Terra Nova Mission Concept Review

T.I.G.E.R. Mission

2

Title Team Structure

…………………………………..

3

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

4

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

5

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

7

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)

8

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

9

Title Terra Nova Solution: T.I.G.E.R.

Vecto (Bus)

Meta (Orbiter)

Sentio (Lander)

10

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

11

Title Trajectory

Baseline Mission Met Before Chemical Spacecraft Arrives

Chemical Trajectory – 16 years Solar Electric Trajectory – 8 years

12

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

14

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

15

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

16

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

17

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

18

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

19

Title Meta Communications, C & DH

0

5

10

15

20

25

30

35

40

45

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

20

Title Meta Power

• 2 + 1 ASRGs

• 5.5 kg rechargeable lithium ion battery

100

120

140

160

180

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

21

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

22

Title Meta Propulsion System

23

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

24

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

25

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

26

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

27

Title Sentio Landing Zone

South Polar Region

The “Tiger Stripes”

Within 500 m of the safest plume determined after surface mapping

performed by Meta

28

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

29

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

30

0

5000

10000

15000

20000

25000

30000

35000

40000

45000

0 12 24 36 48 60 72 84 96 108 120 132 144 156 168 180 192 204 216

Dat

a St

ored

(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

31

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

32

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

33

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

34

Title Sentio Propulsion System

1.03 kg

35

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

36

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)

37

Title Mass Summary

Sentio 402 535

Meta 1022 1288

Vecto 1010 1280

CBE (kg) MEV (kg)

3103 kg

38

Title Cost Analysis

0

200

400

600

800

1000

1200

1400

1600

1800

2000

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

39

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

40

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

41

Title

BACKUP SLIDES

42

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

43

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

44

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

45

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

46

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:

47

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

48

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 ----

49

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

50

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

51

Title Backup – Sentio Power

80

90

100

110

120

130

140

150

160

170

180

1 5 9 13 17 21 25 29 33

Pow

er (W

)

Time (mins)

Landing Operations

TotalPower

Avg Pwr

52

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:

53

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 ----

54

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