATAACQUISITION,PROCESSING,• SERIALDATABITSTREAM- RECONFIGURABLE
ANDSTORAGE • DATASTORAGEFORCOMPUTATION
MINIMUMSOLARARRAYMARGIN • PROGRAMMABLE,PRIORITIZED,SEQUENTIALPROTECTION LOADSHEDDINGIFSOLARARRAYMARGINFELL
BELOWA SELECTEDVALUEi i
SUBSYSTEMPERFORMANCE • DETERMINETHEHEALTH(EFFICIENCY)OFTHEMONITORING POWERSUBSYSTEMBYCOMPUTINGTHEINTERNAL
POWERLOSSES(TOTALSOURCEPOWERINPUTMINUSTHETOTALLOADPOWERDELIVERED)
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Candidate Functionsfor Automation (cont)
FUNCTION DESCRIPTION
LOADPROFILEDETERMINATION • UTILIZINGA PRE-PROGRAMMEDORGROUNDGENERATEDSEQUENCEOFSPACECRAFTCOMMANDS,CALCULATETHEMAXIMUMPOWERANDENERGYSTORAGEREQUIREMENTFORTHESEQUENCEANDCOMPARETOTHESOLARARRAYANDBATTERYSOURCESCAPABILITY.SENDANALARMFLAGTOTHEFLIGHTDATASYSTEMFORTRANSMITTALTOGROUND,IFSOURCECAPABILITYIS LESSTHANREQUIRED.
LOADSEQUENCEGENERATION eUTILIZINGTHEPRIORITIZEDSEQUENTIALLOADSHEDDINGDATA,GENERATEA NEWLOADSEQUENCEBASEDONPOWERSOURCECAPABILITY
0
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Implementation Decisionsc_
Candidate FunctionsFor AutomationFunction Rationale
r
BA'i'I'ERYCHARGECONTROL DEMONSTRA_REDUCEDMONITORINGREQUIREMENTS
POWERCHAINFAULTDETECTIONAND DEMONSTRATEINCREASEDFAULTTOLERANCESWITCHOVERWITHCROSSSTRAPPING ANDFLEXIBILII"Y
SUBASSEMBLYPERFORMANCEMONITORING 1 DEMONSTRATEINCREASEDFAULTTOLERANCE,FLEXIBILITY,AND
SUBASSEMBLYFAULTDETECTIONANDRECOVERY RECONFIGURABILITY
POWERMARGINMANAGEMENT DEMONSTRATEPOTENTIALFORREDUCEDPOWERSOURCEMARGIN
LOADEQUIPME_TMONITORINGANDFAULT DEMONSTRATEINCREASEDFAULTTOLERANCEDETECTION FLEXIBILITY,ANDRECONFIGURABIL.ITY
DATAACQUISITION,PROCESSING,AND DEMONSTRATEMOREFLEXiBLE,RECONFIGUR-STORAGE ABLETELEMETRYINTERFACE
RELAYSTATUSMONITORING DEMONSTRATEREDUCEDTELEMETRYREQUIREMENT
MINIMUMSOLARARRAYMARGINPROTECTION MAXIMUMPOWERPOINTDETECTORREQUIRED
SUBSYSTEMPERFORMANCEMONITORING
LOADPROFILEDETERMINATION COMPLEX,DOABLESOFTWARETASK
LOADSEQUENCEGENERATION
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VO 75 Power SubsystemAPSM Configuration
-BOOST t f REDUNDANTCONVERTER BATTERIES
REDUNDANTBATTERYCHARGERS
USERLOADS
tttttSOLAR r UNREGULATED REGULATORAND REGULATED_IAC AND DC POWI_R
ARRAY I" DC POWER INVERTERCHAINS AC POWER- DISTRIBUTION
I , I I ,r BATTERYCHARGECONTROL " FAULTDETECTIONAND • LOADMONITORINGAND" FAULTDETECTION& RECOVERY SWlTCHOVEROFELEMENTS FAULTDETECTION
• PERFORMANCEMONITORING " PERFORMANCEMONITORING " RELAYSTATUSMONITORINGi
LOCALPROCESSOR LOCALPROCESSOR LOCALPROCESSOR
I .. !'POWERMARGIN MANAGEMENT
.,SERIALBITSTREAMTELEMETRYi
'-' CENTRALPROCESSOR
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oO_
APSM Evaluation Results
Function Test Results
BATTERYCHARGECONTROL "STATEOFCHARGE • WITHIN+10%OVER3 CHARGE/ESTIMATOREVALUATION DISCHARGECYCLES
• BATTERYOVER-TEMPERA- • CHARGERSWITCHEDTOLOWRATETURESIMULATION
• BATTERYSTATEOFCHARGERESPONSETEST
• BATI'ERYDISCHARGED "CHARGERSWITCHEDTOHIGHRATE
• BATTERYOVERCHARGED,CHARGERSWITCHEDTOLOWRATE
POWERCHAINFAULT "MAIN INVERTERFAILURE • SWITCHEDTOSTANDBYINVERTERDETECTIONANDSWITCHOVERSIMULATION
• MAINBOOSTERREGULATOR-SWITCHEDTOSTANDBYBOOSTERFAILURESIMULATION REGULATOR
SUBASSEMBLYPERFORM- •CALCULATEEFFIClENCIESOF -RESULTSWITHIN5%ANCEMONITORING SUBASSEMBLIESANDCOM-
PARETORESULTSOFHANDCALCULATIONS
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APSM Evaluation Results (cont)Function Test Results
SUBASSEMBLYFAULT •BATTERYCHARGER •CHARGERTURNEDOFFDETECTIONAND RECOVERY EFFICIENCYBELOWLIMIT
SIMULAT!ON
• BATTERYCELLVOLTAGE •FAILEDCELLBYPASSEDANDBELOWLIMITSIMULATION SPARECELLCONNECTED
POWERMARGINMANAGE- • TOTALLOADSIMULATED • SEQUENTIALLOADSHEDDINGMENT TO BEIN EXCESSOFSOLAR SEQUENCEEXECUTED
ARRAYCAPABILITY
LOADEQUIPMENTMONITOR-•SIMULATEDVARIOUSLOAD ,ACCURATELYDETECTEDANDINGANDFAULTDETECTION FAULTS DISCONNECTEDFAILEDLOAD
• CALCULATEDEACHLOAD •CALCULATIONSWITHIN+2%IMPEDANCEANDCOMPAREDTO RESULTSOF HAND _,_CALCULATIONS
RELAYSTATUSMONITORING •TESTEDBYEXECUTIONOF •ACCURATEMAINTENANCEOFSEQUENTIALRELAYEXCITA- RELAYSTATUSDATATION COMMANDS
,_. DATAACQUISITION, "COMPAREHARDWIRE "ACCURACYOFAPSMDATAWITHIN•_ PROCESSINGANDSTORAGE MEASUREMENTSWITH MEASUREMENTTOLERANCES
APSMDATA
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c_oo
APSMResults
• TECHNICAL
• PROGRAMMATIC
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APSMTechnicalResults
• ACCOMPLISHEDOBJECTIVESOFDEMONSTRATINGTHEAUTOMATIONOFKEYFUNCTIONSIN POWERSUBSYSTEM
• CONTINUOUSMONITORINGNOTREQUIRED
• ALGORITHMSFORKEYFUNCTIONSSUCHAS LOADMANAGEMENT,SUBSYSTEMFAULTTOLERANCE
• HIGHLIGHTEDIMPORTANCEOFSYSTEMCONSIDERATIONSSUCHASINTERFACEMANAGEMENT
• NEWINVENTIONSNOTNECESSARYTOACCOMPLISHOBJECTIVES
• APSMACTIVITYHIGHLIGHTEDFUNCTIONSTHATWOULDBENEFITFROMADVANCEDTECHNOLOGY
• ACCURATESTATEOFCHARGEINDICATOR
• SELF-TESTOFSTANDBYUNITS
• MAXIMUMPOWERPOINTDETECTOR
• MODULARITYo
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i,-a
° APSMTechnicalResults(Cont)
• AUTOMATIONCOULDBESUCCESSFULLYACCOMPLISHEDWELLWITHINSTATEOFTHEARTOFONBOARDCOMPUTATIONALCAPABILITY
• USEOFONBOARDCOMPUTATIONALCAPABILITYCANHAVEPOSITIVEEFFECTONPOWERSUBSYSTEMCHARACTERISTICS
SPECIFICPOWER 50_ INCREASEWHENCOUPLEDWITHADVANCEDTECHNOLOGY
PRELAUNCHCOST SLIGHTREDUCTION- SINGLESPACECRAFT40°/oREDUCTION- FIVESPACECRAFT
OPERATIONSCOST 5_oREDUCTION
FAULTTOLERANCE IMPROVEDTHROUGHPERFORMANCEMONITORING
FLEXIBILITY INCREASEDWITHRECONFIGURABILITY
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APSMProgrammaticResults
• MORECOMPLEXTASKTHANORIGINALLYANTICIPATED
• IMPORTANCEOFCORRECTMIX OFPOWERSYSTEMENGINEERS,SOF'IWAREEXPERTS,AUTOMATIONEXPERTS
• "SYSTEMS"VIEWPOINTESSENTIALFORMAXIMUMBENEFIT
*DISTRIBUTEDvs CENTRALIZED
. REDUNDANCYMANAGEMENT
*DEGREEOFMODULARITY
• NEEDFORMANAGEMENTOFSOFTWAREDESIGN
_l-,J
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FuturePlanetarySpacecraftPowerSystemRequirements
CONS!DERATIONS
I SPECIFICPOWER
e DEGREEOFAUTONOMY
e RELIABILITY
o INTERDEPENDENCEOFPOWER/SPACECRAFTDESIGN
e DISTRIBUTIONOFCOMPUTATIONALCAPABILITY
e MISSIONDURATION
e ROUNDTRIPLIGHTTIME
o POWERSYSTEMCOST
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AdvancedPlanetaryPowerSystemRequirements
SPACECRAFTREQUIREMENTS
FAULT POWERSYSTEMTOLERANCE REQUIREMENTS
COST FLEXIBILITY
LONG AUTOMATIONLIFE
• POWERSYSTEMREQUIREMENTSAREINTERACTIVEWITHMISSIONANDSPACECRAFTDESIGN
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TypicalPowerSystemMass
POWER MASS,KGKW
SCI ENCE SPACE- POWER POWER _PAYLOAD CRAFT ELECT SYSTEM PWR/SC PWR/PAYLOAD.
VIKINGORBITER 0.6 73 2540 37 178 7 240
VOYAGER 0,48 108 792 25 137 17 130
GALlLEO 0,6 98 2078 30 147 7 150
NEP (N_PTUNE) 100 150 17000 685 3990 24 2660URBITER
SEP (HALLEY) 25 124 2082 312 1112 53 900
O HIGH POWER SYSTEMS NEED GROWTH FROM 4 W/KGTO 25W/KG
O ADVANCED POWER SYSTEM R & D HAS LARGE POTENTIAL PAYOFF,I
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FutureRequirementsAdvanced PlanetaryPowerSystemsDRIVERS
• LOWPOWERSYSTEMS(0.4- I kw)
LOWCOSTDESIGNS- HIGHINHERITANCE
LONGLIFE
REDUCEDMISSIONOPERATIONS
REDUCEDSYSTEMMASS
FAULTTOLERANCE
• HIGHPOWERSYSTEMS(10-1000kw)
REDUCEDSYSTEMMASS
FAULTTOLERANCE
LONGLIFE
REDUCEDMISSIONOPERATIONS
LOWCOSTDESIGNSi-..I
l.,a¢j'I
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C_
System-LevelIssuesinAdvancedAutonomous Planetary PowerSystems
1. DEGREEOFPOWERSYSTEMAUTONOMYREQUIRED
2. DISTRIBUTIONOFON-BOARDPROCESSINGANDCONTROLFUNCTIONS
3. EFFECTOFPOWERSYSTEMAUTONOMATIONONUSERSYSTEMREQUIREMENTS
4. EVALUATIONOFBENEFITSOFFLEXIBILITYANDMARGINCONTROLS
5. IMPACTOFPOWERSYSTEMAUTONOMYONSPACECRAFTDESIGN
6. DEFINITIONOFDIGITALDATAANDCONTROLINTERFACES
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TechnicalIssuesinAdvancedAutonomousPlanetaryPowerSystems
1. COST/BENEFITUNCERTAINTYFROMPOWERSYSTEMAUTONOMYMASS/COMPLEXITY/COST
2. DEFINITIONOFPOWERSYSTEMAUTONOMYSTRATEGIESWHICHDONOTIMPACTRELIABILITY
3. DISTRIBUTIONOFPOWERSYSTEMAUTONOMYBETWEENDIGITALANDANALOGFUNCTIONS
4. INFLUENCEOFPOWERSYSTEMCHARACTERISTICSONAUTONOMATIONSTRATEGIES(ACVERSUSDC,etc.)
",..,.I
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RecommendedPlanetaryPowerSystemAutomationObjectives
i, IDENTIFICATIONOFPOWERSYSTEMFUNCTIONSWHOSEAUTOMATIONHAS
HIGHESTPAYOFFS(MASS/COMPLEXITY/COST)
2, DEVELOPMENTOFA METHODOLOGYFOREVALUATINGBENEFITOFAUTOMATING
SPECIFICPOWERSYSTEMFUNCTIONS
3, DEVELOPMENTOFCRITERIAFORDISTRIBUTINGDATAANDCONTROLFUHGTIONS
o GROUNDVERSUSON-BOARD
• ON-BOARDCENTRALVS,DISTRIBUTED
4, ASSESSMENTOF INTERACTIONOFAUTOMATIONSTRATEGIESWITHPOWERSYSTEMCHARACTERISTICS
o AC/DCDISTRIBUTION
o VOLTAGELEVEL
• DIGITAL/ANALOGLOGIC
5, IDENTIFYPOWERHARDWAREDEVELOPMENTSREQUIREDFORAUTOMATION
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MARTINMARIETTAPOWERSYSTEMAUTOMATIONEXPERIENCE
l.._a
L.O
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• t',O
AUTOMATEDPOWERSYSTEMSCONTRACTSANDRELATEDIR&DPROJECTSII III
Customer PeriodofTitle or IR&D Performance Descriptionof Effort
FlexibleCharge D61D 1975-1976 - Single-Cell ProtectionandCellDischargeController IR&D Bypass(FCDC) - A-h Integration ChargeControl
- Uses Intel 8080Microprocessor- BreadboardSystemControlling
Thirty 8 A-h NiCdCells
Single-Cell Protector NASA 1975-1976 - Monitor Single-CellVoltageand(SCP) LeRC Cell Bypass
- AnalogandDigital LogicImplementation
- PrototypeSystemDemonstratedon Single40A-h Cell inLife-CycleTest
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AUTOMATEDPOWERSYSTEMSCONTRACTSANDRELATEDIR&DPROJECTS(cont)
Customer PeriodofTitle or IR&D Performance Descriptionof Effort
MultiplexedCell NASA 1976 - Sameas SCPwith FollowingProtector(MCP) Differences:
MCPMultiplexes18-CellBatteryPrototypeSystemDemonstratedwith 18-CellBattery
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AUTON'_TEDPOWERSYSTEMNIANAGEMENT(APSM)II II I II
SponsoringAgency:JetPropulsionLaboratory
ContractPhases:- ConfigurationStudy- HardwareContract
Periodof Performance:1977-1979
ContractDescription:- SystemHIWDesign- SystemSIWDesign- SystemConceptualDesign- IntegrateDesignHIWandSIWwithVikingOrbiter75Government-FurnishedHIW
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LINEARCHARGECURRENTCONTROL(LC3)i _ I II I I IHII
ProjectSupport:
- Air ForceSupportedPartof Effort- Internal IR&DProjectSupportedAnotherPartof Effort
Periodof Performance:1976-1980
Objective: ImplementationFeature
- LongLife,HighReliability - SpecialNiCdChargeControlAlgorithm- IndividualCellMonitor
- HighLevelof LoadManagement - AccurateStateof ChargeMonitorandTelemetry
- LighterWeightandLowerVolume- UniquePowerH/WApproachThat
DoesNotUseSwitchingRegulators
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POWERSYSTEMGOALSUTILIZINGDISTRIBUTEDMICROPROCESSORAPPROACHIII I II I II
SpacecraftComputer DataCom SystemBusData
Monitoring /-- EPSCentral Local
Diagnosis ... r_.,__ Computer MicroprocessorCabling
Ik I",- r System
Subassembly1I
GSE Microprocessor
ReduceGSE BatteryAcceptanceTests CycleLife
WeightPowerSystem ReliabilityBusCabling PowerConditioningEquipment
PowerSystem EfficiencySubassemblyN Weight
FlexibilitySolarArray
SizeWeight
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FunctionalCapabilityHI
TheLC3 Is aFlexibleBatteryChargeControlSystem
- BatteryTemperatureControl
- BatteryTemperatureCompensatedVoltageControl\
- Ampere-HourIntegration
- CautionandShutdown
e_
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Po
ElectricalCapabilityII I
II
Theelectricalcapabilitylistedis forthe breadboardsystem.Thebasicdesignis not limitedto these levels.
- OutputVoltage:20to40Vdc
- Input Voltage. 20to 42Vdc
- OutputCurrent: Oto40A
- Efficiency:96.7to 97.1%MaximumLoad
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EPS MOCKUP FUNCTIONAL DIAGRAM
linearrBalj;j-Y-- .,
Cur renl ! Regulator ~
--- Regulalor 1 "~eq ulaled I 1SOLAR ARRAY BUS
~I-~~ .J:. load Bank
IUnr egUla~~TI 0-j
Model EPS
linearrBilluy- , Output
•r"tllar S(,lar
>-- - Currenl! Regulator • Bus
I'll r ay Array ~RC!lIlla 10 r
1 fRegulated • 1<;jl'lulalor ... - -_ ... Si",',lalo r~ Model _J !
lippe, UpperSegment '--- Segment f.-
fUor eg ula::1:;
I
E
n Sequent-Model ~
Ballery~,~.!.!!!l~ia'
~
Partial• Celf Vollage
=>
~~._- ~ Shunt -- • Ballery Vollage ~
rfc::
• Ballery Temperalure.2
)oJar ~-- ~rray..:. ~
",:;
olar • Ballery Currenl ;;;.;.: ~§'\rr ay ~rr ay ~egulator
\:>~
Simulator Simulator
Q
-- --.lOIVe r loove r
~)l'<Jmenl 1--1 Sl"llllent
"--0
I n
. - 0--'~!
l, • 1
Sy~>lt/lllnter'ace IConlroll UnitSystem Moclup Tes.~
Mkrollfoces50rlMkrocomputer Interlace• EPS Power Management• Batlery Charge Cootrol• EPS Energy Balance Control• (PS fa 1111 Prolec lion
i ",-rnal
• Correclive Actions
Da!," r,',"'uand IlI1k.:'D.~hca'ed Ballery II Mananeo",nl MicroorOl.essors
[olMnalnala; L'll'lllla 1I11 LillI< , I l'O'.'ler MaIl.Jwmenl MlCrocompulPr }---
& I'eripherals-
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co
POWERHARDWAREADVANTAGESJI I
SizeandWeightReduction:
- NoSwitchingRegulators
- NoLargeMagnetics
Efficiency:
- NoSwitchingRegulatorLosses
- DissipationReducedbya Factorof2 to3
- SolarArraySizeReduction
EMC:
- SwitchingRegulatorsarea PrimeNoiseSource
- Noiseis ReducedConsiderably
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PROGRAMMABLEPOWERPROCESSOR(p3)i I II B
NASAMSFCObjective:- Design,Build, andTestp3
IR&DProjectObjective:- PerformQualificationTestingon p3Periodof Performance:Nov1979-Nov1981
Objective- !.mplementationFeature- ReduceDevelopmentCost _ p3DesignCanBeUsedfor SeveralFunctions
- NoH/WChangesOtherThanROMChangeRequiredto ChangefromOneModetoAnother
- UsableonSeveralSIC - FlexibleInterfaceCommandandDataInterface
- DevelopMechanicalDesign,andBuildEngineeringModel
- MinimizeSizeandWeight
- PerformPreliminaryQualificationTest
r,o_o
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0
p3FunctionalCapabilityIIII I I I
A singlep3componentcanoperatein severaldifferentmodes.
- BatteryControl
- BatteryCharger- PeakPowerTracker(SolarArray)- CautionandShutdown
- BusVoltageControl
- VoltageRegulator- CautionandShutdown
- PowerLimiter(ShuttlePowerExtensionPackage)- PeakPowerTracker- FuelCellCurrentLimiter- CautionandShutdown
- PowerBusOverVoltageProtection
- ShuntRegulator- CautionandShutdown
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RequirementsI .......... I Ill IIlI
INPUT
VOLTAGE: 26VDCTO375VDC
VOLTAGE 450 VOLTS FOR 20 MS
TRANSIENT
POWER: LESSTHAN20 Kw
INRUSH: 25 JOULES ABOVE NORMAL LOAD
RIPPLE: 5,0 AMPS RMS
(.,0
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Co
RequirementsI I I
Output
Voltage: 24Vdcto180Vdc
Degraded,Performance: 0 to24Vdc
Current: 0 to I00Adc
DCPower: InputVoltage OutputVoltage OutputCurrent150Vdc 30Vdc 90Adc250Vdc 150Vdc 40Adc200Vdc 150Vdc 80Adc
Theabovesteadylevelsarerequiredforbaseplatetemperaturesof lessthan 30oc.
I.l%XV0 RippleVoltage,VoltsRMS
Ripple: II .5%xV0I _ !I II _ !.
30Hz 50KHz1.5KHz
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p3SimplifiedBlockDiagramIII r I I I I II
j J p2Power Stage _ _ Output
_-"'_ _ _L!.. Power
lt--tPower BaseDrive
Bias I ' lt----I (PWM)'"_ Internal
Regulator JPulseWidth Modulator -_ I/O
tl--I F-I_
p2 Control J-
RIUFMDM orI/F Processor I PROM j IPC/,
I Patch t p3 ProgrammablePower ProcessorTo RIU or FMDM "[ Plug T-- p2 Power Processor
PC/I ProgrammableController and Interface
p-=
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l.-a
(ao
MINIATUREAUTOMATEDPOWERSYSTEM(MAPS)II I I I | I I III
Periodof Performance:May1982
SystemDescription:
- TotallyAutomatedTerrestrialBatteryCharger- TwoSeries6A-h NiCdCells- SolarArray PowerSource- RCA1802Microprocessor- l-k, 8-bitCMOSROM- OneHundredTwenty-Eight8-bitCMOSRAM- MonitoringEachCell, If Cell Is Bad,Replacewith OneofFourSpareCells- PowerSupplyOperatesDownto 0.5Vln Voltage
Status:
- BreadboardBuildandTestComplete- PackagingDesignto Be InitiatedSoon
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TECHNOLOGYISSUESII I I I
I) DevelopingEntirePowerSystems,PowerSystemSubmodules,andlorLowerLevelComponents
2) Approachto RequirementDefinition.forAdvancedPowerSystemDevelopment.
3) SICPowerSystemControlPartitioningin Areasof LoadManagement,FaultDetection,andCorrectiveAction
4) SICandSubsystemControlH/WandS/WArchitecture
5) ControlMethodsandResultingAlgorithmsfor NewComponents,suchasNiH2Batteries,andfor NewAnnlications,suchasShuttlePEPPowerLimiter
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SPACE POWER SYSTEM AUTOMATION WORKSHOP
28/29 OCTOBER 1981
MARSHALL SPACE FLIGHT CENT_P
Dave Massie-AFWAL/POOCWPAFB,'OH 45433513-255-6235
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DEVELOPMENT HISTORY - SUPPORTING TECHNOLOGY
0 HIGH VOLTAGE HIGH POWER SYSTEM O MEGAWATTTURBOALTERNATOR TECH.
O ADVANCED SILICON AND GALLIUM AR- O PM GENERATOR TECH.SENIDE SOLAR CELLS
0 HIGH POWER SWITCH TECHNOLOGYO NICKEL-HYDROGEN BATTERY TECH.
0 ADVANCED POWER PROCESSOR TECH.0 HIGH ENERGY DENSITY RECHARGEABLE
BATTERY TECHNOLOGY 0 SC INDUCTIVE ENERGY STORAGE TECH.
0 HIGH EFFICIENCY MULTIPLE BANDGAPCASCADE CELL TECHNOLOGY
0 CONCENTRATING PHOTOVOLTAIC POWERSYSTEMS TECHNOLOGYDEVEL.
0 PRIMARY FUEL CELL TECHNOLOGY
0 REGENERATIVE FUEL CELL TECHNOLOGY
0 NUCLEAR RADIATION HARDENING TECH.
0 LASER RADIATION HARDENING TECH.
0 LIGHTWEIGHT SOLAR ARRAY TECHNOLOGYFRUSA, HASPS
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AUTOMATIONOBJECTIVE
AUTOMATIC REAL TIME MONITORING OF EPS HEALTH, COMPUTATION, AND
COMMAND/CONTROL OF SPACE VEHICLE POWER FROM SOURCE TO LOADS
BASED UPON SENSING
o TEMPERATURES
o PRESSURES
o CURRENTS
o VOLTAGES
o ANGULAR POSITIONS
o ACCELERATION
o DISPLACEMENTS
LOtO
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o
BENEFITSOF POWER SYSTEM AUTOMATION
0 IMPROVED RELIABILITY/SURVIVABILITY
O SIMPLIFIED GROUND STATION COMMAND AND CONTROL FUNCTIONS
RELATED TO SPACE VEHICLE ELECTRICAL POWER SYSTEMS OPERA-
TIONS
O REAL TIME ELECTICAL POWER SYSTEM STATUS AND CONTROL
0 QUICK RESPONSE TO CHANGING POWER NEEDS AND NEEDS FOR SELF-
PROTECTION - VIRTUALLY NO TIME DELAY BETWEEN SENSING ANOMALOUS
OPERATION AND EPS "SAFING"
O LOWER WEIGHT AND COST (PARTICULARLY IN THE ESS)
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AUTOMATED POWER SYSTEM GENERAL FUNCTIONS
0 POWER MANAGEMENT
O LOAD MANAGEMENT
O RELIABILITY MANAGEMENT
O CONFIGURATION MANAGEMENT
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4_r,o
AUTOMATEDPOWER SYSTEM SPECIFICFUNCTIONS
O BATTERY CHARGE/DISCHARGE CONTROL, PROTECTION AND RECONDITIONING
O POWER SOURCE CONTROL AND VOLTAGE REGULATION
0 FAULT DETECTION,ISOLATION,AND AUTOMATICCORRECTION/COMPENSATION/RE-
CONFIGURATION
O EPS HEALTH AND STATUSMONITORING
O EPS DATA PROCESSING,DATA STORAGE AND RETRIEVAL
O SOLAR ARRAY ORIENTATION CONTROL
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ISSUES
0 FAILURE TO INCORPORATE AUTOMATIC DETECTION OF EPS FAULTS
WITH SUBSEQUENT ON-BOARD CORRECTION/RECONFIGURATION WILL
RESULT IN CONTINUED INCREASE IN RELIANCE ON GROUND STATION
COMMAND/CONTROL/DATAPROCESSING
O STATION COMMANDAND CONTROL FUNCTIONS VERSUS AUTOMATEDCOM-
MAND AND CONTROL FUNCTIONS
0 ABILITY TO PREDICT POWER SYSTEM PERFORMANCE PARAMETERS FOR
THE LIFETIME OF THE SPACE VEHICLE
O NEED FOR CONTINUED OPERATION OF MILITARY SPACE VEHICLES WITHOUT
GROUND STATION COMMAND/CONTROL
O DEVELOPMENT OF STATUS MONITORING/SENSING CIRCUITRY AND CONTROL
ALGORITHMS
4_
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TASK 682JI0 - FAULTTOLERANTPOWERSYSTEM
Section I Requirement
a. Background - Program Genesis and Motivation
Satisfactory operation of military satellites is dependent upon
an adequate and reliable source of electrical power. Over the years
solar array/battery power systems have operated to a significant degree
under the command/control capabilities of satellite tracking stations
which periodically monitor the health of the system. With the advent
of advanced microprocessor and computer technology is is now feasible
to provide an autonomous electrical power system management capability.
Such a capability would greatly relieve and simplify ground station
commandand control functions related to satellite electrical power
system operations.
Satellites are not always in communication with ground
stations. Therefore, in the event of a power system anomaly, the
capability to autonomously sense the anomaly and reconfigure the
operation of the power system would enhance the reliability of the
system. The key to achieving this capability is to place each element
of the power system under the control of a dedicated local microprocessor/
microcomputer as illustrated in Figure I. This approach would permit
power system capability to perform automatic real time monitoring of
health, computation, and command/control of spacecraft power from source
to loads. Virtually no timedelay would be encountered in sensing and
"safing" electrical power system operations in the event of malfunctions
thus avoiding severe system degradations which might otherwise occur.
The automatic fault detection and correction capability could also
significantly enhance the survivability of the spacecraft power system.
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k
,°,°____L__ L[ -*' '_sArray Load _ Loads
Oistributor _ (Simulator)(Simulator) Charger Battery Battery
Regulator I
r-...... l -1 II Local Local Local Local Local , i Local
I Microprocessor MicroprocessorMicroprocessor Microprocessor| Microprocessor Microprocessor II " I
L_ ' 4 J....--" - _L- -_ -- Z --_---'_'_- -- -- -1__ I I , kk..--- SystemContro.
Oedicated£PS InterfaceMicrocomputer(Intel 8080)
2_l___t_(;roundControlCentralComputerand/orCommandSimulator
Figure 1 - Fault Tolerant Power System Schematic
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b. Objective - ImprovementsAnticipated
The objectiveof this new task is to demonstratea Fault
Tolerant Power System for military space vehicleapplications. Ability
to autonomouslydiagnose,detect,and correct faults are principal
featuresof the system. As such the systemwould possess inherent
capabilityto operate independentof external command/controlnormally
providedby satelliteground trackingstations. Ground stationcommand/
control involvementwould only be required in the event that a system
anomalyresults in an alarm situationwhere parametersbeing automati-
cally monitoredexceed pre-establishedmaximum or minimum limits. For
any anomaloussituationsshort of alarm situations,automaticon-board
reconfiguration/correctionwould be implementedwith a subsequentreport
to ground stations. Improvementsresultingfrom a Fault Tolerant Power
System Concept include:
• Autonomy
• Survivability
• ImprovedReliability
• Real Time ElectricalPower System Status
. Lower Cost and Weight
• Design Simplicityand Flexibility
The Fault Tolerant Power System (FTPS)will be able to quickly
respond to changingmission power needs and needs for electricalpower
system self protectivemeasures. Examples include (a) load matching to
power system capabilitysuch as switchingoff non-essentialloads under
conditionsof low bus voltageor supplementingsolar array power with
batterypower, (b) automaticdisconnectof defective loads,and (c)
switchingout defectivebatterycells and switchingin good spare cells•
The ability to utilizeSpare batteryceils as opposed to use of redundant
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batteriesprovidesa tremendousweight savings in the electricalpower
system - doubling or perhapstriplingeffectiveenergy density of the
energy storage subsystemin the FTPS approachmay be possible.
c. PotentialApplications
Technology derivedfrom the FTPS ADP will be applicableto a
wide range of futureAir Force space vehicleswhere a high degree of
autonomy,survivability,and reliabilityare required. Furthersatellite
traffic in earth orbit will escalate substantiallyin the post 1980
time period. Consequently,it will become increasinglydifficultfor
these stations to keep up with command/controland data processing
requirements. Automationfeaturessuch as those provided by the FTPS
will help to relieveand simplifyground station satellitesupport
requirements. The spectrumof mission operationsto wnich this techno-
logy applies includesurveillance,communications,meteorology,and
navigation.
d. RequirementsDocumentList
The latest approvedtechnicaldirectiondocumentcoveringwork
relatedto this task is ProgramManagementDirectiveR-S 2133 (9)/PE
63401F dated 23 December 1977. It should be pointedout however that
this task is being proposedas a new initiativefor FYSI start. This
task is responsive to SAMSO/ESDTechnologyNeeds TN-SAMSO-AFAPL-IO02-
70-15, "Solar Cell Power Systems";TN-SAMSO-AFAPL-lO02-76-20,"High
EfficiencySpacecraftPower Generation".andTN-ESD-AFAPL/AFCRL-IO02-
.70-01,"Solar EnergyConversion".
Section II TechnicalApproach
a. TechnicalApproach
The technicalapproachencompasses(I) command and control
design tradeoffs,(2) developmentof sensingcircuitry,signal condition-
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ing circuitry,and associatedalgorithms,(3) microprocessor/micro-
computer interfacedefinition,(4) design,fabricationand demonstration
of a breadboardFault Tolerant Power System as illustratedin Figure J
for ground demonstration,and (c) developmentof preliminarydesign
specificationsfor fault tolerantsystems operatingin the load power
range from 5 to 25 KWe. The FTPS breadboardwill be configuredto
performand demonstratethe followinggeneral type functions:
• Load ManagementFunctions
• Power Management Functions
• ReliabilityManagementFunctions
• ConfigurationManagementFunctions
In providingthe above type of generalfunctions,the FTPS will demon-
strate many specificfunctions. Examplesof specific functionsare as
follows:
• Battery Charge/DischargeProtectionand Reconditioning
• Solar Array OrientationControl
• Power Source Controland VoltageRegulation
• Fault Detection,Isolation,and Correction
• Power System Data Storageand Retrieval
The ground tests of the FTPS breadboardhardwarewill be geared
to demonstratingthe generaland specificfunctionsdefined above.
Resultsof these tests plus the knowledgegained during the course of
the FTPS programwill be utilized in the preparationof design specifi-
cations•
b. AlternativeApproaches
Redundancyat the unit level is a possiblealternativeapproach
to the FTPS concert, however;standbyunits would add considerablecost
and weight• Automatic failuredetectionand switchoverto standbyunits
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is really a trend toward the FTPS conceptanyway. Failureto incorpo-
rate automaticfailuredetectionand switchoverwould increasereliance
on active ground stationcommand/control/dataprocessingrather than
relieve such reliance. Thus, there are no apparentgood alternative
approachesto the FTPS for providingthe requisitehigh degree of
autonomy,reliability,and survivability.
c. TechnologyTransition
Resultsof this task will establishan advanced technology
base for implementingFTPS concepts into future Air Force space vehicle
systems. The task will demonstratethe autonomyand flexibilityof the
concept througha completeand thoroughground test program. Specifi-
cationswill be developedfrom which future systemscan be tailored.
The technologyderivedfrom this programwill be factoredAnto the
developmentof the High VoltageHigh Power System of Task 682J08.
Section Ill DevelopmentSummary
a. ProposedContractualand AFAPL supportingefforts under Task
682JI0 are structuredfor the successfuldevelopmentand laboratory
demonstrationof a Fault Tolerant Power System breadboardmodel. Test
data and FTPS specificationswill be end items of this advanceddevelop-
ment programtask.
The work will not requirethe developmentof specialized
microprocessormicrocomputertechnology. Instead,commerciallyavailable
microprocessorsand a microcomputerwill be utilized. Some specialized
sensingcircuitrywill have to be developed. An example is an ampere-
hour integratorcircuitfor measuringbatterystate-of-charge.
A developmentstep outline for the FTPS Task is as follows:
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DevelopmentStep/Event InitiationDate CompletionDate
FTPS SOW/RFPPreparation; l Oct 1980 l Feb 1981TechnicalEvaluationofProposals;Contract Prep.
Power System Performance l Feb 1981 l Aug 1981Predictions;Command&Control DesignTradeoffs
DevelopSensingCircuits l Jun 1981 30 Oct 1981and Algorithms
Microprocessor/Microcomputer l Sep 1981 30 Nov 1981Integration
BreadboardFTPS Ground l Feb 1981 l Mar 1982DemonstrationHdw Design (Go/No Go)
Fabricationof FTPS Ground l Mar 1982 30 Sep 1982DemonstrationHdw
FTPS Test & Evaluation l Oct 1982 30 Jul 1983
Final Report & Design 30 Jul 1983 30 Oct 1983Specifications
b. EvaluationCriteria
Key items effectingdevelopmentof the breadboardFTPS are (a)
power system performancepredictions,(b) command and controldesign
tradeoffsand (c) developmentof sensingcircuitsand algorithms. These
key elementsof work will receivepriorityattentionearly in the program.
An InterimTechnicalReportwill be deliveredat the twelfth (12th) pro-
gram month covering resultsof these key items.
Design of the breadboardFTPS will proceed _n parallelwith
other elementsof work culminatingin a Critical Design Review upon
completionof approximatelyfifteen (15) months of effort. The CDR is
a Go/No Go decision point in the program. Providedthere are no
insurmountableproblems identifiedas a result of the CDR, the contractor
will be authorizedto proceedwith hardwaremanufacture,integrationand
test.
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c. Schedule
The overallschedulefor the variouselementsof work to be
conductedunderTask 682ji0is shownin the attachedAFSC FormI03 -
ProgramSchedule.Totaldurationof theeffortis approximately
thirty-six(36)monthsfundedover threefiscalyears- FY81,82 and
83.
d. Progressand Accomplishments
AFAPLhas initiateda literaturereviewpertainingto the
varioustechnicalconsiderationsrelatedto the proposedFaultTolerant
PowerSystem. Knowledgeresultingfromthisreviewwill be used to
improveTask682JI0planningand preparationof a highqualitystatement
of work if thistaskis approved.
e. Resources
I. Financialand Manpower- see summary.
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SYSTEM (project) NUMBER Fault SUBSYSTEM TYPE OF SCHEDULE AS OF" DATEPROGRAMSCHEDULETolerant Power /stem Advanced Develo(_
IX) L FY 19 FY 19, ,982 1983 ,984N cY 1980 cY_ 81E :4 I 12 3 4
1
FTPSTPP Submission: i
ete
)aration uE
7 and Tech. Eval. of Proposals iB
9 Power Performance Predictions_o nl .:r it l_; Command& Control Design Trades12
,3 Sensln 9 Circuits & Algorithms14
,slrhcroprocessor/M!crocomputer r: C,-i,6!Inteqration w ._v.r_17
,8Breadboard FTPS Ground_ Demonstration Hdw. Desiqn2O
2; Fabricate FTPS Groundz2 Demonstration Hdw.Z3
z_ FTPS Breadboard Test & Evaluation_s
_.6Final Technical Report &• J ° •
;_ Design Specifications_8
_0
||
|2
|3
14
_5
;6
AUTHENTICATION 4 2 3 4
PREVIOUS EDITION WILL BE USED.
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Section IV ManagementConcept
a. ManagementAgency
The AFAPL is responsiblefor the managementof all contractual
and in-houseeffortsunder this task while SAMSO is responsiblefor
management of ProgramElement63401 (including682J - Advanced Space
Power Supply T_chnology)funds and the identificationof Spacecraft
power technologyneeds.
b. ParticipatingAgencies
I. Responsibilities
SAMSO will manage all P.E. 63401F funds, identifyuser needs
and coordinateon all Statementsof Work, AF Formlll, DD Form 1634,
TechnicalProgramPlans and Requestsfor D&F. The AFAPL will manage all
Project 682J contractsand in-houseefforts, supportSAMSO throughsub-
mission of appropriatedocumentationand participationin briefingsand
studiesand will provide the manpower for these activities.
2. A Memorandumof AgreementbetweenSAMSO, Deputy for Technology
and the AFAPL covers the work of Project682J. This MOA and Annex I were
signed in August 1975.
c. Execution
l. Execution of the FTPS programwill be throughan.AdvancedDevelop-
ment Contractawarded the successfulbidder on a multiple source proc-
curement. Specific tasks associatedwith this programare identified
by Phase in Section II above.
2. ProcurementApproach
All contemplatedprocurementswill be publicizedby synopsis
in the CommerceBusiness Daily utilizingthe R&D Source Sought procedure.
A Cost-Plus-Fixed-Feetype contract is presentlycontemplatedbased.upon
inabilityto obtain definitivespecificationsand lack of previouspricing
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information. Higher risk type contractswill be consideredat the time
of negotiationand will be utilizedif practicable,
3. Program Controls
The contract resultingfrom Task 682JI0 will requirethe
submittalof a Contract Funds Status Report (DD Form 1586), and R&D
TechnicalPlan and MonthlyProgramSchedule and R&D Status Reports.
SectionV Assessments
This is a proposednew Space Power Advanced Developmentprogram
for which a priorityassessmentremains to be made. It is proposedfor
the purpose of significantlyenhancingnon-nuclearpower systemscapa-
bility for future high energy military space vehiclesystems using the
Space Shuttle.
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POWERSYSTEM
AUTOMAT!ONREQUIREMENTS
FOREARTHORBIT
J. R.LANIER,JR0
O10-1
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i-,-,I ,
EPSAtJTOMATIONQUIZ
A SYSTEMIS , ",WHENITCAN,TOSOMEDEGREE,• SEQUENCETHROUGHA SERIESOFMEASUREMENTS
OFEQUIPMENTOUTPUTS,COMPARETHESEMEASUREMENTSAGAINSTSTANDARDS,ANDTAKECORRECTIVEACTIONIFTHEREISAN UNACCEPTABLEDEVIATIONBETWEENTHEMEASUREMENTANDTHESTANDARD,
"SUPPLYTHEPROPERWORD;"AUTOMATIC'"OR"AUTONOMOUS"AND"AUTOMATICALLY"OR"AUTONOMOUSLY"AS DESIRFD.
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EPSAUTOMATIONDEFINITIONS
AUTON£ATIC:(SELF-ACTING)HAVING,ASELF-ACTINGORSELFREGULATINGMECHANISM
AUTONOMOUS:(INDEPENDENT)CARRIEDONWITHOUTOUTSIDECONTROL;E×IST!NG!NDEPENDENTLY.
AUTOMATION: AUTOMATICALLYCONTROLLEDOPERATIONOFA sYSTEM.BYMECHANICALORELECTRONICDEVICESTHATTAKE.THEPLACEOFHUMANORGANSOFOBSERVATION,DECISION,ANDEFFORT.
(.Yl
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O0
EARTHORBITALPOWERSYSTEMAUTOMATIONREQUIREMENT
TOPROVIDECONTROLOFANEPS,WITHOUTEXTERNALINTERVENTION,
TOEFFECTSYSTEMOPERATIONEQUIVALENTTOTHATWHICHWOULDBE
PROVIDEDBYA TEAMOFEPSEXPERTSINCONTROLOFTHESYSTEM.
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EPS AUTOMATION
A SYSTEMHASBEENAUTOMATEDWHENIT CANINDEPENDENTLY
SEQUENCETHROUGHA SERIESOFMEASUREMENTSOFEQUIPMENTOUTPUTS,
COMPARETHESEMEASUREMENTSAGAINSTSTANDARDS,ANDTAKECORRECTIVE
ACTIONIF THEREIS ANUNACCEPTABLEDEVIATIONBETWEENTHEMEASUREMENT
ANDTHESTANDARD.
'..0
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O_0
EPSAUTOMATIONREQUIREMENTIMPLIES:
• INFORMATIONAVAILABLE- SENSORS.
• DATAREDUCTION-COMPUTER
• LOGIC-COMPUTER
• DECISIONMAKING- COMPUTER
• CONTROL-COMPUTERIRECEIVERS(SWlTCHF ETC.)
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-POWERMANAGEMENTSYSTEM.FUNCTIONS.
• DECODE/ISSUECOMMANDS"FROM SiCCOMPIITFR
eACQUIREIREDUCEEPSDATA
eTRA.NSMITSELECTEDDATATOTELEMETRY,SYSTEM
•TIMEISYNCHRONIZEPOWERSYSTEM.EVENTS
•CONTROLEPSOPERATION
• POWERGENERAT!ONMANAGEMENT,
•ENERGYSTORAGEMANAGEMENT
• blSTRIBUTIONSYSTEMMANAGEMENT
• LOADMANAGEMENT"
• INTERACTWlTHTHERMALSYSTEM
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O_
DRIVERSFOREARTHORBITALPOWERSYSTEMAUTOMATION
ODATAAVAILABILITY
0 GROUNDCOVERAGE
• DATALINKAVAILABILITY
0 TELEMETRYSHARING
ODECISIONTIME
• DATAREDUCTION
• HUMANRESPONSE
oCOST
• TEAMSOFEXPERTS
• DATANETWORKS
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SPACEPOWERSYSTEMAUTOMATIONWORKSHOP
AMPSPROGRAMSTATUSANDOBJECTIVES
ARTHURD. SCHOENFELD
MARSHALLSPACEFLIGHTCENTER
,_ HUNTSVILLE,ALABAMA
1981OCTOBER28
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AUTONOMOUSSPACECRAFTMANAGEMENTCONCEPT
(ASM)
• AUTONOMOUSMAINTENANCE- MAINTENANCEANDOPERATIONS
TASKSPERFORMEDONBOARDWITHOUTGROUNDINTERACTIVITY
• AUTONOMOUSFAULTDETECTION,ISOLATION,ANDREMOVAL-
SAFEGUARDHEALTHOFTHESPACECRAFT
• AUTONOMOUSRECONFIGURATIONORRECOVERY-FOLLOW
PROCEDURESFORREPLACINGFAILURESWITHREDUNDANTPARTS
ORSWITCHTOALTERNATEMODES
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ASMVERSUSPRESENTAPPROACHSUMMARY
ASM PRESENT
• HANDS-ONON-ORBITCHECKOUT • HANDS-ONON-ORBITCHECKOUT
• SELFPERFORMANCEMONITOR • PERFORMANCEMONITORVIA TELEMETRY
• SELFHEALTHMONITOR • HEALTHMONITORVIA TELEMETRY
• MOREDIRECTMEASUREMENTOFHEALTH • INDIRECTMEASUREMENTOFHEALTH
- ADDITIONALSENSORSINDIVIDUALLY - LIMITEDTELEMETRYLISTMONITORED
• DATAANALYZEDANDSWITCHINGCOM- • DATAREVIEWEDANDSWITCHINGMANDEDBYON-BOARDFAULTMONITOR COMMANDEDBYGROUNDCREW
• TRENDANALYSISPOSSIBLE • TRENDANALYSISPREDICTSFAILURES
e. HIERARCHYOFRESPONSEUPTOSAFEHAVEN • SAFEHAVENMODE.
C_
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O_
o_ HIERARCHICALSTATES
SYSTEM
MAINTAINCRITICAL FUNCTIONS
MAINTAIN QUALITYOF SERVICE
SAFETY ASSESSMENT
DETERMINESTATE OF HEALTH
GATHER DATA FOR PERFORMANCEPREDICTIONS
INTERDEPENDENTSUBSYSTEMMANAGEMENT
INDEPENDENTSUBSYSTEMMANAGEMENT
AUTONOMOUSOPERATIONAND MAINTENANCE
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CRITERIAFORASMACCEPTANCEANDAPPLICATION
• ESTABLISHNEED
, - ENHANCEDMANAGEMENTOFCOMPLEXSYSTEMS
- VULNERABILITYREDUCED
- LIFECYCLECOSTREDUCED
- CONVENIENCEINCREASED
• DEMONSTRATENEWTECHNOLOGIES
- SUBSYSTEMALGORITHMS
- SPACECRAFTMANAGEMENTSTRATEGIES
• PROVETHEDESiGNCONCEPT
- SHOWTHATRELIABILITYANDAVAILABILITYAREIMPROVED
- SIMULATEANDANALYZE
• QUANTIFYRISKSANDBENEFITS0'_
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co
PROGRAMHIGHLIGHTS
o ESTABLISHEDBASELINEDESIGNFORMODULAR250kWELECTRICALPOWERSYSTEM-MULTIPLEPOWERSOURCESANDLOADCENTERS
• DEVELOPEDMANAGEMENTCONCEPTFORUTILITYTYPEPOWERSYSTEM-FULLPOWERSOURCEUTILIZATIONANDADAPTIVECONTROLOFLOADBUSES
• DEFINEDPOWERSUBSYSTEMALGORITHMS
• DEVELOPEDPOWERMANAGEMENTSUBSYSTEMARCHITECTURE-POWERSUBSYSTEMPROCESSORS,ANDDISTRIBUTEDPOWERSOURCEANDLOADCENTER.PROCESSORS.
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PROGRAMHIGHLIGHTS(Continued)
• SELECTEDFLIGHTQUALIFIEDMICROPROCESSORSFORPOWERMANAGEMENTSUBSYSTEM
• DEFINEDDATABUSNETWORKANDDATACOMMUNICATIONSPROTOCOLS
• INITIATEDSOFTWAREDEVELOPMENTOFKEYPOWERSUBSYSTEMALGORITHMSUSINGHIGHLEVELLANGUAGE(FORTH)
• DEVELOPEDCONCEPTFORATESTBEDANDDEMONSTRATIONSYSTEMOFANAUTONOMOUSLYMANAGED250kWPOWERSYSTEM- INITIALFACILITYOF48kWEXPANDABLEIN 16kWINCREMENTS
O__.O
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MULTICHANNELREFERENCEELECTRICALPOWERSYSTEMDESIGN
CHANNEL 17
CHANNEL 1 , kSOLAR • v FUTURE
SOLAR ARRAY [ i _ SATELLITE
ARRAY SWITCH- EXPANSIONINGUNIT
POWERSOURCE ENERGYCONTROL STORAGE
.o,o !.o,o!CENTER "**1 CENTER
;.._ 10I I I I iI i I i 'I I I I I
-- -- SUBSYSTEM -- -JCONTROL
LCC= LOADCENTERCONTROL
GENERATION -- CASSEGRAIN CONCENTRATOR SOLAR ARRAYENERGY STORAGE - NICKEL-HYDROGEN BATTERY (160, 15(_AH CELLS)BATTERY CHARGER - SOLAR ARRAY SWITCHING UNITREGULATION --220 :J:20 VOLTS (BATTERY CHARACTERISTICS)POWER TRANSMISSION -- DIRECT CURRENT AT SOURCE VOLTAGEPOWER DISTRIBUTION -- DIRECT CURRENT AT SOURCE VOLTAGEPOWER PROCESSING - AS NEEDED WITHIN EACH PAYLOAD OR LOAD CENTERCHANNEL QUANTITY - DEFINED BY BATTERY CAPACITY (17)RELIABILITY -- FAIL OPERATIONAL, FAIL SAFE
GRACEFULCAPACITY DEGRADATION WITH FAILURESLIFE - INDEFINITE; REPLACE FAILED UNIT AT NEXT SERVICE OPPORTUNITY
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CENTRALPROCESSINGFUNCTIONSPOWERSUBSYSTEMRELATED
I,PAYLOADOPERATIONANDPIAINTENANCE
• INTER-SUBSYSTEMCONTROLS
• MONITORSTATEOFHEALTFIOFSUBSYSTEMPROCESSORS
• PAYLOADFAULTMANAGEMENT
• FAULTISOLATIONANDCONFIGURATIONMANAGEMEPITOFSDBSYSTEMPROCESSORS
• FAULTTOLERANTCENTRALPROCESSING
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-_ AUTONOMOUSMANAGEMENTISTHE HEARTOF UTILITYSPACECRAFTPOWER
TRANSMISSIONENERGY STORAGE DISTRIBUTION
REGULATION _ EXTENDEDLIFE /REDUCED FAULT
SOLAR _ REDUNDANCY_ REDUCED /F_ ........ _ [ARRAY II _7l COMPLEMENT • \COSTS / ...... m..," PAYLOAD L_WL_|.... . _ i \ / ADAPTABILITY " l::3" JswrrcH_ p .,,_1 \ / REDUNDANCY -,,,,uNrr II (B4J' I MICROPROCESSOR \ ............ ._ _ [
II _ I _ CONTROLLED __ _I::NIIAN(;IJ:;MENT l'"a !!! _ I DIGITAL _ _ POWER .
_! _ ELECTI__er Mana e sy_UlTY _,
g mentSub
POWERGENERATION I F__ I ...no-- -- FULL ..v,-_u,aI III I II I III rr_-_ I AVAILABILITYSOLARARRAY UTILIZATION \ IIIIII I III I III III FF--F_r-_F_] / FLEXIBILITY
.., -------\I_l MOTORSB ! II Jl I
i PREPLANNED /g"__.._ CONTROLLERS _ _ _l_RESUPPLY PROJECTIONS "_DECISIONS /"
• / REDUCED SUPPORT LIGHTING OVENS
" ..... ".P--Z........ w ...." AUTONOMOUSMANAGEMENTDESIGN : GROUND SUPPORT
ENGINEERING ADAPTABILITYDEPENDABILITY
FUll UTUZATION REDUCEDCOSTSEXTENDEDLIFE
REDUCEDREDUNDANCY
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BENEFITSFROMAMPS
•REDUCES.REDUNDANCYREQUIREMENTSICOSTS
- ACCOMMODATESWIDESPREADDEGRADATIONIFAILURESTHROUGHFLEXIBLELOADMANAGEMENTTECHNIQUES
• REDUCESDEVELOPMENTCOSTTHROUGHMANAGEMENTOFCOMPLEXMODULARIZEDSYSTEMSUSINGLOWERPOWERMODULESANDNEARTERMTECHNOLOGY
•REDUCESRESUPPLYCOSTSBY:
- OPERATINGEQUIPMENTTOEXTENDLIFE- EARLYDEGRADATIONDETECTIONANDCORRECTIVEACTION- RESUPPLYPROJECTIONS- MISSIONADAPTABILITY
• REDUCESGROUNDSTATIONOPERATIONALCOSTS
- REDUCESCOMMUNICATIONTRAFFICREQUIREMENTS- MINIMIZESGROUNDFACILITIESFORINCREASING
SATELLITEQUANTITY/COMPLEXITY- FEWERPERSONNEL- CONTINUINGSUPPORTCOSTSREDUCED
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p..a
BENEFITSFROMAMPS
• IMPROVESDEPENDABILITYANDPERFORMANCETHROUGHUSEOFEXTENSIVEDIAGNOSTICDATA
• .DECREASESASTRONAUTMONITORINGREQUIREMENTS
• OPERATESUTILITYTYPEPOWERSYSTEMFORA WIDEVARIETYOFPAYLOADMISSIONSANDLOADS
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AUTONOMOUSPOWERMANAGEMENTAPPLICATIONS
• SPACEPLATFORMS
• MILITARYSPACECRAFT
• MANNEDSPACESTATION
• ELECTRICPROPULSIONSPACECRAFT
.,.,j
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CONCLUSIONS
• A UTILITYTYPEPOWERSYSTEMCONCEPTHASBEENDEVELOPEDTHATALLOWSLARGESYSTEMPOWERTOBEATTAINED_IITHNEARTERMTECHNOLOGY
• MODULARAPPROACHREDUCESDEVELOPMENTANDRESUPPLYCOSTSANDENABLESINCREMENTALASSEFBLY/EXPANSIONOFLARGEPOWERSTATIONS
• UTILITYTYPEPO_ERSYSTEMVERSATILITYREQUIRESA NEWAPPROACHTOPOWERMANAGEMENTINSPACE
o AMPSPROVIDESA COSTEFFECTIVEAPPROACHTOTHEREQUIREDPOWERMANAGEMENTBY:
- MINIMIZINGGROUNDSTATIONSUPPORT- IMPROVINGEQUIPMENTLIFE- REDUCINGRESUPPLYCOST- ACCOMMODATINGWIDEVARIETYOFPAYLOADMISSIONSANDLOADS- RECOVERYFROMEQUIPMENTDEGRADATIONANDFAILURE
• AMPSPOWERMANAGEMENTSTRATEGIESAREA KEYTECHNOLOGYDEVELOPMENTFORLARGEPOWERSYSTEMSANDMILITARYSPACECRAFT
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"STRAWMAN"
TECHNOLOGYI SSUILS
AND
SPECIFICOBJECTIVES
'',4"",4
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"-4oo
TECHNOLOGY ISSUES
o DISTRIBUTED VERSUS CENTRAL CONTROL
o ALGORITHM MODELING
o CONTROL REQUIREMENTS
o CONTROL PHILOSOPHY
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TECHNOLOGY ISSUES
• DISTRIBUTED VERSUS CENTRAL CONTROL
CENTRAL HYBRID DISTRIBUTED
I i
J ICONTROLLERS i
,NST i ,I I
I ' I_' I
I , I
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co
TECHNOLOGY ISSUES
• ALGORITHM MODELING
ACCURATE MODELING/CHARACTERIZATION OF COMPONENTS
BETTER UNDEH_rANDING OF COMPONENT CHARACTERISTICS AND THEEFFECTS OF VARYING PARAMETERS ON THE COMPONENT RELIABILITY,EFFICIENCY, AND LIFE MAY BE NEEDED TO PROPERLY DESCRIBE THECOMPONENTS EFFECTON POWER SYSTEM PERFORMANCE.
PHILOSOPHY OF REDUNDANCY INTERNAL TO THE ALGORITHM
DUE TO THE FRAGILE NATURE OF SOFTWARE AND THE POTENTIALCONSEQUENCESOF ERROR, A REDUNDANCY PHILOSOPHY MAY BEREQUIRED OTHER THAN THAT INVOLVED AT THE SYSTEM LEVEL.
STANDARDIZATION VS. OPTIMIZATION
IT IS IMPORTANT TO RECOGNIZE THE OVERALL SYSTEM ECONOMY INTERMS OF SUFFICING VERSUS OPTIMIZING PHILOSOPHY - - -A FAMILY OF "STANDARD" ALGOBITHMS MAY BEADEQUATE BUT SHOULDBE COMPARED WITH THE POSSIBILITY OF UNIQUE (OPTIMUM) ALGORITHMSFOR EACH NEED.
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TECHNOLOGY ISSUES
• CONTROL REQUIREMENTS
DEPTH OF MONITORING (PENETRATION)
DEPENDING ON SYSTEM REDUNDANCY!RECOVERY PHILOSOPHY, THEDEPTH OF MONITORING MAY VARY FROM SUBSYSTEM LEVEL DOWN TOCOMPONENT LEVEL. (BATTERY TO CELL)
DATA SAMPLING RATE
SINCE THE LEVEL OF COMPLEXITY AND CONTROL IS DIRECTLY DEPENDENTON THE DATA SAMPLE RATES, VARYING SAMPLE<:RATESMAY BE DESIRABLEFOR OPTIMUM SYSTEM MANAGEMENT.
i-.t
coi..-.t
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cor.o
TECHNOLOGY ISSOES
• CONTROL PHILOSOPHY
POWERDOwr_ VS. LIGHT LOAD OPERATION
IT MAY BE DESIRABLETO POWERDOWNPORTIONS OF A SYSTEM FOR LONGPERIODS OF "STANDBY" OPERATIONS AS OPPOSEDTO OPERATION OF THETOTAL SYSTEM AT A FRACTION OF ITS RATING.
LOAD SHEDDIN_ (PRIORITIZATION)
FOR CERTAIN SITUATIONS IT MAYBE DESIRABLE TO PRIORITIZE LOADS(OR LOAD BUSES)AND ENABLE BUSESACCORDING TO SYSTEM CAPACITY.
SELF-DIAGNOSIS AND OVERRIDE
CERTAIN SELF-DIAGNOSTICS WILL UNDOUBTEDLY BE REQUIRED; THECONSEQUENCEOF THIS DIAGNOSIS AND THE ABILITY TO OVERRtDIEAND/OR REPROGRAMAN AUTOMATED SYSTEM MAY NEED TO BE TRADEDOFF AGAINST THE DEGREE OF SOPHISITICATION NECESSARY FOR "'TOTAL"AUTONOMY.
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SPECIFIC OBJECTIVES
DISTRIBUTED VERSUS CENTRAL CONTROL
• IDENTIFY OPTIMUM APPROACH FOR VARIOUS CLASSESOF USE
(PLANETARY, EARTH ORBITAL, LARGE VS. SMALL, MILITARY)
• IDENTIFY COST VS. BENEFIT OF OPTIMUM APPROACH VS. STANDARD
• ESTABLISH LEVELS OF AUTHORITY REQUIRED IN EACH
cobo
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co
SPECIFIC OBJECTIVES
ALGORITHM MODELING
• GENERATE ALGORITHMS
• CREATE STANDARD SET OF ALGORITHMS
• ESTABLISH COST/BENEFIT FOR USEOF STANDARD VS. OPTIMUM
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SPECIFIC OBJECTIVES
ALGORITHM MODELING
IDENTI FlED ALGORITHMS
• BATTERY CHARGE CONTROL • SWITCH/LOAD BUS MONITORING
• BATTERY STATE--OF--HEALTH • FAULT DEFINITION
• RECONDITIONING • ENERGY PLANNING/ALLOCATION
• TREND PROJECTION • SOLAR ARRAY POWER REALLOCATION
• SOLAR ARRAY STATUS • LOAD BUS ASSIGNMENTS
• COMMAND PROCESSING • POWER SUBSYSTEMS STATE-OF-HEALTH
C'l RCUlT BREAKER PROGRAMMING • REPLACEMENT SCHEDULI,_]G
• CONTROLLER ANOMALIES
ALGORITHM TYPES
• EFFECTS ACTION
• GATHERS DATA
,_-.=03L_3
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p...=
coO_
SPECIFIC OBJECTIVES
CONTROL REQUIREMENTS
• ESTABLISH RATES REQUIRED FOR OPTIMUM MANAGEMEN1• GENERATION• STORAGE
• DISTRIBU'_ION
• DETERMINE SENSITIVITY OF CHANGE IN SAMPLE RATE TO SYSTEM PERFORMANCE,RELIABILITY, AND COST
• ESTABLISH LIMITS OF DATA ALGORITHMS DETERMINATION FOR ACTION AND CONSEQUENCES.OFVARIATIONS IN THOSE LIMITS
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SPECIFIC OBJECTIVES
CONTROL PHILOSOPHY
• DETERMINE COST EFFECTIVE LEVELS OF REDUNDANCY (SYSTEMPAD)
• ESTABLISH LEVELS OF SYSTEM DEGRADATION WHERE.SPACECRAFTHIERARCHY DECIDE
WHETHER TO CQNTINUE IN DEGRADED MODE FOR MAX'IMUM LIFE OR TO OPERATE IN ANEARLY WEAROUT MODE TO ATTAIN HIGHER LEVELS OF PERFORMANCE
• ESTABLISH MODES OF POWERDOWN OPERATION COMMANDED BY THE SPACECRAFT
HIERARCHY DUE TO POINTING CONDITIONS, THERMAL CONDITIONS, OR OTHER SPACECRAFTCONSTRAINTS.
i.-=CO,..4
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SPACE POWER SYSTEM AUTOMATION WORKSHOP
MARSHALL SPACE FLIGHT CENTER
OCTOBER 28 & 29, 1981
REPORT OF WORKSHOP GROUP NUMBER i
by
Sidney W. Silverman (Workshop Chairman)
Matt Immamura
Bill Brannian
Dave Peterson
Bob Giudici
Roy Lanier
John Armantrout
Doug Turner
THE QUESTION ADDRESSED
WAS
WHAT ARE THE TECHNOLOGY ISSUES INVOLVED IN
THE AUTOMATION OF A SPACE POWER SYSTEM?
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BACKGROtmD sw, ,
The most iignifioan% factor in deriving the technology issues
is %o define what the word "issues" encoml_sses. A composite of
the group'sdiscussionis the following.
Techmologyissuesare technicalproblems/questionsthatmustbe
resolvedpriorto implementationin a spacecraftor missionin
orderto minimizeriskcriteria.The issuemustmeeta defined
ob_ctive.
In orderto be consideredan issue,at leastone of thefollow-
ing must be true,
•Ithaslittleor no historyof use.
-It requireslonger%ban'normal'projecttimeallowedfordevelopment.
•It has unacceptablerisk (technical,cost,schedule)
andvalue,comparedto alternatives.
In addition--a meaningfulRFP can be writtenforthe issue.
CONCLUSIONS/RECOMMENDATIONS,In orderof technicalcriticalitythe technicalissuesares
I. To implementthe automationand autonomousoperation
_f the electrical power system, the primar_ item is the control
aspect, which implies the software and the verification of the
sensing and corrective action• This includes sensors to detect
the selected parameters, algorithms for the component reaction_
and the subsystem operation and interaction with other components
and subsystems, and effectors to cover the required ranges of
values ( for 50-500KW spacecraft power systems). The control
technique must assure that the automation of the electrical
power system is fault-%olerawt and can operate in programmed
modes A_gardless of the degraded conditions encountered. Control
concepts thus are the governing factors in effective automation
and autonomous operation of the electrical power system.
2, Once the control concept has been selected and the design
initiated, the next important item is the availability of @pe_-
Qualified components forh_h Dower applications. Included will
be thosecomponentswhichare availablewitha pastuse history,
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those which are logical candidates but have not been qualified,
those which will have to be modified from existing designs, and
those which are unavailable for various reasons. The latter will
result in extensive R&D programs to conceive, fabricate, develop,
and test the component within %ha allotted, seh_hle. Oempenents
will have to be suitable for application to a controlled, auton-
omous, operational electrical power system.
3. As the power levels are increased to the multihundred kilo-
watt range, higher operating and dlstributln_ voltages become nec-
essary in order to decrease system amperes, losses, and the size of
the cOm_ements and the distribution system, Limitations may be
imposed b_availability of qualified components. The voltage
selection will have to be made at the electrical system level
because of the interfaces with the other systems and the require-
aent8 for pr_tecttOn and 8a_.ety _, At hAgher l_Wmr_ lewelS .and_ high-,
er voltages or currents, interactions with the environment become
severe and s_gnificant. Special concepts must be formulated so
that the electrical power system can operate.
GENERAL,
A definition of technology readiness can be described in
followlng program schedule chart. At the time of technology read-
inessp all development work will have been completed and only
design engineering will remain to be done.Technology Technology Ready Launch
Ready _ _ For _ _gram
P_a@ea
R_, Early Develop- A&Bmerit _ _- " _wI-4 Years " 9-12- _3-5 Years
MOs.
LOW .... _ _
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SPACE POWER SYSTEM AUTOMATION WORKSHOP
MARSHALL SPACE FLIGHT CENTER
OCTOBER 28 & 29, 1981
REPORT OF WORKSHOP GROUP NUMBER 2
by
NAME ORGANIZATION
Floyd E. Ford (Chairman) NASA/GSFCFrederick C. Vote JPL
John W.°Lear Martin/Marietta
Charles Sollo TRW
Joe Navarro McDonnell-Douglas_- CA
Mike Glass Lockheed
Wayne Hudson NASA HeadquartersDon Routh NASA/MSFC
Don Williams NASA/MSFC
THE QUESTION ADDRESSED
WAS
WHAT ARE THE TECHNOLOGY ISSUES INVOLVED IN
THE AUTOMATION OF A SPACE POWER SYSTEM?
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Background:
The group 2 session on Technology Issues (TI) for Automated Power Systemswas initiated by addressing the following questions:
• Is the automation of power systems needed or required for future
space missions requiring large (greater than 25KW) power systems?
• Is it conceivable to think in terms of an autonomous power system,
supporting mission objectives for extended periods (several days to weeks)without human intervention or monitoring?
After considerable discussions on suchtopics as trends in power levels,
complexity of large systems, user requirements for quality power, overallsystem cost, etc., the group achieved the following consensus:
a. Automation is required for large power systems.
b. An autonomous power system is conceivable.
The group could not agree on the level (or degree) of automation without
a cost benefit analysis to illustrate the various trade-offs. There was
general agreement that a fully automated power system would most likely
be achieved through evolution with incremental growth from today's systemsto those needed in the i990's. However, the technology for automation is
believed to be one that enables large power systems, not merely to enhancethem. There seems to be no question that the large systems of the future
will require a much higher degree of automation than that existing inpresent power systems.
Some other important considerations supporting automation technologyforpower systems are as follows:
• Large power systems will be extremely complex in terms of on-orblt
configuration management, amount of housekeeping data, and overall energymanagement.
• Power and load management will require on-board intelligence toefficiently and effectively use the system's energy
• Speed of detection and correction of failures/faults will becritical for large systems.
• The need for longer periods of spacecraft autonomy is a driverfor automation.
The group expressed a need for a trade-off study to establish the
benefits of automation versus the degree of automation that may beachieved in a power system. To place this question in perspective, one
example is given. Should a power system be completely self-correcting orshould it depend on ground intervention. For instance, if a failure is
detected in one of several of the power buses, is it acceptable to theusers to power down and wait for ground intervention or is there sufficient
cost justification to automate the diagnostic functions necessary to makedecisions required to reconfigure the loads to another bus.
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Conclusions/Recommendations:
The group 2 session defined five technology issues. They are as follows:
I. Establish a reference power system design from which to base the
requirements for automation.
Comment
The reference system should serve as a baseline for trade-off studies,
total subsystem analysis, and mission analysis. The reference designshould consider the environment and user community for low earth orbit,
geosynchronous, and planetary type missions. The needs of the various
type payloads (high power pulse loads, long duty cycle loads, etc.)should be a strong consideration in arriving at a reference design.
2. Develop and document the architecture/methodology to be pursuedin the automation of large power systems.
Comment
The group recognized that any power system consists of a multiplicity ofbasic components such as batteries, solar arraysandelectronics. However
the philosophy used in assembling these components into a _ystem will
strongly influence the approach to automation. Such issues as centralvs. distributed control, type of sensor information needed, processor
characteristics and storage capability, distribution of intelligencewithin the system (central computer vs. local microprocessors), degree of
modularization of power units, and the overall system philosophy should
be thoroughly investigated prior to initiating any hardware development.
The early decisions made on these issues will impact development cost
throughout the program. The minimum level of automation consistent witha reliable and cost effective power system should be the "first cut"
design.
3. Strongly emphasize "system engineering" in the power systemautomation effort.
Comment
The successful outcome of an automated power system technology program
will, to a large extent, depend on the amount of system engineering that
goes into the decision making process. It must be recognized that the
power system is only one of the several subsystems that will make up a
spacecraft, vehicle or space platform. _rade-offs and/or decisions made
by the power system designer can significantly influence design philosophy
and/or cost of other subsystems such as mechanical, thermal, data handling,
attitude control, communication, etc.
4. Develop models of power systems and system components required
to generate the algorithms that accurately represent the characteristicsof the individual system components.
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Comment
The process of automation requires algorithms that accurately represent
the characteristics of the individual system components. This requires
that components such as batteries, solar arrays, electronic switches,
etc., be defined in analytical terms from models that have a high degree
of validity and accuracy. Both dc and ac models should be developed.
Performance validation of large power systems will depend primarily on
synthesizing the system using computer simulations. This is contrasted
with past practices where "all up" ground system tests were conducted to
demonstrate systemperformance prior to launch.
5. Identify and initiate development of components required for theautomation of power systems.
Comments
It was generally agreed that the basic piece parts (battery cells, solar
cells, transistors, etc.) for a power system currently exist. However, anumber of components required for the automation process either do not
exist, or are inadequate, Those specifically discussed included high
power overload switches (space qualified), actuators with digital
interface, electronic switchgear (non-mechanical) and accurate current
sensors with large dynamic range.
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General:
The overall view of the group, as perceived by the chairman, was that
large space power systems will require levels of automation much greater
than those being implemented in present designs. The architecture of the
large power system, the philosophy of design, the methodology of hardwareimplementation, and the launch and operational scenarios are presently
nonexistent. These are interdependent quantities and are usually studied
and defined as part of a project conceptual design phase. Consequently,it is understandable that most of the issues addressed during the workshop
dealt with system engineering rather than technology. Of the five recommen-
dations presented by group 2, only numbers 4 and 5 relate to technology.
What is implied by this, is that a technology program for the automation
of power systems must emphasize systems engineering first. From the
systems engineering a number of technology issues will emerge.
During the workshop discussions, it became apparent that there are two
prevailing "schools of thought" on large power systems in space. Theyare as follows:
. Develop power system modules (i.e., 25KW) and use these mooules
as building blocks in space for growth to a I00 to 250KW capability over
some period.
• Develop a "unit" power system of the size that is needed (i.e.,i00 or 200KW) and place this unit in orbit.
The second approach has been referred to as a "mini-utility" system. The
point of raising this issue is not to promote one concept over the other,
but rather to illustrate the divergence of technical opinions, even on
the basic scenario'for achieving large power capabilities in space.
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SPACE POWER SYSTEM AUTOMATION WORKSHOP
MARSHALL SPACE FLIGHT CENTER
OCTOBER 28 & 29, 1981
REPORT OF WORKSHOP GROUP NUMBER 3
by
Howard Weiner (Workshop Chairman)
Robert Corbett
Kent Decker
Joe Voss
Lu Slifer
Chris Carl
George Von Tiesenhausen
Lt. Ed Gjermundsen
THE QUESTION ADDRESSED
WAS
WHAT ARE THE SPECIFIC OBJECTIVES INVOLVED IN
THE AUTOMATION OF A SPACE POWER SYSTEM?
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BACKGROUND
Workshop Group No. 3 was assigned the task of establishingspecific objectives involved in the automation of a space powersubsystem. Considerable attention was also given to the "strawman"set of objectives developed by NASA-MSFC personnel. As a resultof these discussions a set of recommendations, presented below,were derived. These recommendations do not necessarily representall of the objectives required for automation. However, they dorepresent a well-conisdered set of initial specific objectives.
RECOMMENDATIONS
This section contains a set of recommendations arranged inorder of decreasing priority _.e. Recommendation No. I has highestpriority). Each recommendation is also a brief description of theaction needed to accomplish a specific objective.
Priority ranking was based on a temporal ranking. Thus, thespecific objective of Recommendation No. 2 needed substantialcompletion before specific objectives of subsequent recommendationscould be meaningfully attained.
RECOMMENDATION NO. i
Identify All Potential!y Useful Autonomy Functions
An Autonomy Function is defined herein as a specificcapability, designed into a spacecraft which permits the spacecraftto execute a specific on-board task (with decision making) withoutintervention or control from the ground.
A number of autonomy functions have been identified, whichare useful for power subsystem autonomy, including:
i) Battery Charge Control2) Battery State-of-Health
- Reconditioning- Trend Projection
3) Solar Array Status4) Command Processing (Circuit Breaker Programming)5) Switch/Load Bus Monitoring (Fault Definition)6) Energy Planning/Allocation (Solar Array Power
Relocation)7) Load Bus Assignments8) Power Subsystems State-of-Health
- Replacement Schedules- Controller Anomalies
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While these functions may appear to be sufficient, therecan be more subtle considerations, based on a more global viewpointthan that of a power subsy_t_--ededededededededede_l_gner,which require additionalautonomy functions be utilized for the larger more complex space-craft. A proper understanding of these considerations can beattained by the use of a team of experts from the following space-craft technologies:
i) Artificial Intelligence2) Spacecraft Systems3) Power Subsystems4) Computer Design/Programming
Thest teams should be capable of identifying, categorizingand prioritizing all potentially useful autonomy functions. As anexample, it may be useful to utilize the following categories asautonomy function discriminators.
i) Level of Control Authority- System- Subsystem- Local
2). ResponseTimeRequirement- Fast ( i0-6Sec)- Moderate (_i0-3Sec)- Slow (_i Sec)
3) Mission Impact- Critical- Non-Critical
By means of these categories, etc, the optimum methods of implementingan autonomy function can be more easily attained.
RECOMMENDATION NO. 2
Establish Desisn and Reliability Directives for the PowerSubsystem
Another key task for the team of experts is the establish-ment of Design and Reliability Directives for the Power Subsystem.This task should be at as high a priority level as the first taskof identifying all potentially useful autonomy functions.
The team should carefully review all mission and operationsrequirements in order to determine the appropriate levels of per-formance, reliability and autonomy for the power subsystem. Directivesshould then be issued for controlling design. As an example:
"Failure of an autonomy function shall not cause anydegradation of power subsystem performance or lifetime"
Directives, such as the above, can then be used to determinelevels of redundancy in autonomy function and power subsystem equip-ment as well as the type of redundancy (block, functional, standby,etc).
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These directives will also serve as the basis fordetermining optimum monitoring approach, data sample rates andother elements of the autonomy functions.
RECOMMENDATION NO. 3
Generate Algorithms for Each Autongmy Function
An Algorithm is defined herein as a series of logicalsteps needed to perform an Autonpmy Function.
In order to determine the optimum level of autonomy fora given power subsystem, the penalties vs benefits of variousapplicable autonomy function must be evaluated. Assessment ofthese require that an algorithm, for each function, be generatedand that various methods of implementing that algorithm hardware,software, memory, data rate, sensors, data conversion, etc beevaluated. Hence, prior to the selection of any autonomy functions,for a given application, it is desirable that algorithms be generatedfor all potentially useful autonomy functions.
It should be noted that development of standard algorithmsmay be useful in terms of generating penalty information during thepreliminary design process. However, algorithms and methods ofimplementing these algorithms should be optimized by the time thecritical design review process occurs.
RECOMMENDATION NO. 4
Develop a More Rigorous Definition of Potential ComputerArransements
As development of spacecraft autonomy proceeds, it willbecome necessary to develop more rigorous definitions of proposedcomputer arrangements. The present scheme of "Distributed", "Hybrid"or "Central Control" arrangements can lead to confusion duringevaluation and trade-off processes. A proposed approach (whichshould be modified as more complex arrangements are developed) isshown in Figure I. The approach is simply to indicate the numbersof computers at successively lower levels of command and controlheirarchy. The arrangements shown in Figure i are based on thefollowing heirarchy:
i) Spacecraft System Level2) Subsystem Level3) Local Level
Additional definitions of arrangements should be developedwhen computers are used on a ring (or circular) type of data bus.
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RECOMMENDATION NO. 5
identify Optimum Computer Arrangements Based on the Sizeof the Size of the Spacecraft
The "size" of a spacecraft, in terms pertinent to powersystem autonomy, may be the physical size of the spacecraft or thepower subsystem, thepower requirements of the spacecraft, the degreeof "complexity" of the power subsystem or the rate of command, controland monitoring data - or any combination of the above. Essentially,the "larger" the spacecraft, the more likely a "distributed" computerarrangement will be required. As an example, if the data raterequired for power subsystem autonomy is of the order of _i00 KHZ,the use of the spacecraft central computer alone may be sufficient.On the other hand, a data rate of 10MHZ will require distributionof autonomy tasks between a spacecraft central computer (_3MHZ presentlyavailable), a power subsystem computer (_3MHZ) and numerous of locallevel processors (100KHZ - 800 KHZ).
Other considerations such as a planetary vs earth orbitalspacecraft, a military vs civil spacecraft or levels of authorityfor each processor are relatively minor with regard to their impacton computer arrangements.
A standard computer arrangement for all spacecraft "sizes"is not indicated. Nor is it even indicated for all classes of space-craft for a given "size". In the final analyses, an optimum computerarrangement will be used in the final design of autonomy for anypower subsystem, even though a majority of the developed "standard"autonomous functions will findmultiple application.
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SPACE POWER SYSTEM AUTOMATION WORKSHOP
MARSHALL SPACE FLIGHT CENTER
OCTOBER 28 & 29, 1981
REPORT OF WORKSHOP GROUP NUMBER 4
by
Wayne Wagnon (Workshop Chairman)
Ron Larson
Fred Lukens
Art Schoenfeld
Ron Given
Irving Stein
C. S._Crowell
Dave Massie
Dick Gualdoni
THE QUESTION ADDRESSED
WAS
WHAT ARE THE SPECIFIC OBJECTIVES INVOLVED IN
THE AUTOMATION OF A SPACE POWER SYSTEM?
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SPACE POWER SYSTEMAUTOMATION WORKSHOP
INPUT FROMGROUP 4
This document summarizes the inputs by the individual memberscomprising Group 4 on Automation Objectives.
Background:
With the current emphasis being placed on space platform systems,it becomes necessary to investigate new ways to make thesesystems affordable. That is, affordable in terms of reducing thelife cycle costs, extend the operational life, and improve theperformance of the systems involved. To this end, automation andautonomous systems technologies are expected to make significantand important contributions to the development and operation of thesemissions.
In the case of the on-board electrical power system, a program mustbe defined and implemented that is affordable and will ensure, inthe event of a failure, that the system degrades gracefully whileproviding for some minimum set of useful services. Therefore, themost basic of al_ objectives is to d_fine an electrical power systemautomation plan that will achieve the greatest early-on benefits(such as timely reconfiguration and reconstitution of itself) withoutadding to the complexity of a fully autonomous system.
Concl_sions:
Much has been accomplished in providing new automation tools tothe hardware designer that improves the performance of today'sflight equipment. Microprocessors are being used to program andcontrol system level functions with excellent results. In the cas_of space power systems, many of the technology issues involving dis-tributed versus central control, algorithm modeling, control require-ments/philosophy, voltage type/level, partitioning between spacecraftand ground and between hardware and man, etc. can be resolved throughthe application of automation techniques. To be successful, automa-tion must be implemented as an integral part of the system designto ensure that the power demands of the users are met withthegreatest reliability, flexibility and efficiency.
Recommendations:
The objectives and actions taken to evaluate and implement an agreedupon level and/or philosophy of automation for a space power subsystem
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must be focused so as to provide a utility type of operation.It must also reduce the ground and on-board operational burden,accommodate near-term hardware technology limitations and reducethe development, operations, and resupply costs of the system.Based upon this premise, the following recommendations are made:
i. Classify and characterize the power subsystem require-ments. This includes the function, quality, type, voltage level,quantity, constraints, load profiles, etc. In addition, thisaction should consider all potential power utilization equipmentsas well as the mission phases (i.e., pre-launch, launch, orbitaloperations, on-orbit service/maintenance/resupply, etc.).
2. Develop a comprehensive list of all potential functionsand/or activities that could impact the power subsystem and pre-vent it from performing an effective utility type of operation.This would include such parameters as operational environments,single point failures, insufficient redundancy, %Lnqualified partsand components, human error, over-stressed conditions, poor designconcepts, inadequate protection, inaccurate sensors, etc.
3. Generate a candidate list of automation activities thatwould eliminate and/or minimize all the identified impacts andwould provide both a short term and long term benefit to the powersubsystem if implemented. Items to 5e considered would includeredundancy, component derating, fault management, shifting of burdenfrom man to machines, application of algorithms for managementstrategies, partitioning of functions between space platform andground and between man and machines, application of hiearchy controlfunctions, level of monitoring, etc.
4. Conduct an indepth trade-off study to evaluate and analyzethose candidate automation activities selected as having themaximum pay-off or benefits for the space power system. Questionsto be addressed would include the type sensors to be used, level ofredundancy to employ, derating factors, central vs distributedcontrol, control strategies, sampling rates, fault detectionmethodologies, response times, operational limits_ diagnosis routines,etc.
5. Develop a balanced partitioning of the automation and controlfunctions between the ground, the space platform and the power sub-system. The partioning should be based on such factors as selectedcontrol sensors, sensor control circuitry, integration methodology,applicable control algorithms, display requirements, redline para-meters, telemetry links, communication bandwidths, data pre-processing,etc.
6. Develop a fault detection, isolation, diagnosis, and pro-tection plan. The plan should consider such parameters as interfacerequirements, equipment reconfiguration and recovery requirements,
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"safing" for on-orbit servicing,supervisorycontrols for loadswitching,system protection for out-of-toleranceconditions,load limiters,reconditioning,trend analysis, etc.
7. Develop algorithms,as appropriate, for the followingfunctions:
a) Battery management strategies
b) Bus power allocations
c) Power distributionmanagement
d) Power processingmanagement
e) Thermal management
f) Battery reconditioning
g) Monitoring health status
h) Trend analysis
i) Fault recovery/reconfiguration
j) Platform processor interfacing
k) Platform display and man interfacing
I) Ground support interfacing
m) Sensing/controlparameters
n) Test and validation
These algorithms are intended to enhance and to enable the imple-mentation of selected automation activitiesto improve performance,reduce costs, and to extend the useful life of the space power sub-system.
8. Develop a technologyreadiness demonstration program tovalidate and assess the automation functions and methodologyemployed. In addition to exercisingand validating the specificautomationefforts incorporatedinto the design and those imposedon the power subsystem,the demonstrationwill include a completedynamic performanceand stabilitycharacteristicsof the system.Individualparameters such as the followingare to be included:
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a) Load switching
b) Reconfiguration
c) Fault recovery
d) Fault isolation
e) Power regulation
f) Power processing
g) Sensor response
h) Circuit protection
i) Other
9. Define, develop and verify the needed automation tech-nology for items such as the following:
a) Sensors
b) Sensor circuits
c) Solid state circuit breakers
d) Fault isolation switches
e) Load limiters
f) Data processors
The above nine areas of activity are in priority in that they arelisted in the normal sequence of events to accomplish the broadautomationobjectives previously stated. A carefully planned andcoordinated implementationautomationplan will have significantbenefits making a space platform system affordable.
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SPACE POWER SYSTEM
AUTOMATION WORKSHOP
AT THE
MARSHALL SPACE FLIGHT CENTER
OCTOBER 27-29, 1981
ATTENDEES
NAME ADDRESS
Jim Miller Marshall Space Flight Center(205-453-4950) ECII
Marshall Space Flight Center, AL35812
Dick Carlisle RSS-5(202-755-2403) National Aeronautics & Space Administration
600 Independence Blvd.Washington, D.C. 20546
Chris Carl Jet Propulsion Lab(792-2018 FTS) 233-307
4800 Oak Grove Dr.Pasadena, CA 91030
Sidney W. Silverman Boeing Aerospace Co.(206-773-2457) (Prefer home address for mailing)
19630 Marine View Drive, S.W.Seattle, Wash. 98166
Joseph M. Voss Boeing Aerospace Co.(206-773-1198) Org. 2-3743, M/S 8C-62
P.O.B. 3999Seattle, WA 98124
Frederick C. Vote Jet Propulsion Lab(213-354-4182) Mail Stop 198-220
4800 Oak Grove DrivePasadena, CA 91109
Fred Lukens Martin Marietta(303-798-8752) Mail Stop S0550
P.O.Box 179Denver, CO 80201
Robert E. Corbett Lockheed Missiles & Space Co.(408-742-3305_ D/62~16 B/151
P.O. Box 504Sunnyvale, CA 94086
Floyd E. Ford NASA/Goddard Space Flight Center(301-344-5845) Code 711
Breenbelt, MD 21077
Lu Slifer NASA/Goddard Space Flight Center(301-344-5845) Code 711
Greenbelt, MD 21077
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ATTENDEES
NAME ADDRESS
Howard Weiner The Aerospace Corp.(213-648-6273) Mail Station: D8-II02
P. O. Box 92957Los Angeles, CA 90009
Wayne Wagnon Marshall Space Flight Center(205-453-4623) Code EC31
Marshall Space Flight Center, AL 35812
George von Tiesenhausen Marshall Space Flight Center(2054.453-2789) PS01
Marshall Space Flight Center, AL 35812
Charles Sollo TRW, M2-2120(213-535-1712) One Space Park
Redondo Beach, CA 90278
Arthur D. Schoenfeld TRW, M2-2020(213-536-1972) One Space Park
Redondo Be_ch, CA 90278
William R. Brannian TRW/STG, M2/2020(213-536-1971) One Space Park
Redondo Beach, CA 90278
Jerome P. Mullin National Aeronautics and Space Administration(202-755-3278) RTS-6
600 Independence Blvd.Washington, D.C. 20546
Jim Graves Marshall Space Flight Center(205-453-2514) ECI2
Marshall Space Flight Center, AL 35812
Kent Decker TRW(213-536-2960) M2-2384
One Space ParkRedondo Beach, CA 90278
Douglas Turner get Propulsion Lab.(213-354-2346) 4800 Oak Grove Dr.
Pasadena, CA 91030
Joe Navarra Mcdonnell Douglas Astronauti _ Co.(714-896-4551) 5301 B_is_ Ave.
Huntington Beach, CA 92647
Dave Massie A.F. Aero Propulsion Lab(513-255-6235) AFAP/POE
Wright Patterson AFBDayton, OH 45433
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ATTENDEESADDRESS
NAME Headquarters-Space Division (AFSD)YLXT
Lt. Ed Gjermundsen Los Angeles Air Force Station_213-615-4195) P.O. Box 92960
Los Angeles, CA 90009
Marshall Space Flight CenterER01
Jack MacPherson Marshall Space Flight Center, AL 35812(205-453-1023)
Lockheed Missiles & Space Co.P. O. Box 504 B/151 0/6216
Mike Glass Sunnyvale, CA 94086
Lockheed Missiles & Space Co.P. O. Box 504 B/151 0/6216
Ron Given Sunnyvale, CA 94086(408-742-5194)
Lockheed Missiles & Space Co.P. O. Box 504 B/151 0/6216
Jon Armantrout Sunnyvale, CA 94086(408-743-2614)
Lockheed Missiles & Space Co.P. O. Box 504 B/151 0/6216
Larry Chidester Sunnyvale, CA 94086(408-742-2270)
Marshall Space Flight CenterECI2
Roy Lanier, Jr. Marshall Space Flight Center, AL 35812(205-453-2113)
McDonnell Douglas5301 Bolsa Ave. M/S14-3
Paul Crawford Huntington Beach, CA 92647(714-896-4858)
McDonnell Douglas5301 Bolsa Ave. M/S14-3
Wayne Marcus Huntington Beach, CA 92647(714-896-4309)
Marshall Space Flight CenterPDI4
Donald E. Williams Marshall Space Flight Center, AL 35812(205-453-3666)
Marshall Space Flight CenterEDI5
Harry Buchanan Marshall Space Flight Center,AL 35812(205-453-4582)
Marshall Space Flight CenterECI3
C. S. Crowell _Marshall Space Flight Center, AL 35812(205-453-4637)
MartinMariettaDenverAerospaceMS 1130
JohnW. Lear P. 0.Box179(303-977-5457) Denver,CO 80201
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ATTENDEES ADDRESS
N______ Jet PropulsionLabM.S. 198-224
Irv Stein 4800 Oak Grove Dr.(213-354-6048) Pasadena,CA 91109FTS 792-6048
General Dynamics-ConvairM.S.41-6760
Dave Peterson P.O. Box 80847(714-277-8900) San Diego, CA 92138ext 2204
NationalAeronauticsand Space AdministrationRTS-6
Wayne Hudson 600 IndependenceBlvd.(202-755-3278) Washington, D.C. 20546
National Aeronautics & Space AdministrationRSS-5
Richard A. Gualdoni 600 Independence Blvd.(202-755-2403) Washington, D.C. 20546
National Aeronautics & Space AdministrationRTE-6
Ronald L. Larsen 600 Independence Blvd.(202-755-3273) Washington, D.C. 20546
Martin Marietta Corp.P. O. Box 179
Matt S. Imamura Denver, CO 80201(303-977-0701)
Marshall Space Flight CenterPDI4
Don Routh Marshall Space Flight Center, AL 35812(205-453-3773)
NASA/Marshall Space Flight CenterPD24
Danny Xenofos Marshall Space Flight Center, AL 35812(205-453-4261)
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I. REPORT NO, 2. GOVERNMENT'ACCESSION NO. 3. RECIPIENT'S CATALOG NO.NASA CP-2213
4. TITLE AND SUBTIT'LE 5. REPORT DATE -
March 1982• Space Power Subsystem Automation Technology 8. PERFORMINGORGANIZATIONCODE
7. AUTHOR(S) 8. PERFORMING ORGANIZATION REPORT #
ComPiled by Jame_ R, Graves9. PERFORMING ORGANIZATION NAME AND ADDRESS tO. wORK UNIT NO.
George C. Marshall Space Flight Center M-37tI. CONTRACT OR GRANT NO.
Marshall Space Flight Center, Alabama 35812
13. TYPE OF REPORT & pIERIOD COVERED
12, SPONSORING AGENCY NAME AND ADDRESS
National Aeronautics and Space Administration Conference Publication
Washington, DC 20546 14. SPONSORINGAGENCYCODE
15. SUPPLEMENTARY NOTES
Proceedings of a ConferencefW_orkshop held at the Marshall Space Flight Center,Alabama, •October 28-29, i98i.
16, ABSTRACT
With the rapidly increasing interest in the application of automation techniques to spacepower subsystems, the Office of Aeronautics and Space Technology decided to hold a workshopduring the last week of October i98i. About 50 specialists convened at the Marshall Center
for the two-day interchange. The technology issues involved in power subsystem automationand the reasonable objectives to be sought in such a program were discussed. After a full dayof review of current programs, progress, and plans, the participants were divided into four
workshops to discuses the different aspects of these issues and objectives." These proceedingsgave insight into the complexities, uncertainties, and alternatives of power subsystem auto-mation, along with the advantages from both an economic and a technological perspective.Whereas most spacecraft power subsystems now use certain automated functions, _the idea ofcomplete autonomy for long periods of time is almost inconceivable. Thus, it seems prudentthat the technology program for power subsystem automation be based upon a growth scenariowhich should provide a structured framework of deliberate steps to enable the evolution ofspace power subsystems from the current practice of limited autonomy to a greater use of automation with each step being justified on a cost]benefit basis. Each accomplishment should movetoward the objectives of decreased requirement for ground control, increased system reliabi-lity through on-board management, and ultimately lower energy cost through longer life sys-tems that require fewer resources to operate and maintain. This approach seems well-suitedto the evolution of more sophisticated algorithms and eventually perhaps even the use of somesort of artificial intelligence. On thing seems certain: Multi-hundred kilowatt systems of thefuture will require an advanced level of autonomy if they are to be affordable and manageable.
i7. KEY WORDS .... 18. DISTRIBUTION STATEMENT '
Spacecraft automation technology Unclassified - UnlimitedAutomation components technologyPower system autonomy
Subject Category 20
'1'9. SECURITY CLASSIF. (of this report'j 20. SECURI'TY CLASSIF. (of this pale) 21. NO. OF PAGES 22. PRICE
Unclas sffied Unclassified 2i 5 At 0. T , • ,
For sale by National Technical Information Service, Spzingfleld, Virginia 22151
NASA-Langley,1982
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National Aeronautics and SPECIAL FOURTH CLASS MAIL Postage and Fees Paid _==m==._==_
SpaceAdministration BOOK National Aeronautics andSpace Administration
Washington,D.C. NASA-45120546Official Business
Penalty for Private Use, $300
POSTMASTER: If Undeliverable (Section 158Postal Manual) Do Not Return
II I III