Crew Exploration Lander for Ganymede, Callisto, and … training 6-person crew 3.4 day transits 180 days in lunar orbit Three LM1s (for redundancy ... ROV – (Surface) Rover Vehicle

SSD LM1 Moon LanderSlide 1 of 18 Slides

Mark G. Benton, Sr.8/3/2009 10:53 PM

© 2009 Mark G. Benton, Sr.All Rights Reserved

Mark G. Benton, Sr., The Boeing CompanyMark G. Benton, Sr., The Boeing CompanyAIAA 2009 Joint Propulsion ConferenceAIAA 2009 Joint Propulsion Conference

August 3 August 3 -- 5, 2009, Denver, Colorado5, 2009, Denver, Colorado

Crew Exploration Lander for Ganymede, Crew Exploration Lander for Ganymede, Callisto, and EarthCallisto, and Earth’’s Moon s Moon -- Vehicle Vehicle

System DesignSystem Design (AIAA(AIAA--20092009--5179)5179)

Spaceship DiscoverySlide 1 of 18 Slides

AIAA 2009 Joint Propulsion Conference8/3/2009 10:53 PM





Spaceship Discovery Spaceship Discovery –– ArchitectureArchitecturefor Human Solar System Explorationfor Human Solar System Exploration

Spaceship DiscoveryConceptual vehicle architectureModular spacecraft, assembled

in Earth parking orbitNumber of drop tanks tailored

to mission V requirementsBi-modal NTR engines

– High Isp propulsion (950 s)– High elec. power (200 kw)

Crew protective systems– Artificial gravity– Radiation shielding– High degree of redundancy

Design Reference Missions *DRM 1: MoonDRMs 2 / 3: MarsDRMs 5 / 6: Callisto / Ganymede

Launch, Assembly, DepartureModular 50 MT subassemblies

(33.0 m L x 8.4 m dia.) launched Assembled in 556 km (300 nmi)

altitude, circular Earth orbitSystems checked out and

propellant tanks topped offMission crew arrivesEscape to solar transfer ellipse

* Note: DRM 4 exploration mission to asteroid Ceres reserved for future work

Crew Module (CM)

Service Module (SM)

Main LH2Propellant Core Tank (CT) (4 pl)

Engineering Module (EM)

Main LH2Propellant Drop Tank (DT) (12 pl)

Deployable Solar / Thermal Shade (2 pl)

Side View Cutaway –Key Features

Side View –Main Ship

Closed Brayton Cycle (CBC) Electrical Gen. System (3 places)

5-Port Docking Module (DM)

Very Low Boil off System (VLBOS) (Cryo. Retention)

Ganymede, Callisto, Earth’s Moon Lander Module LM1(DRMs 1, 5, 6)

Mars Lander Modules LM2, LM3 (DRMs 2, 3)

Reentry Module (RM)

Bimodal Nuclear Thermal Rocket (NTR) Engine (3 pl)

Abort Propulsion System (APS) Main Engine

Artificial Gravity (AG) Centrifuge

Galactic Cosmic Ray (GCR) & Solar Particle Event (SPE) Biological Shield (LH2 & H2O)

Gimbaled High Gain Antenna (2 pl)




Spaceship Discovery Spaceship Discovery –– Details ofDetails ofDRMs 1, 5, and 6 Exploration MissionsDRMs 1, 5, and 6 Exploration Missions

DRM 1 – Earth’s Moon Flight test SSD Flight test LM1 landersCrew training 6-person crew 3.4 day transits 180 days in lunar orbit Three LM1s (for redundancy) 30 day duration per lander

DRM 5 – Callisto Four person crew Four year total durationOne year, 9 month transits 183 day wait time at JupiterCapture into 185 km circular

Callisto parking orbit Three LM1s (for redundancy) 30 day duration per lander

DRM 6 – GanymedeCrew, duration, transits, wait

time at Jupiter same as DRM 5Capture into 185 km circular

Ganymede parking orbit Three LM1s (for redundancy)

b. DRMs 5 or 6 – Outbound Transit to Jovian System and Insertion into Callisto or Ganymede Orbit

a. DRMs 5 or 6 – Assembly in Earth Parking Orbit in Preparation for Trans-Jupiter Injection

c. DRMs 5 or 6 – In Orbit around Callisto or Ganymede, Ready for Landing MissionsDRM 1 – Trans-Lunar Injection, Outbound Transit, Lunar Orbit Insertion, and Ready for Landing Missions

d. DRMs 5 or 6 – Trans-Earth Injection, Inbound Transit, and Earth Trajectory InjectionDRM 1 – Trans-Earth Injection, Inbound Transit, and Earth Orbit Insertion




LM1 Design RequirementsLM1 Design Requirementsand Mission Flight Performanceand Mission Flight Performance

Target Planetary Body Ganymede Callisto Moon

Planetary ParametersRadius at Surface (km) 2,631 2,410 1,738Equatorial Rotation (m/s) 26.7 10.5 4.6Gravitational Parameter (km3/s2) 9,887 7,179 4,903Gravity at Surface (m/s2) 1.428 1.237 1.62Circ. Parking Orbit ParametersParking Orbit Radius (km) 2,816 2,596 1,923Parking Orbit Altitude (km) 185.4 185.4 185.4Orbital Velocity (m/s) 1,874 1,663 1,597Descent ParametersV for Transfer Burn 1 (m/s) 221 203 197 Periapsis Altitude (PDI) (km) 15.2 15.2 15.2 Inertial Velocity at PDI (m/s) 1,968 1,749 1,711Relative Velocity at PDI (m/s) 1,941 1,739 1,706True Anomaly at Landing (deg) 11.9 10.4 13.9 Ascent ParametersRelative Vel. at Burnout (m/s) 1,938 1,707 1,628Rel. Vel. at 185 km Alt. (m/s) 1,876 1,663 1,600V for Circulariz. Burn 2 (m/s) 335 265 258Ascent True Anomaly (deg) 37.7 38 32.31 Includes 25 m/s maneuvering, 5 degree decent plane change, and 1% flight performance reserve.2 Includes 100 m/s maneuvering, 5 deg. ascent plane change, launch from +30 degree inclination, and 1% flight performance reserve.

Temperature Ranges (C):Ganymede -179 to -130Callisto -196 to -116Moon -180 to +130

Descent to Surface *

Powered Descent Initiation (PDI) Point

Descent Transfer Orbit

Descent Transfer Burn

- True Anomaly, PDI to Landing

Landing Point

Ascent to Orbit *

Parking Orbit

Launch Point

Orbit Circularization Burn

- True Anomaly, Launch to Circularization Burn

* Note: Drawings Not to Scale




LM1 Design Data LM1 Design Data ––Configuration Elevation ViewsConfiguration Elevation Views

Abbreviations and AcronymsAS – Ascent StageBSW – Biological Shield WaterCOM – Communications Equip.DS – Descent StageECS – Equipment Cooling Sys. FAE – Fixed Ascent Engine FDK – Flight DeckGDE – Gimballed Descent Eng. GNC – Guidance, Nav., ControlHAB – Crew Habitat LGR – Landing Gear LSS – Life Support SystemME – Main EngineMMH – Mono-Methyl HydrazineMPS – Main Propulsion SystemNTO – Nitrogen Tetroxide OML – Outer MoldlinePRP – PropellantPRS – PressurizationRCS – Reaction Control SystemROV – (Surface) Rover VehicleRTQ – RCS Thruster QuadSCR – SupercriticalVDM – Vehicle Drive MotorVDW – Vehicle Drive Wheel

GDE (8 pl)

AS ECS/LSS Bay

DS BSW Tanks (8 pl)

Deploy w/ Pyros, Spring & Gravity Assist

45-Deg. Cutaway (LGR Stowed)

+ 0.6 m Stroke, & + 0.6 mLeveling Strut

DS Thrust Cylinder Structure Pri. Struc.

Independent Suspension VDM & VDW (8 pl)

45-Deg. Cutaway (LGR Depl.)

SSD-LM1-v2

Tunnel to Air Lock in DS

DS Cargo Bay

FDK & HABCrew Cabin

DS MPS LO2 Tank

DS Air Lock

DS MPS LH2 Tank

Side View Cutaway

Reflective Thermal Foil

AS MPS NTO Tk. (2 pl)

DS Fuel Cell /LSS SCR LO2Tks. (2 pl)

DS Fuel Cell /LSS SCR LH2Tks. (2 pl)

Fuel Cell(4 pl)

Front View Cutaway

AS RCS NTO Tk. (4 pl)

AS FAE (8 pl)

AS MPS MMH Tk. (2 pl)

AS RCS MMH Tk. (4 pl)

LSS SCR LO2 Tk. (2 pl)

ECS/LSS H2O Tk. (2 pl)

DS MPS LO2 Tank

DS MPS & BSW PRS Tks (4 pl)




LM1 Design Data LM1 Design Data ––Configuration Cross Section ViewsConfiguration Cross Section Views

Design Features Two-way trans: orbit – surfaceAbort to orbit during descentSingle engine-out redundancy FDK, HAB, ROV functionalityRadiation shielding for HAB Insulation for extreme tempsCrew: 2 (3 for rescue)Payload: 500 / 125 kg (DS/AS)Endurance:30 / 7 d (DS/AS) LM1 Total Masses

– 21.97 MT (Ganymede)– 19.62 MT (Callisto)– 20.12 MT (Earth’s Moon)

Descent Section (DS) LH2 – LO2 MPS propellants (8) gimballed, 12.2 kN main eng.

(throttleable 100% - 30%)Power: LH2 / LO2 fuel cellsAirlock and cargo bay

Ascent Section (AS)MMH – NTO MPS propellants (8) fixed 3.3 kN main eng.MMH – NTO RCS propellantsPower: Solar Arrays / Batts.

DS RCS NTO Tk. (4 pl)

RCS PRS Tank (2 pl)

DS MPS NTO Tk. (2 pl)

Crew HAB Incl. Sleep, Food Prep., & Hygiene Facilities

MPS PRS Tank (4 pl)

DS RCS MMH Tk. (2 pl)

RTQ (4 pl)

FAE(8 pl)

Tunnel to Airlock in DS

AS Lower Level

LSS SCR LO2Tanks (2 pl)

Tunnel to Airlock in DS

AS Upper Level

DS MPS LH2 Tank

Cargo Bay

DS-AS PyroSep. Bolts(6 pl)

DS Surface Access Door Pair (2 pl)

DS Fuel Cell/ LSS SCR LH2Tank(2 pl)

Airlock in DS

Insulated Fuel Cell Bay (2 pl)

DS Upper Level (LGR Stowed)

Air Lock

Cargo Bay

Fuel Cell(4 pl)

Fuel Cell / LSS SCR LO2 Tks.(2 pl)

GDE(8 pl)

DS Lower Level (LGR Depl.)

Crew Bunk(2 pl)

MPS and RCS Tank Bay (2 pl)

LSS H2O Tks (2 pl)

FDK w/ (2) Large Windows

Batteries

GNC & COM Bay

DS MPS MMH Tk. (2 pl)

DS MPS & BSW PRS Tks (4 pl)

DS BSW Tanks (8 pl)

SSD-LM1-v2




Moon Landing Mission Description Moon Landing Mission Description ––Launch, Assembly, Transit, & DeorbitLaunch, Assembly, Transit, & Deorbit

Launch and Assembly (a, b)Modular Spaceship Discovery

design: Assembly in LEO– Modules launched into 556

km (300 nmi) assembly orbit– Assembly completed during

approximately one year– Max. launch dimensions:

33.0 m long x 8.4 m dia.– Max. mass 50 MT incl. fairing

& airborne support equip. (2) 21.97 MT LM1 landers

launched simultaneously Outbound Transit and

Landing Preparations (c) (3) landers docked to Spaceship

Discovery docking moduleHibernation mode during transit LM1s cryo. tanks cooled by

Spaceship Discovery VLBOSCapture into moon parking orbit

Start of Landing Mission (d)Crew enters LM1 lander Lander undocks in moon orbit Landing gear extends & locksDeorbit burn injects vehicle into

descent transfer orbit (d) Deorbit Burn

(b) Orbital Assembly(a) Launch Configuration

(c) In Transit

SSD-LM1-v2




Moon Landing Mission Description Moon Landing Mission Description ––Powered Descent (PD) Flt. PerformancePowered Descent (PD) Flt. Performance

Powered Descent Trajectory - Altitude vs. Downrange Displacement

0.0

0.5

1.0

1.5

544.5 545.0 545.5 546.0 546.5 547.0 547.5

Downrange Displacement from Entry Interface (km)

Alti

tude

(km

)

100 m Hover Altitude

Powered Descent Trajectory - Axial Velocity vs. Altitude

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8

12

16

20

02004006008001,0001,2001,4001,6001,800

Velocity (m/s)

Alti

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Entry Interface Altitude

Powered Descent Trajectory - Axial Velocity vs. Altitude

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Descent to Surface *

Powered Descent Initiation (PDI) Point

Descent Transfer Orbit

Descent Transfer Burn

- True Anomaly, PDI to Landing

Landing Point

* Note: Drawing Not to Scale

Note: Flight Performance Plots Shown for Ganymede Sizing Case




(b) Pitch Program

(c) Vertical Descent

(a) Powered descent Initiation (PDI)

SSD-LM1-v2

Moon Landing Mission Description Moon Landing Mission Description ––Powered Descent at Constant T/WPowered Descent at Constant T/W

Constant T/W Phase (e, f, g)Powered Descent Initiation (PDI)

at periapsis of descent xfer orbit T/W = 2.5

– Minimize gravity losses– Constant crew decel. (0.36 g)– Robust excess thrust

Pitch program controls thrust vector angle and descent rate

Single engine-out during PD –(8) for (6) engine redundancy

Powered Descent Trajectory - Flight Path and Thrust Vector Angles vs. Time

-90.00

-80.00

-70.00

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-50.00

-40.00

-30.00

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Thru

st V

ecto

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ath

Angl

e (D

eg.) Timed

HoverPhase

SoftLandingPhase

Flight Path Angle

Thrust Vector Angle

Note: Flight Performance Plot for Ganymede Sizing Case




Moon Landing Mission Description Moon Landing Mission Description ––PD Final: Hover and TouchdownPD Final: Hover and Touchdown

Hover & Soft Landing (h, i, j) Timed hover: Up to 60 s

– T/W = 1.0– (4) or (2) engines operating– Locate and avoid obstacles

Soft landing– 0.75 < T/W < 1.32– Vertical velocity < 1.0 m/s

Abort-to-orbit in all PD phases– Descent stage jettisoned– Ascent engines ignited– Ascent trajectory initiated

Powered Descent Trajectory - T/W and Axial Acceleration vs. Time

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0.50

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T/W

(Non

-Dim

.) or

Acc

eler

atio

n (E

arth

g's

)

TimedHoverPhase

SoftLandingPhase

Axial Acceleration

Vehicle T/W

(h) Hover: T/W = 1.0

(i) Descent: T/W = 0.75 – 1.32

(j) Touchdown: T/W = 1.32

SSD-LM1-v2

Note: Flight Performance Plot for Ganymede Sizing Case




Moon Landing Mission Description Moon Landing Mission Description ––Surface Operations PhaseSurface Operations Phase

Surface Operations (k, l) The LM1 lander provides a

roving habitat for the crew– Up to 1 km/day (30 km total)– Steerable, powered wheels

Biological shielding for crew – Hazardous radiation

environment near Jupiter – Advanced “dual-mode”

composite materials– Shield water layer in AS

cabin filled from DS tanks– Same protection as main

ship Spaceship DiscoveryCrew will spend most of 30 d

mission inside shielded HAB– Brief EVA sorties due to

high radiation environment Fuel cell surface power

– 4.1 kW maximum– 1.0 kW wheel drive motors– 1.0 to 2.0 kW for heaters– 1.0 kW ECS, LSS, GNC,

COM, lighting and HAB– 3.0 kW duty cycle (reactants)– Potential higher endurance

using residual propellants

4 cm H2O Radiation Shield in Cabin Wall

Surface Access Ladder

(k) LM1 Landed Configuration (l) LM1 Side View Cutaway

Cargo Bay

SSD-LM1-v2




Moon Landing Mission Description Moon Landing Mission Description ––Ascent, Rendezvous, and DockingAscent, Rendezvous, and Docking

Ascent to Orbit (m, n, o) LM1 AS launches from DS

– Astronauts leave portable LSS units in airlock

– Launch w/ smaller emergency LSS units

– Shielding water drained from AS cabin into DS storage tks

– Pyrotechnics sever bolts and umbilical connections

– AS engines igniteAscent to 185 km parking orbit

– Same config. as ATO in PDCircularization burn at 185 km

– Up to 5 deg. plane change Rendezvous & Docking (p)

AS maneuvers for correct orbital alignment

Main ship could rescue crew in parking orbit if required

AS performs rendezvous and docking w/ main ship

Crew transfers to main shipAS jettisoned in orbitDeorbit w/ residual propellantsPreparations for next manned

landing or return to earth (p) Rendezvous and Docking(o) Circularization Burn

(n) Ascent to Parking Orbit(m) Liftoff from Descent Stage

SSD-LM1-v2




Ascent Trajectory - Flight Path and Thrust Vector Angles vs. Time

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Elapsed Time From Ignition (s)

Ang

le fr

om H

oriz

onta

l (De

gree

s)

Flight Path Angle

Thrust Vector Angle

Burnout

Moon Landing Mission Description Moon Landing Mission Description ––LM1 Ascent Flight Performance LM1 Ascent Flight Performance

Ascent Trajectory - Altitude vs. Inertial Velocity Components

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150

200

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Velocity (m/s)

Altit

ude

(km

)Horizontal Velocity -

Includes 26.7 m/sEquatorial Rotation

Vertical Velocity

Burnout

Orbital Altitude

Ascent Trajectory - Altitude vs. Acceleration Components

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200

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Altit

ude

(km

)

Horizontal AccelerationVertical Acceleration

Burnout

Orbital Altitude

Ascent to Orbit *

Parking Orbit

- True Anomaly, Launch to Circularization Burn

Launch Point

Orbit Circularization Burn

* Note: Drawing Not to Scale





Key Enabling Technologies Key Enabling Technologies ––LM1 Crew Exploration LanderLM1 Crew Exploration Lander

Reliable Module Launch (a) 25-50 MT subassemblies,

33.0 m length x 8.4 m diameter Robust Orbital Assembly (b)

Autonomous rendezvous and docking of large modules

Zero-g fluid transfer including cryogenic liquids

Dual-Mode Composites (c) Lightweight structuresRadiation shielding capability

Long-Term Cryo Storage (c) Long-term, low-loss storage

systems for cryogenic liquidsDuring orbital assembly, transit,

and on surface of moons Surface Exploration Equip. (d)

Exploration equipment Life support systemsPower generation systemsRugged insulation for extreme

environmentsRugged space suitsAvionics & communicationsScientific equipment

(a) Reliable Module Launch

(d) Surface Exploration Equipment(c) Dual-Mode Composites and Cryo Storage

(b) Robust Orbital Assembly

SSD-LM1-v2




Spaceship Discovery Trans-EarthInjection (TEI) Burn from Ganymede Orbit

LM1 Ascent from Ganymede

Summary Summary –– Spaceship DiscoverySpaceship DiscoveryLM1 Crew Exploration LanderLM1 Crew Exploration Lander

Conclusion: LM1 Crew LanderA proposed solution to land

people on Ganymede & Callisto Flight testable on Earth’s MoonMulti-function vehicle

– Lander– Habitat– Rover

Radiation shielding for crewUp to 30 days enduranceUp to 30 km surface mobilityBased on proven technologies

from Apollo, Shuttle, Altair Layout & structure in common

to LM2/LM3 Mars landers– Reduce development cost

Design for safety / redundancy– Abort-to-orbit during PD– LM1 can be rescued in

parking orbit by main shipDesign for mission success

using multiple LM1 landers– Enables a lander to be used

to rescue another lander– Enables multiple landing

attempts during high value deep space missions SSD-LM1-v2





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Entry Interface Altitude

Backup: LM1 Design Data Backup: LM1 Design Data ––Descent Flight Performance Descent Flight Performance

Powered Descent Trajectory - T/W and Axial Acceleration vs. Time

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arth

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SoftLandingPhase

Axial Acceleration

Vehicle T/W


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Powered Descent Trajectory - Thrust Force vs. Time

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Forc

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Backup: LM1 Design Data Backup: LM1 Design Data ––Dimensions, Masses, & ConsumablesDimensions, Masses, & Consumables

LSS Consumables Ascent Stage

Descent Stage

LM1 Overall

Assumptions (kg/man-day)Breathing Oxygen 1.0 1.0Water 3.0 7.5Dried & Condensed Food 2.0 2.0EnduranceTotal Man-Days 14 60 74Total Days, 2 Crewmembers 7 30 37Consumables Mass (kg)Breathing Oxygen 14 60 74Water 42 450 492Dry Food 28 120 148Add’l. Fuel Cell Reactants 1 232 232Total Consumables 84 862 9461 Additional LH2 and LO2 carried to extend roving range; these could be converted to backup LSS consumables.

Note: MPS & RCS Propellant Masses Shown for Ganymede Sizing Case

Ascent Stage 1

Descent Stage 1

Total for Descent 1

Rescue Ascent 2

Nominal Ascent 3

Dimensions (m)

Length Overall 4.3 5.1 9.4 4.3 4.3

Diameter 7.0 7.5 7.5 7.0 7.0

Mass (kg)Payload 380 500 880 20 125Crew Shielding Water 1,722 1,722(2) PLSS in Airlock 90 90 Crew, Suits, ELSS 240 240 360 240Structure & Insulation 605 1,079 1,684 605 605Propellant & Press. Tanks 344 491 834 344 344Landing Gear 159 159Drive Motors and Wheels 119 119ECLSS, Power, & Avionics 454 525 979 454 454Main Engine 111 266 377 111 111RCS 216 216 216 216Dry Mass Margin (15%) 259 396 655 259 259Life Support Consumables 84 862 946 84 84RCS Propellant (Usable) 432 432 216 216Operating Empty Mass 3,124 6,209 9,333 2,668 2,653Main Propellant (Usable) 3,382 9,250 12,632 3,382 3,382

Total Mass 6,506 15,459 21,965 6,050 6,035Non-Prop/Non-Cons. Mass Frac 0.361 0.320 0.332 0.349 0.3471 Nominal descent: Two crew members, space suits & ELSS units, 500 kg payload.2 Three crew members, space suits & ELSS units, and 20 kg contingency sample.3 Two crew members, space suits & ELSS units, and 125 kg sample payload.4 (Payload + Shielding + Struct./Ins + Eng./Subsys (Incl. Prop. Residuals) / Total Mass

Lander Module 1 (LM1)Descent Ascent




Nominal Descent 1

Rescue Ascent 2

Nominal Descent 1

Rescue Ascent 2

Nominal Descent 1

Rescue Ascent 2

Major Propulsive Burns Deorbit & Descent

Ascent & Circularz

Deorbit & Descent

Ascent & Circularz

Deorbit & Descent

Ascent & Circularz

Req'd. Delta Velocity (km/s)

Orbital Maneuvering 3 0.219 0.313 0.201 0.246 0.195 0.240

Powered Descent or Ascent 1.941 1.876 1.739 1.663 1.706 1.600

Gravity Losses 0.255 0.319 0.201 0.315 0.308 0.431

Flight Perf. Reserve (FPR) 0.034 0.022 0.027 0.019 0.035 0.018

Total 2.450 2.530 2.167 2.242 2.244 2.289Performance ParametersSpecific Impulse (I SP) 448 316 448 316 448 316Mass Ratio (M i / M f ) 1.750 2.268 1.641 2.066 1.670 2.097Burn Propellant Fraction 0.429 0.559 0.391 0.516 0.401 0.523Initial Thrust / Weight 4 2.372 2.315 2.763 2.960 2.163 2.222Final Thrust / Weight 4 4.151 5.250 4.535 6.114 3.611 4.660

Mass (kg)Operating Empty Mass 9,333 2,668 9,286 2,644 9,296 2,649Main Propellant 12,632 3,382 10,334 2,819 10,824 2,906Total Mass 21,965 6,050 19,620 5,463 20,120 5,555

GanymedeLander Module 1 (LM1)

Callisto Moon

Backup: LM1 Design Data Backup: LM1 Design Data ––Descent & Ascent Flight PerformanceDescent & Ascent Flight Performance

1 Nominal descent (2 crew) is sizing case. 2 Rescue ascent (3 crew) is sizing case.3 Includes a plane change of 5.0 degrees during both descent and ascent.4 Referenced to the acceleration of gravity at surface: (1.428 m/s2 Ganymede; 1.237 m/s2 Callisto; 1.620 m/s2 Earth’s Moon).

Documents

Crew Exploration Lander for Ganymede, Callisto, and … training 6-person crew 3.4 day transits 180 days in lunar orbit Three LM1s (for redundancy ... ROV – (Surface) Rover Vehicle