T.I.G.E.R. Mission Terra Nova Mission Concept Revie · Mission Concept Review . ... Map the terrain...
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Terra Nova Mission Concept Review T.I.G.E.R. Mission
Transcript of T.I.G.E.R. Mission Terra Nova Mission Concept Revie · Mission Concept Review . ... Map the terrain...
Terra Nova Mission Concept Review
T.I.G.E.R. Mission
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Title Team Structure
…………………………………..
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Title Mission Constraints
1.) Conduct science in orbit and on the surface of Enceladus 2.) $3B budget in FY15 3.) Atlas V-551 base launch vehicle 4.) 1 ASRG (additional $57 million) 5.) Launch within 10 years of funding
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Title Enceladus
• Sixth largest moon of Saturn • Producer of the E-ring • Surface temperature of -201 degrees Celsius • Interesting geothermal activity • Plumes at south pole jettisoning out H2O • Currently holds high potential for life
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Title Science Goals
Terra Nova Science Mission Objectives:
1. Understand interactions between Enceladus and Saturn
2. Map the terrain of Enceladus
3. Analyze composition of the surface and atmosphere
4. Develop better understanding of cryovolcanism and geysers on moon
Orbiter & Lander chosen to achieve science goals
• Surface Chemistry Package and LDMS to test physical composition and biological potential
• Camera and seismometer to test geologic activity
• Visible/near IR and thermal imagery
• Radio sounder to understand the interior structure
• Dust Micro-Analyzer along with a GCMS to understand the plumes
• Magnetometer to better understand magnetic interaction with Saturn
Orbiter Lander
Both
Science Mission Objective
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Title Orbiter Science Traceability Matrix
Science Objectives Measurement Objectives Instruments
Map surface and observe changes Create visual maps & compare THEMIS System (Thermal
emission Imaging System
Derive ejected matter composition Capture ejected materials MEMSA (Micro Electron with
Microprobe Sample Analyzer)
Understand interior structure
Measure and confirm interior structure
MARSIS (Mars Advanced Radar for Subsurface and Ionosphere
Sounding) Understand cryovolcanism
mechanisms Determine surface composition Ralph - Multicolor Visible Imaging Camera
Understand tectonics Characterize magnetic & plasma
environment and induction signature
Magnetometer (MAG)
Understand elements present on surface
Produce ions from substances to analyze
Cassini-Huygens Probe GCMS (Gas Chromatograph Mass
Spectrometer)
Measure seismic activity Determine tidal & global/static topography
LOLA (Lunar Orbiter Laser Altimeter)
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Title Lander Science Traceability Matrix
Science Objectives Measurement Objectives Instruments
Understand magnetic effects
Understand magnetic field & interaction with Saturn's field
Urey Instrument - Surface Chemistry Package
Observe high-detail imagery of surface
Obtain high-definition imagery of landing site PanCam - Panoramic Camera
Understand composition of surface
Determine surface composition with direct samples
MOMA (Mars Organic Molecule Analyzer)
Understand internal seismic activity & effects
Determine geologic seismic activity contribution to landscape
changes Seismometer
Understand magnetic field & interaction with Saturn’s
Separate magnetic effects from those caused by Saturn MAG - Magnetometer
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Title Terra Nova Solution: T.I.G.E.R.
Vecto (Bus)
Meta (Orbiter)
Sentio (Lander)
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Title T.I.G.E.R. Mission
Targeted Investigation and Gathering of Enceladian Research (T.I.G.E.R.)
• Atlas V-551 launch vehicle
• Launch date: March 14, 2023
• 10.5 mission duration
• 2.5 year orbiting science mission
• 1 year landing science mission
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Title Trajectory
Baseline Mission Met Before Chemical Spacecraft Arrives
Chemical Trajectory – 16 years Solar Electric Trajectory – 8 years
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Title Vecto Features
• Xenon Ion Engines: NEXT
• 1010 kg max expected wet mass
• 8 years travel
• $704 M cost
• 17 kW solar electric power system
Vecto Global Presentation
Structure Solar Arrays
Electrical Network
Payload Adapter System
Hexagonal
Aluminum Alloy
Rigid Structure
63 m2
Rigid Structure
From -15° C to +50° C
Redundancy
Low Shock
Controlled Separation
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Title Vecto Propulsion
• 320 kg of Xenon
• Thrust 0.236 N
• ISP 4190 s
Acceleration of Xenon particles
NEXT for propulsion
1 spare 1 active
Configuration
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Title Meta Features
2.5 year science lifespan
2 + 1 ASRGs supply power
1303 kg max expected wet mass
116 kg max expected science
Dual-mode propulsion system
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Title Meta Mass Summary
% of Total Mass Mass (kg) Thermal 4.2 43.2
Power 6.4 66.6
Communications 12.5 129.7
Data Handling 3.3 34.6
Structures 16.5 110.0
Propulsion 7.2 75.0
GNC 2.3 23.9
Science Payload 7.8 81.0
CBE Total 100% 625.0
MGA (30%) 268.7
MEV Dry Mass 893.7
Propellant 409.3
MEV Wet Mass 1303.0
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Title Meta Structure
• Composed of aluminum alloy rods with 16 mm diameter
• High gain antenna on top for radiation shielding
Mass 110 kg Diameter 2 m Height 2.4 m
Meta structure must survive force from launch acceleration of wet mass, be light, and utilize volume
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Title Meta Stress Analysis
Max Allowable Stress 47.5 Mpa Max von Mises Stress 47.4 Mpa
Factor of safety = 2
Must support 76.2 kN of force from launch
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Title Meta Communications, C & DH
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0 10 20 30 40 50
Dat
a St
ored
(M
B)
Time (hours)
Meta Communication Profile
Communication Window 9 hours daily
Data Transmission Rate 100 kbps
Average Daily Data Sent 40 MB
Meta communications subsystem must send the data that is created by science to Earth
4m HGA on Meta using Ka-band
70m DSN dish on Earth
• Two 2 Gb SSDR
• Two RAD 750
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Title Meta Power
• 2 + 1 ASRGs
• 5.5 kg rechargeable lithium ion battery
100
120
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200
220
1 25 49 73
Pow
er (
W)
Time (hours)
Science Phase Power Profile
PowerRequired
EOL PowerGenerated
Meta power subsystem must provide power for the entire system as well as the scientific instruments on board
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Title Meta Propulsion System
Propulsion Component Quantity
Fuel Tank 1
Oxidizer Tank 1
Helium Tank 2
Main Engine 2
Attitude Control Engine 16
Meta propulsion must insert Meta into Enceladus orbit and maintain orbit
HiPAT Dual-Mode Thruster MR-106E
Thruster
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Title Meta Propulsion System
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Title Meta Thermal Control
Maintains all internal components for target of 20° C ± 5°C
• Must survive hot case at Earth flyby, endure cold case during travel
Thermal Component Quantity MLI 15 Layers VCHP 3.1 m RHU 60 Radiator with louver 4.2 m2
Waste Heat From ASRG’s Primary Heat Source
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Title Meta Guidance, Navigation, & Control
Instrument Quantity Reaction Wheel 8
Hydra Star Tracker 2
SSIRU 2
Meta GN&C subsystem must guide Meta safely into Enceladian orbit and point instruments toward the surface
100% Control Authority
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Title Sentio Features
Minimum 1 year science mission
540 kg max expected wet mass
22 kg max expected science mass
1 ASRG + primary battery
Monopropellant propulsion system
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Title Sentio Mass Summary
% of Total Mass Mass (kg)
Thermal 2.6 10.6
Power 18.8 76.4
Communications 6.2 25.0
Data Handling 8.5 34.6
Structures 27.3 106.0
Propulsion 8.3 33.6
GNC 1.3 5.3
Science Payload 3.8 15.4 CBE Total 100% 311.7 MGA (30%) 134.0 MEV Dry Mass 445.8 Propellant 94.3 MEV Wet Mass 540.1
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Title Sentio Landing Zone
South Polar Region
The “Tiger Stripes”
Within 500 m of the safest plume determined after surface mapping
performed by Meta
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Title Sentio Structure
Trapezoidal design based on Enceladus Flagship Mission Concept Study conducted
by NASA Goddard Space Flight Center
Mass 106 kg
Height (stowed) 0.6 m
Height (landing) 1.1 m
Bottom Surface Area 1.14 m2
Top Surface Area 0.51 m2
Spring loaded aluminum legs with aluminum honeycomb inserts and
circular footpad
Sentio structure must survive force from 9G landing deceleration of dry mass
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Title Sentio Stress Analysis
Max Allowable Stress 47.5 MPa
Max von Mises Stress 6.5 MPa
• Force from landing: 26.8 kN
• Factory of Safety: 2
• Force is split between 3 legs
• Capable of landing on inclined surface up to 12˚
Sentio Communications, C & DH
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0
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25000
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35000
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45000
0 12 24 36 48 60 72 84 96 108 120 132 144 156 168 180 192 204 216
Dat
a St
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(M
b)
Time (hours)
Sentio Communication Profile
Communication Window 94 minutes daily Data Transmission Rate 128 kbps
Component Quantity
Helix Antenna 1
Monopole Antenna 1
UHF Transceiver 2
UHF Diplexer 2
Coax Transfer Switch 2
Sentio communications subsystem must send all collected science data to Meta
• RAD 750 computer • Two 2 Gb SSDR
Continues to mission end
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Title Sentio Power Sentio power subsystem must provide power for all Sentio subsystems including all scientific instruments throughout the life of the mission
• 1 ASRG • 4.4 kg rechargeable
lithium ion battery
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Title Sentio Power – Redundancy
Worst case scenario experience complete failure of primary power source
• 45.19 kg non-rechargeable lithium battery
• 18,182 W-hr capacity
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Title Sentio Propulsion System
Sentio propulsion must maneuver Sentio during descent procedures
Propulsion Component Quantity Fuel Tank 1 Helium Tank 1 Main Engine 2 Attitude Control Engine 16
Thrust-to-weight ratio of main engine ≥ 1.3
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Title Sentio Propulsion System
1.03 kg
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Title Sentio Thermal Control
Sentio thermal subsystem must keep spacecraft equipment and science equipment within survival and operational temperatures
Thermal Component Quantity MLI 18 Layers VCHP 6.6 m Radiator with louver 1.095 m2
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Title Sentio Guidance, Navigation, & Control
Instrument Quantity IMU 4 Star Sensor 2 Radar Altimeter 1
Sentio GN&C must maintaining proper positioning and attitude control during the descent to the surface of Enceladus
Inertial Measurement
Unit (4)
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Title Mass Summary
Sentio 402 535
Meta 1022 1288
Vecto 1010 1280
CBE (kg) MEV (kg)
3103 kg
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Title Cost Analysis
0
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Meta Sentio Vecto Total
FY 1
5 D
olla
rs (
Mill
ion
)
ASRG Penalty
Launch Services
30% Reserve
Est Cost (FY15)$735 $532 $704
$1.97B
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Title Risk Analysis
Risk Description
R1 NEXT still in LDT
R2 Availability of PU-238
R3 Debris damage
R4 Cost model uncertainty
R5 Landing zone uncertainty
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Title Summary
• Atlas V 551 – 3213 kg throw mass • Cape Canaveral 14 March 2023
Launch
• Extensive operational lifetime • Comprehensive instrument suite
Science
• Vecto • NEXT is an enabling technology • 1+1 Thruster configuration
• Meta • 2+1 ASRG
• Sentio • Soft lander • ASRG allows year long baseline mission
Architecture
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Title
BACKUP SLIDES
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Title Backup – Vecto Mass Summary
% of Total Mass Mass (kg)
Power 24 118.4
Structures 25 121.7
Propulsion 51 248.2
CBE Total 100% 488.3
MGA (30%) 210.0
MEV Dry Mass 698.3
Propellant 311.7
MEV Wet Mass 1010
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Title Backup – Orbital Science Mission
Instrument Capabilities
Thermal Emission Imaging System (THEMIS)
Uses multi-spectral thermal infrared images to determine surface mineralogy and physical properties
Multicolor Visible Imaging Camera (Ralph)
Covers large areas in a short period of time without mosaic photos like a traditional framing camera
Radar Sounder (MARSIS) Uses radar waves in the range of 15-25 MHz to search for liquid or frozen water up to 1 km beneath the surface
Micro Electron Microprobe with Sample Analyzer (MEMSA)
To confirm composition of ejected materials by sampling the plumes
Lunar Orbiter Laser Altimeter (LOLA)
Uses global static short wavelength topography to determine time variable long wavelength
Magnetometer Characterizes the magnetic and plasma environment
Cassini-Huygens Titan Probe (GCMS)
Defines mass spectrum of molecules found on the surface to determine molecular structure and composition
Doppler Wind Experiment (DWE)
High precision tracking investigation to determine wind direction and magnitude
Backup – DV Table
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Sentio Maneuver DV (m/s) DV Margin (%)
Effective DV (m/s)
Plane Change/Retroburn 88.9 10 97.8
Null Impact Velocity 180 10 198
Hazard Avoidance 90 10 99
Total Sentio DV w/ Reserve
358.9 394.8
Meta Maneuver DV (m/s) DV Margin (%)
Effective DV (m/s)
Enceladus Orbit Insertion 47.8 10 52.6
Plane Changes (4) 400 10 440
Orbit Maintenance 60 10 66
DV Reserve 500 500
Total Meta DV w/ Reserve 1007.8 1058.6
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Title Backup – Meta Power
Instruments Mass (Kg) Power(W) Lifetime (yrs) Frequency Duration Thermal Mapper 11 14 2.5 48 hours 24 hours Visible near/ir mapper 10 6 2.5 48 hours 24 hours
Dust Mirco Analyzer 10 5 2.5 continuous continuous
Laser Altimeter 10 10 2.5 continuous continuous
Magnetometer(2) 8 2 2.5 continuous continuous
GCMS 10 20 2.5 continuous continuous MARSIS (Radar Sounder) 20 60 2.5 24 hours 4 hours Radio Science (orbiter) - Doppler Wind Exp. from Cassini-Huygen 2.05 18.4 2.5 continuous continuous Orbiter Communications 149.1 74.1 2.5 24 hours 9 hours
Orbiter Thermal 32.57 10 2.5 continuous continuous Orbiter GNC 16.7 20 2.5 Orbiter Data Handling 24.5 46.8 2.5 Total 303.92 286.3
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Title Backup – Meta Propulsion System
• Bi-propellant main engine • Mono-propellant attitude control
engines • Fuel – hydrazine • Oxidizer – nitrogen tetroxide (NTO)
Bi-propellant dual-mode
system
• Two propellant tanks - fuel & oxidizer • Two helium tanks & helium • Distribution & control system - piping &
valves • Engines - main and attitude control
Subsystem consists of:
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Title Backup – Landing Science Instruments Instrument Capabilities
Urey Surface Chemistry Package
Identify oxidants in the surface ice and measure isotopes
Short Period Seismometer (SEIS)
To detect long period normal mode oscillations
Panoramic Camera (PANCAM)
To obtain a panoramic view of the Enceladian landscape
Descent Imager Takes photos to determine surface terrain
Magnetometer Characterizes the magnetic and plasma environment
Laser Desorption Mass Spectrometer (LDMS)
Characterizes complex mixtures of large molecules
Sampling Arm Gathers small samples of surface material for the Urey instrument
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Title Backup – Meta Propulsion Propellant Mass
Mass (kg) % Additional
Nominal Propellant 342.09 ----
Residuals & Uncertainty ---- 8.5
Loaded Propellant 371.17 ----
ACS Propellant ---- 9.0
Total Fuel 234.04 ----
Total Oxidizer 170.54 ----
Total Propellant 404.58 ----
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Title Backup – Meta Propulsion Engines & Tanks
Engine Classification Chosen Engine Quantity Specific
Impulse Propellant
Main HiPAT 445N (100-lbf) Duel Mode 2 329 sec Hydrazine / Nitrogen
Tetroxide (NTO)
Attitude Control MR-106E 22N (5-lbf) 16 235-229 sec Hydrazine
Tank Classification Contains Material Volume (m3 x 103)
Fuel Hydrazine PMD 301.4
Oxidizer NTO PMD 152.7
Fuel Pressurant Helium COPV 67.3
Oxidizer Pressurant Helium Metallic 18.8
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Title Backup – Sentio Dry Mass
% of Total Mass Actual Mass (kg)
Thermal 2.6 10.6
Power 18.8 76.4
Communications 6.2 25.0
Data Handling 8.5 34.6
Structures 27.3 110.8
Propulsion 8.3 33.6
GNC 1.3 5.3
Science Payload 3.8 15.4 Total 100% 311.7 MGA (30%) 134.0 Total w/ MGA 445.8
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Title Backup – Sentio Power
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1 5 9 13 17 21 25 29 33
Pow
er (W
)
Time (mins)
Landing Operations
TotalPower
Avg Pwr
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Title Backup – Sentio Propulsion System
• Mono-propellant main engine • Mono-propellant attitude control
engines • Fuel - hydrazine
Mono-propellant dual-mode
system
• One propellant tank • One helium tanks & helium • Distribution & control system - piping
& valves • Engines - main and attitude control
Subsystem consists of:
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Title Backup – Sentio Propulsion Propellant Mass
Mass (kg) % Additional
Nominal Propellant 87.63 ----
Residuals & Uncertainty ---- 3.5
Loaded Propellant 90.70 ----
ACS Propellant ---- 3.0
Total Propellant 93.42 ----
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Title Backup – Sentio Propulsion Engines & Tanks
Engine Classification Chosen Engine Quantity Specific
Impulse Propellant
Main MR-120 90N (20-lbf) 2 229 – 222 sec Hydrazine
Attitude Control MR-106E 22N (5-lbf) 16 235 – 229 sec Hydrazine
Tank Classification Contains Material Volume (m3 x 103)
Fuel Hydrazine PMD 126.2
Fuel Pressurant Helium Metallic 28.7
