INTEGRATED TECHNOLOGY PLAN EXTERNAL REVIEW JUNE 26, 1991 ... · integrated technology plan i...

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LOW THRUST PROPULSION

INTEGRATED TECHNOLOGY PLAN

IEXTERNAL REVIEW

JUNE 26, 1991

L,.,

5"

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AGENDA

APPLICATIONS

OBJECTIVE

STATE-OF-ART MISSION IMPACTS

EARTH SPACEPLANETARY

PROGRAM

APPROACHCONTENT

= "STRATEGIC"= "CURRENT"

ADVANCED TECHNOLOGY BENEFITS

-- • SUMMARY

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https://ntrs.nasa.gov/search.jsp?R=19930074429 2020-03-23T23:05:33+00:00Z


I LARGESPACESYSTEMSII

AUXILIARY

CHEMICAL

ELECTRIC

PLANETARY

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SPACE PROPULSION TECHNOLOGY DIVISION

LOWTHRUSTPROPULSION

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JOBJECTIVE'!

PROVIDETECHNOLOGIESFOR A BROADRANGEOF FUTURE SPACESYSTEMS

• SPACECRAFT

--PLANETARY

--EARTH-ORBITAL

• LARGE SPACESYSTEMS--SPACE STATION_

--TENDED .......

CD-I10-41480

• VEHICLES

--EARTH-TO-ORBiT

--ORBIT TRANSFER

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STATE-OF-ART


MISSION IMPACTS

LOW EARTH ORBIT (LEO):

- ORBITER APS

- SPACE STATION

GEOSYNCHRONOUS (GEO):

- TRANSFER ORBIT (GTO)

- SATELLITES

PLANETARY

LOW THRUST PRIMARY AND AUXILIARY PROPULSION

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lAPS OFFERS MAJOR LEVERAGEI

SIIUTTLEOi'IDITEI1

/_PS MASS- KLDS

40--

30--

20--

10 --

0DUEEP.$T sonTIE

MISSION

• APS MASS IS 11.4°/o TO 18.6% OF 0RIJITER

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_A F_EED_I¢

SPACE STATION FILEEDOM - PIVlC

Propulsion System PropeUaut Resupply

"%_5-

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r "1' II --- No Low-Thrust

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* AVERAGED OVER 11 YEAR CYCLE

BASELINE SPACE STATION FREEDOMPROPULSION REQUIRES _>23K LBSLOGISTIC/YEAR*

MANIFEST & OTHER CONSTRAINTSIMPLY= 1 SHUTTLE ORBITER FLIGHT/YEAR WiTH BASELINE PROPULSION

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GEOSYNCHRONOUSTRANSFERORBITMASS FRACTIONSFORRECENTCOMMUNICATIONSSATELLITES

1.0 m

FRACTIONINJECTED 0.5 --

MASS

0.0INTELSATVA SATCOMKu 3('THREEAXIS) (THREE AXIS)

J--] NONPROPULSIONMASS

_ PROPULSIONDRY MASS

ON-ORBITPROPELLANT

APOGEEPROPELLANT

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FRACTIONINJECTED

MASS

PLANETARY SPACECRAFT INJECTED MASS FRACTIONS

1.0 r- _ ,,'[-'----

......,..,,.......,.

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PIONEER10 & 11

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PROPULSIONDRYMASS

0N-0RBITPROPELLANT _,

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STATE -OF-ART


MISSION IMPACTS

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_LEO

12-19% OF ORBITER DELVERED MASS (> 50% OF PAYLOAD)~ ORBITER/YEAR FOR SPACE STATION LOGISTICS

GEO

55-65% OF MASS DELIVERED TO GTOON-ORBIT LIFE LIMITER

PLANETARY

OVER 80% OF INJECTED MASS FOR PLANNED MMII MISSIONS

IIN-SPACE FRACTIONAL MISSION PENALTIESREDUCED ONLY BY IMPROVED IN-SPACE PROPULSION

!

PR3-5

LOW THRUST PRIMARY & AUXILIARY PROPULSION

JPL

MANAGEMENT STRUCTURE

506-42-31

°OO"AMi IMANAGER _"

(OAST/RP) i

LERC

SSTAC

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' I" PROGRAMMATIC APPROACH !

PROGRAM STRUCTURED TO SUPPORT:• TECH TRANSFER & APPLICATIONS VERSUS TIME• MAJOR BENEFITS FOR FUTURE MISSIONS

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HIGH POWER1ELECTRIC

MPD


I CHEMZCALI

STORABLES INTEGRATEDH/O

ELEMENTS

ION ARCJET

LOW POWER IELECTRIC

RESISTOJET

co-go-47613

LOWTHRUSTPROPULSION

]STORABLESJ

.... I

THRI

CHEMICAL

[ FUNDAMENTALS ]

JHYDROGEN/OXYGEN J

CD-gO-4761|

PR3-7

I SYSTEM ITECHNOLOGYI


LOW POWER

ELECTRIC

[ FUNDAMENTALSJ

INTEGRATION1TECHNOLOGY

CD-90-476t4

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I FUNDAMENTALSI

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ADVANCED ICONCEPTS

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TECHNOLOGY TRANSFER

I MECHANISMS/EFFORTS I

SPACE ACT AGREEMENT (NASA/INDUSTRY)

FOUR IN PLACE

THREE IN NEGOTIATION

BAILMENT AGREEMENT (NASA/INDUSTRY)

- ONE IN PLACE

MOA (INTRA AGENCY)

- TWO IN PLACE

"OUTREACH" (ACADEME & DOE)

- FIVE ARCJET SYSTEMS PROVIDED

- ION SYSTEMS IN FAB

LOW THRUST Pk,.,PULSION"STRATEGIC "PROGRAM (1)

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(11.o)

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91 92 93 94

FY

TRANSPI_

DOW POWER ID_RIC

HIGH POWER I¢_¢

LOW THRU_'T CHEMICAL

(12.5)

95 96

(l) A.._SUMES PROPOSED NEP & DEEP SPACE PLATFORM PROPULSION FOCUS£D pROCRAMS

(_4.5)

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LOW THRUST Pi. JPULSION

" CURRENT " PROGRAM (I)

] TgCH TP.,AJCSFIgR

LOW POWER gLEC'rRIC

] HIGH POWER _C

] LOW THRUST CHEMICAL

8

(6. I) (6.3)

_Of_

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91 92 93 94 95 96 97

FY

{I)/kqsuMF.,$ PROPOSED NZP & DEEP 8PACE PLATI_OP, M PROPULSION FO_JS_D PROGlUd_S

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LOW THRUST CHEMICAL

TECHNOLOGIES

EARTH-STORABLE

NTO/MMH

NTO/N2H 4

SPACE STORABLELOYJN2H4LOX/HC

INTEGRATED 14/O

PROGRAM

"CURRENT" "STRATEGIC"

• VALIDATE 100LBF ROCKET FOR MMII • VALIDATE 100LBF ROCKET FOR MMII• COMPLETE 15LBF ROCKET VALIDATION• APOGEE VERSION DEMO

(1) (1)

• ROCKET DEMO • ROCKET VAUDATIONVEHICLE APS ROCKET DEMO

• RAD-COOLED ROCKET VALIDATION• VEHICLE APS PROGRAM INITIATED

(1) ASSUMED FOCUSED PROGRAM

PR3-10

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LOW THRUST PROPULSIONii

LOW POWER ELECTRIC

PROGRAM

TECHNOLOGIES "CURRENT' "STRATEGIC"

ARCJET

>600s, 1-2kW

<IKW & 2-5KW

• ROCKET VALIDATION ROCKET, PPU, & GASSIFIERVALIDATION

• SYSTEM TECHNOLOGY VALIDATIONS

DERATED" ION • THRUSTER DEMO • THRUSTER/PPU DEVELOPMENT

"HALL THRUSTER" • TECHNOLOGY EVALUATION • TECHNOLOGY EVALUATION

"STRATEGIC" PROGRAM ENABLES SECOND GENERATION ARCJETAND STATIONKEEPING ION OPTIONS

= =

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TECHNOLOGIES

SEPS

NEPS (ROBOTIC)


I "STRATEGIC" VERSUS "CURRENT" PROGRAM I

HIGH POWER ELECTRIC (1)

"CURRENT"

THRUSTER VALIDATION

THRUSTER DEMO_

PROGRAM

"STRATEGIC"

SYSTEM VALIDATIONS- THRUSTER- PPU

THERMAL & PROP. MGT.INTERFACES

SYSTEM INTEGRATION INITIATED

• SYSTEM R&TINITIATED

"STRATEGIC" PROGRAM ENABLES SEP & ROBOTIC NEPSSYSTEM R&T

(1) MWCLASS NEPS FOCUSED PROGRAM ASSUMED

PR3-11

I SPACECRAFT ON-BOARD PROPULSION (LERC, JPL) [

GOAL: PROVIDE DUAL-MODE (NTO/N2H 4) PROPULSION FOR P_N_ARY MISSIONS

AUGME_ATION OBJECTWEi [ASSURE DUAL MODE PROPULSION READINESS]• DEVELOP DUAL MODE HOT ROCKET• DEVELOP ADVANCED TANKAGE

I STATIONKEEPING PROPULSION (LERC, JSC) J

GOAL: PROVIDE I_GRATED H/O & RESISTOJ_ SPACE STA_ON PROPULSION

AUGMENTATION: [ENABLE LOGISTICS OPERATIONS BENEFffS FOR SPACE _ATION]• DEVELOP H/O ROCKETS• DEVELOP LOW PRESSURE ELECTROLYSIS• D_ELOP SINGLE RESIST_ET FOR H20 & WASTE GAS

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GOAL: PROVIDE ADVANCED AUXILIARY PROPULSION FOR EAR_ LAUNCH VEHICLES

AUGMENTATION GOAL: [PROVIDE EVOLUTIONARY HI PERFORMANCE OPERATIONALLYEFFICIENT AUXILIARY VEHICLE PROPULSION]

• PROVIDE RAD COOLED EAR_ & SPACE STORABLE PROPULSION• PROVIDE INTEGRATED H/O PROPULSION

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FOCUSED TECHNOLOGY

SPACECRAFr ON-BOARD PROPULSION

P_T_YDb-_M ODE PROP_ION

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3-,

2- i_, ;_- _ _(1.0)

1 -

0 _93 94

(3.0)

(4.3)

95

(1.2)

JOINT JP_A _RC PRO_ PROPOSED

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m

R

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093

FOCUSED TECHNOLOGY

SPACECRAFT ON-BOARD PROPULSION

SPACE STATION FREEDOM

"STRATEGIC"

(g.9)

[] H/O PROPULSION

(7.7) I H20/GAS RESISTOJET

94 95

FY

(5._)(4.7)

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96 97

(1.4)

98

O

40

30

20

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94

FOCUSED '. _,CHNOLOGY

TRANSPORTATION

AUXILIARY PROPULSION"STRATEGIC"

(46.2)

(29 3)

95 96 97 98 99 00 O1 02

FY

INTEGRATED H]O

SPACE STORABLES

HOT ROCKETS

(9.B)

Ig/_l_ Reduced Hydrazine Logistics

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Current PotentialBaseline Baseline

1 flight per 5Propulsion Element Upmass i flight per year years

Ground Processing (Man-Hours) $2oo K/Year $200 K/5 Years

Dedicated SSF Hazardous ProcessingFacility

$50 Million N/A

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SPACE STORABLE IMPACT (1)

FIXED VOLUME

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SPACE STORABLES

• OFFER SIGNIFICANT BENEFITS FOR FUTURE ETO VEHICLES

(1) =F: McDONNEL DOUGLAS STUDY FOR JSC (MDC E0713)

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GTO

WEIGIIT,LDS

ON-BOARDPROPULSION

0000

7000

6000 I I I I300 400 500 600

STATIONKEEPING Isp, s

IMPACTS(I)

LAUNCII APOGEE

SITE Isp, s

0 KSC 313D KSC 323• KOUFIOU 313

ADVANCEDSTATIONKEEPINGAND APOGEEPROPULSION

• REDUCEGTO REQUIREMENTS• MITIGATE LAUNCH SITE IMPACTS

(1) 15 YEAll GEO LIFE, 3500 LDS EOL WEIGIIT

C[1 _ 474_,7

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ADVANCED ORBIT TRANSFER PROPULSION IMPACTS(1)

ELECTRIC CHEMICAL

MLEO, Lbs 10307 37782

TRIP TIME, DAYS 180 1

LAUNCHER DELTA il TITAN IV

O'IV SEPS IUS

ELECTRIC PROPULSION OFFERS 3X MLEO REDUCTION j

(1) AIAA 89-2496 "Electric Orbit Transfer Vehicle - A Military Perspective", S. Rosen and

J. Sloan/AFSD. 5250 Lbs to GEO

PR3-15

,JPL ADVANCED PROPULSION

FOR TIlE

MARS ROVER SAMPLE RETURN MISSIOH

Significant Launch Mass ReductionsAre Possible Using Electric Propulsion

• Electric PropulsionReduces the LEOLaunch Mass by18 to 42 Percent

• A 300-kW SEP SystemProvides the BestTrip Time Performance

• Centaur InjectionIs Replaced WithLow-Thrust Escape

40000

Om 30000

O

. 20000<O

10000

>0

[] PAYLOAD

[] DRY MASS

[] PROPELLANT

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JPL STATUS OF ELECTRIC PROPULSION FoR PLANETARY MISSIONS

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........ _ARTRA-JECTORY WITH SOLAR ELECTRICPROPULSION ENABLES FIVE ASTEROID RENDEZVOUS

PER MISSION

• FIVE ASTEROIDS CAN BE VISITED

ON THE SAME MISSION WITH

ELECTRIC PROPULSION; ONLYONE ENABLED WITH NTO/MMH

• EXAMPLE ASTEROID TOUR

INCLUDES:

4 - VESTA (90 days)

17 - THETIS (G0 days)

103 - HERA (60 days)

206- HERISLIA (60 days)

77 - FRIGGA (TO EOM)

206 - IIERISLIA (C)

5/12/99

60 dayI

-3e--

• . COAST] 3

/ / 4/26/95 _ ), % 10/29/97

-/,_ 90d., | COAST'\ ",SOd.=

!c0,sT.// \., . _ ;,i,_ / /', LAUNClI',_ I 1 /

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"_ 17-TIIETIS(S) -"

• • _ 7/25/96 - " "

coAsT"-- _.... J__.. . _-3

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NEP MISSION VS B.ALLISTIC - KEY EXPECTED IMPROVEMENTSFLIGHT TIME PAYLOAD MASS SCIENCE

1) NEPTUNE ORBITER/PROBE

SHORTER FLIGHT TIME - 11 YRS VS > 18 YRSTRITON SCIENCE - ORBITER MISSION VS 41 FAST FLYBYS (4-5 KM/S)RING SCIENCE - POSSIBLE TO SPIRAL INWARD TO RING ZONE

ATMOSPHERE SCIENCE - OBSERVATION FROM CLOSE (E.G. 3 RN)ORBIT

2) PLUTO ORBITER/PROBE

ORBITER MISSION VS FAST (13 KM/S) FLYBY FOR BALLISTICMISSIONSPIRAL INWARD AS LOW AS DESIREDRENDEZVOUS WITH CHARONDEPLOY NEPTUNE LANDER OR PROBESHORTER FLIGHT TIME, 10.5 YEARSNEP IS ENABLING (BALLISTIC MODE TAKES > 36 YRS TO DO

ORBITER)

3) JUPITER GRAND TOUR

ORBITER MISSION FOR CALLISTO, GANYMEDE, EUROPA AND IO(IF RADIATION PROBLEM CAN BE TACKLED)DEPLOYMENT OF SOME LANDERS OR PENETRATORS

c: ::

NEP MISSION VS BALLISTIC- KEY EXPECTED IMPROVEMENTS

3) MULTIPLE ASTEROID RENDEZVOUS

4)

5)

MINIMUM OF SIX RENDEZVOUS WITH _ ASTEROIDS(SIZE, TYPE) VS ONE MAJOR TARGET PLUS ONE OR TWO SMALLTARGETS OF OPPORTUNITYON AN AVERAGE OF ONE RENDEZVOUS EVERY TWO YEARS VS -ONE EVERY 4 YEARS

JUPITER POLAR ORBITER

• ADVANTAGE EXISTS IN LARGE PAYLOAD - POTENTIAL FOR MULTI-SPACECRAFT FIELDS AND PARTICLES EXPERIMENTS

COMET NUCLEUS SAMPLE RETURN

• BETTER PERFORMANCE AND ACCESSIBILITY TO LARGER NO. OFCOMETS (MORE OPPORTUNITIES)

• PRESERVATION OF SAMPLE• LOWER APPROACH SPEED WHEN RETURNING TO EARTH

(V_=0 km/s)• IF ALLOWED TO SPIRAL BACK INTO EARTH THEN ORBITAL SAMPLE

RECOVERY INSTEAD OF HIGH VELOCITY (Voo=15km/s) DIRECT ENTRY

i PR3-17

LOW THRUST PROPULSIONII

ESSENTIAL FOR SPACE MISSIONS

- EARTH SPACE- PLANETARY

PREDOMINANT LAUNCH & SPACE VEHICLE "PAYLOAD"

HI LEVERAGE TECHNOLOGIES DEFINED

- INITIAL TRANSFERS ACHIEVED

BROAD & MAJOR BENEFITS ASSURED WITH SUPPORT:

- SPACECRAFT- PLATFORMS- TRANSPORTATION

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INTEGRATED TECHNOLOGY PLAN EXTERNAL REVIEW JUNE 26, 1991 ... · integrated technology plan i...

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