Crew Exploration Lander for Ganymede, Callisto, and Earth s s Moon - Vehicle System Design (AIAA-2009

Transcription

1 Crew Exploration Lander for Ganymede, Callisto, and Earth s s Moon - Vehicle System Design (AIAA ), The Boeing Company AIAA 29 Joint Propulsion Conference August 3-5, 29, Denver, Colorado Slide Spaceship 1 of 18 Discovery Slides Slide 1 of 18 Slides 29 All Rights Mark G. Reserved Benton, Sr. AIAA 29 Joint Propulsion 8/3/29 Conference 1:53 PM

2 Spaceship Discovery Architecture for Human Solar System Exploration Spaceship Discovery Conceptual vehicle architecture Modular spacecraft, assembled in Earth parking orbit Number of drop tanks tailored to mission V requirements Bi-modal NTR engines High Isp propulsion (95 s) High elec. power (2 kw) Crew protective systems Artificial gravity Radiation shielding High degree of redundancy Design Reference Missions * DRM 1: Moon DRMs 2 / 3: Mars DRMs 5 / 6: Callisto / Ganymede Launch, Assembly, Departure Modular 5 MT subassemblies (33. m L x 8.4 m dia.) launched Assembled in 556 km (3 nmi) altitude, circular Earth orbit Systems checked out and propellant tanks topped off Mission crew arrives Escape to solar transfer ellipse Engineering Module (EM) Deployable Solar / Thermal Shade Closed Brayton Cycle (CBC) Electrical Gen. System (3 places) Bimodal Nuclear Thermal Rocket (NTR) Engine (3 pl) Main LH 2 Propellant Core Tank (CT) (4 pl) Very Low Boil off System (VLBOS) (Cryo. Retention) Abort Propulsion System (APS) Main Engine * Note: DRM 4 exploration mission to asteroid Ceres reserved for future work Main LH 2 Propellant Drop Tank (DT) (12 pl) Side View Main Ship Artificial Gravity (AG) Centrifuge Galactic Cosmic Ray (GCR) & Solar Particle Event (SPE) Biological Shield (LH 2 & H 2 O) Side View Cutaway Key Features 5-Port Docking Module (DM) Service Module (SM) Gimbaled High Gain Antenna Crew Module (CM) Ganymede, Callisto, Earth s Moon Lander Module LM1 (DRMs 1, 5, 6) Mars Lander Modules LM2, LM3 (DRMs 2, 3) Reentry Module (RM) Slide 2 of 18 Slides

3 Spaceship Discovery Details of DRMs 1, 5, and 6 Exploration Missions DRM 1 Earth s Moon Flight test SSD Flight test LM1 landers Crew training 6-person crew 3.4 day transits 18 days in lunar orbit Three LM1s (for redundancy) 3 day duration per lander DRM 5 Callisto Four person crew Four year total duration One year, 9 month transits 183 day wait time at Jupiter Capture into 185 km circular Callisto parking orbit Three LM1s (for redundancy) 3 day duration per lander DRM 6 Ganymede Crew, duration, transits, wait time at Jupiter same as DRM 5 Capture into 185 km circular Ganymede parking orbit Three LM1s (for redundancy) a. DRMs 5 or 6 Assembly in Earth Parking Orbit in Preparation for Trans-Jupiter Injection b. DRMs 5 or 6 Outbound Transit to Jovian System and Insertion into Callisto or Ganymede Orbit c. DRMs 5 or 6 In Orbit around Callisto or Ganymede, Ready for Landing Missions DRM 1 Trans-Lunar Injection, Outbound Transit, Lunar Orbit Insertion, and Ready for Landing Missions Slide 3 of 18 Slides d. DRMs 5 or 6 Trans-Earth Injection, Inbound Transit, and Earth Trajectory Injection DRM 1 Trans-Earth Injection, Inbound Transit, and Earth Orbit Insertion

4 LM1 Design Requirements and Mission Flight Performance Powered Initiation (PDI) Point Transfer Burn - True Anomaly, Launch to Circularization Burn Launch Point to Surface * Temperature Ranges (C): Ganymede -179 to -13 Callisto -196 to -116 Moon -18 to +13 Ascent to Orbit * -True Anomaly, PDI to Landing Landing Point Transfer Orbit Orbit Circularization Burn Parking Orbit * Note: Drawings Not to Scale Target Planetary Body Ganymede Callisto Moon Planetary Parameters Radius at Surface (km) 2,631 2,41 1,738 Equatorial Rotation (m/s) Gravitational Parameter (km 3 /s 2 ) 9,887 7,179 4,93 Gravity at Surface (m/s 2 ) Circ. Parking Orbit Parameters Parking Orbit Radius (km) 2,816 2,596 1,923 Parking Orbit Altitude (km) Orbital Velocity (m/s) 1,874 1,663 1,597 Parameters V for Transfer Burn 1 (m/s) Periapsis Altitude (PDI) (km) Inertial Velocity at PDI (m/s) 1,968 1,749 1,711 Relative Velocity at PDI (m/s) 1,941 1,739 1,76 True Anomaly at Landing (deg) Ascent Parameters Relative Vel. at Burnout (m/s) 1,938 1,77 1,628 Rel. Vel. at 185 km Alt. (m/s) 1,876 1,663 1,6 V for Circulariz. Burn 2 (m/s) Ascent True Anomaly (deg) Includes 25 m/s maneuvering, 5 degree decent plane change, and 1% flight performance reserve. 2 Includes 1 m/s maneuvering, 5 deg. ascent plane change, launch from +3 degree inclination, and 1% flight performance reserve. Slide 4 of 18 Slides

5 LM1 Design Data Configuration Elevation Views Abbreviations and Acronyms AS Ascent Stage BSW Biological Shield Water COM Communications Equip. DS Stage ECS Equipment Cooling Sys. FAE Fixed Ascent Engine FDK Flight Deck GDE Gimballed Eng. GNC Guidance, Nav., Control HAB Crew Habitat LGR Landing Gear LSS Life Support System ME Main Engine MMH Mono-Methyl Hydrazine MPS Main Propulsion System NTO Nitrogen Tetroxide OML Outer Moldline PRP Propellant PRS Pressurization RCS Reaction Control System ROV (Surface) Rover Vehicle RTQ RCS Thruster Quad SCR Supercritical VDM Vehicle Drive Motor VDW Vehicle Drive Wheel Slide 5 of 18 Slides FDK & HAB Crew Cabin Tunnel to Air Lock in DS DS Air Lock AS RCS NTO Tk. (4 pl) AS RCS MMH Tk. (4 pl) Fuel Cell (4 pl) Reflective Thermal Foil Side View Cutaway Front View Cutaway AS ECS/LSS Bay DS MPS LO 2 Tank LSS SCR LO 2 Tk. ECS/LSS H 2 O Tk. AS FAE (8 pl) DS Cargo Bay AS MPS NTO Tk. AS MPS MMH Tk. DS Fuel Cell /LSS SCR LH 2 Tks. DS Fuel Cell /LSS SCR LO 2 Tks. GDE (8 pl) DS MPS LH 2 Tank DS BSW Tanks (8 pl) Independent Suspension VDM & VDW (8 pl) 45-Deg. Cutaway (LGR Stowed) 45-Deg. Cutaway (LGR Depl.) SSD-LM1-v2 Deploy w/ Pyros, Spring & Gravity Assist DS MPS & BSW PRS Tks (4 pl) DS MPS LO 2 Tank DS Thrust Cylinder Structure Pri. Struc. +.6 m Stroke, & +.6 m Leveling Strut

6 LM1 Design Data Configuration Cross Section Views Design Features Two-way trans: orbit surface Abort to orbit during descent Single engine-out redundancy FDK, HAB, ROV functionality Radiation shielding for HAB Insulation for extreme temps Crew: Payload: 2 (3 for rescue) 5 / 125 kg (DS/AS) Endurance:3 / 7 d (DS/AS) LM1 Total Masses MT (Ganymede) MT (Callisto) 2.12 MT (Earth s Moon) Section (DS) LH 2 LO 2 MPS propellants (8) gimballed, 12.2 kn main eng. (throttleable 1% - 3%) Power: LH 2 / LO 2 fuel cells Airlock and cargo bay Ascent Section (AS) MMH NTO MPS propellants (8) fixed 3.3 kn main eng. MMH NTO RCS propellants Power: Solar Arrays / Batts. Crew HAB Incl. Sleep, Food Prep., & Hygiene Facilities Crew Bunk FDK w/ (2) Large Windows RTQ (4 pl) DS RCS NTO Tk. (4 pl) RCS PRS Tank Tunnel to Airlock in DS Batteries AS Upper Level AS Lower Level LSS SCR LO 2 Tanks MPS and RCS Tank Bay Tunnel to Airlock in DS LSS H 2 O Tks DS MPS NTO Tk. MPS PRS Tank (4 pl) DS MPS MMH Tk. DS RCS MMH Tk. FAE (8 pl) GNC & COM Bay DS Surface Access Door Pair DS MPS LH 2 Tank Insulated Fuel Cell Bay DS BSW Tanks (8 pl) Fuel Cell (4 pl) GDE (8 pl) Airlock in DS DS Upper Level (LGR Stowed) Cargo Bay DS Lower Level (LGR Depl.) Cargo Bay SSD-LM1-v2 DS Fuel Cell/ LSS SCR LH 2 Tank DS-AS Pyro Sep. Bolts (6 pl) Fuel Cell / LSS SCR LO 2 Tks. DS MPS & BSW PRS Tks (4 pl) Air Lock Slide 6 of 18 Slides

7 Moon Landing Mission Description Launch, Assembly, Transit, & Deorbit Launch and Assembly (a, b) Modular Spaceship Discovery design: Assembly in LEO Modules launched into 556 km (3 nmi) assembly orbit Assembly completed during approximately one year Max. launch dimensions: 33. m long x 8.4 m dia. Max. mass 5 MT incl. fairing & airborne support equip. (2) MT LM1 landers launched simultaneously Outbound Transit and Landing Preparations (c) (3) landers docked to Spaceship Discovery docking module Hibernation mode during transit LM1s cryo. tanks cooled by Spaceship Discovery VLBOS Capture into moon parking orbit Start of Landing Mission (d) Crew enters LM1 lander Lander undocks in moon orbit Landing gear extends & locks Deorbit burn injects vehicle into descent transfer orbit Slide 7 of 18 Slides SSD-LM1-v2 (a) Launch Configuration (c) In Transit (b) Orbital Assembly (d) Deorbit Burn

8 Moon Landing Mission Description Powered (PD) Flt. Performance Powered Initiation (PDI) Point -True Anomaly, PDI to Landing Powered Trajectory - Axial Velocity vs. Altitude 2 Landing Point Entry Interface Altitude Altitude (km) Transfer Burn to Surface * Transfer Orbit * Note: Drawing Not to Scale 1,8 1,6 1,4 1,2 1, Note: Flight Performance Plots Shown for Ganymede Sizing Case Velocity (m/s) Powered Trajectory - Altitude vs. Downrange Displacement Powered Trajectory - Axial Velocity vs. Altitude 1.5 1, Altitude (km) Altitude (m) 1 m Hover Altitude 1 m Hover Altitude Downrange Displacement from Entry Interface (km) Velocity (m/s) Slide 8 of 18 Slides

9 Moon Landing Mission Description Powered at Constant T/W Constant T/W Phase (e, f, g) Powered Initiation (PDI) at periapsis of descent xfer orbit T/W = 2.5 Minimize gravity losses Constant crew decel. (.36 g) Robust excess thrust Pitch program controls thrust vector angle and descent rate Single engine-out during PD (8) for (6) engine redundancy (a) Powered descent Initiation (PDI) Note: Flight Performance Plot for Ganymede Sizing Case SSD-LM1-v2 Powered Trajectory - Flight Path and Thrust Vector Angles vs. Time Thrust Vector or Flight Path Angle (Deg.) Flight Path Angle Thrust Vector Angle Timed Hover Phase Soft Landing Phase (b) Pitch Program Time From Entry Interface (s) (c) Vertical Slide 9 of 18 Slides

10 Hover & Soft Landing (h, i, j) Timed hover: Up to 6 s T/W = 1. (4) or (2) engines operating Locate and avoid obstacles Soft landing.75 < T/W < 1.32 Vertical velocity < 1. m/s Abort-to-orbit in all PD phases stage jettisoned Ascent engines ignited Ascent trajectory initiated Moon Landing Mission Description PD Final: Hover and Touchdown SSD-LM1-v2 (h) Hover: T/W = 1. Note: Flight Performance Plot for Ganymede Sizing Case Powered Trajectory - T/W and Axial Acceleration vs. Time T/W (Non-Dim.) or Acceleration (Earth g's) Vehicle T/W Axial Acceleration Timed Hover Phase Soft Landing Phase (i) : T/W = Time From Entry Interface (s) (j) Touchdown: T/W = 1.32 Slide 1 of 18 Slides

11 Moon Landing Mission Description Surface Operations Phase Surface Operations (k, l) SSD-LM1-v2 The LM1 lander provides a roving habitat for the crew Up to 1 km/day (3 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 Discovery Crew will spend most of 3 d mission inside shielded HAB Brief EVA sorties due to high radiation environment Fuel cell surface power 4.1 kw maximum 1. kw wheel drive motors 1. to 2. kw for heaters 1. kw ECS, LSS, GNC, COM, lighting and HAB 3. kw duty cycle (reactants) Potential higher endurance using residual propellants Surface Access Ladder (k) LM1 Landed Configuration (l) LM1 Side View Cutaway 4 cm H 2 O Radiation Shield in Cabin Wall Cargo Bay Slide 11 of 18 Slides

12 Moon Landing Mission Description Ascent, 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 ignite Ascent to 185 km parking orbit Same config. as ATO in PD Circularization 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 ship AS jettisoned in orbit Deorbit w/ residual propellants Preparations for next manned landing or return to earth Slide 12 of 18 Slides SSD-LM1-v2 (m) Liftoff from Stage (o) Circularization Burn (n) Ascent to Parking Orbit (p) Rendezvous and Docking

13 Moon Landing Mission Description LM1 Ascent Flight Performance - True Anomaly, Launch to Circularization Burn Orbit Circularization Burn Ascent Trajectory - Altitude vs. Acceleration Components 2 Orbital Altitude 15 Launch Point Ascent to Orbit * Parking Orbit Ascent Trajectory - Flight Path and Thrust Vector Angles vs. Time * Note: Drawing Not to Scale Note: Flight Performance Plots Shown for Ganymede Sizing Case Altitude (km) 1 Burnout Vertical Acceleration 5 Horizontal Acceleration Acceleration (m/s 2 ) Ascent Trajectory - Altitude vs. Inertial Velocity Components 9 8 Burnout 2 Orbital Altitude Angle from Horizontal (Degrees) Thrust Vector Angle Flight Path Angle Altitude (km) Vertical Velocity Burnout Horizontal Velocity - Includes 26.7 m/s Equatorial Rotation Elapsed Time From Ignition (s) 5 1, 1,5 2, 2,5 Velocity (m/s) Slide 13 of 18 Slides

14 Key Enabling Technologies LM1 Crew Exploration Lander Reliable Module Launch (a) 25-5 MT subassemblies, 33. 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 structures Radiation shielding capability Long-Term Cryo Storage (c) Long-term, low-loss storage systems for cryogenic liquids During orbital assembly, transit, and on surface of moons Surface Exploration Equip. (d) Exploration equipment Life support systems Power generation systems Rugged insulation for extreme environments Rugged space suits Avionics & communications Scientific equipment SSD-LM1-v2 (a) Reliable Module Launch (b) Robust Orbital Assembly Slide 14 of 18 Slides (c) Dual-Mode Composites and Cryo Storage (d) Surface Exploration Equipment

15 Summary Spaceship Discovery LM1 Crew Exploration Lander Conclusion: LM1 Crew Lander A proposed solution to land people on Ganymede & Callisto Flight testable on Earth s Moon Multi-function vehicle Lander Habitat Rover Radiation shielding for crew Up to 3 days endurance Up to 3 km surface mobility Based 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 ship Design 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 LM1 Ascent from Ganymede Spaceship Discovery Trans-Earth Injection (TEI) Burn from Ganymede Orbit SSD-LM1-v2 Slide 15 of 18 Slides

16 Backup: LM1 Design Data Flight Performance Note: Flight Performance Plots Shown for Ganymede Sizing Case Powered Trajectory - Altitude vs. Downrange Displacement Powered Trajectory - Thrust Force vs. Time Entry Interface Altitude 8 Timed Hover Phase Altitude (km) 12 8 Force (kn) 6 4 Soft Landing Phase Downrange Displacement from Entry Interface (km) Time From Entry Interface (s) Powered Trajectory - Altitude vs. Downrange Displacement Powered Trajectory - T/W and Axial Acceleration vs. Time Altitude (km) Downrange Displacement from Entry Interface (km) T/W (Non-Dim.) or Acceleration (Earth g's) Vehicle T/W Axial Acceleration Timed Hover Phase Soft Landing Phase Time From Entry Interface (s) Slide 16 of 18 Slides

17 Backup: LM1 Design Data Dimensions, Masses, & Consumables Lander Module 1 (LM1) Ascent Stage 1 Stage 1 Total for 1 Rescue Ascent 2 Ascent Nominal Ascent 3 Dimensions (m) Length Overall Diameter Mass (kg) Payload Crew Shielding Water 1,722 1,722 (2) PLSS in Airlock 9 9 Crew, Suits, ELSS Structure & Insulation 65 1,79 1, Propellant & Press. Tanks Landing Gear Drive Motors and Wheels ECLSS, Power, & Avionics Main Engine RCS Dry Mass Margin (15%) Life Support Consumables RCS Propellant (Usable) Operating Empty Mass 3,124 6,29 9,333 2,668 2,653 Main Propellant (Usable) 3,382 9,25 12,632 3,382 3,382 Total Mass 6,56 15,459 21,965 6,5 6,35 Non-Prop/Non-Cons. Mass Frac Nominal descent: Two crew members, space suits & ELSS units, 5 kg payload. LSS Consumables Ascent Stage Stage LM1 Overall Assumptions (kg/man-day) Breathing Oxygen Water Dried & Condensed Food Endurance Total Man-Days Total Days, 2 Crewmembers Consumables Mass (kg) Breathing Oxygen Water Dry Food Add l. Fuel Cell Reactants Total Consumables Additional LH 2 and LO 2 carried to extend roving range; these could be converted to backup LSS consumables. 2 Three crew members, space suits & ELSS units, and 2 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 Note: MPS & RCS Propellant Masses Shown for Ganymede Sizing Case Slide 17 of 18 Slides

18 Backup: LM1 Design Data & Ascent Flight Performance Lander Module 1 (LM1) Major Propulsive Burns Ganymede Nominal 1 Deorbit & Rescue Ascent 2 Ascent & Circularz Nominal 1 Deorbit & Callisto Rescue Ascent 2 Ascent & Circularz Nominal 1 Deorbit & Moon Rescue Ascent 2 Ascent & Circularz Req'd. Delta Velocity (km/s) Orbital Maneuvering Powered or Ascent Gravity Losses Flight Perf. Reserve (FPR) Total Performance Parameters Specific Impulse (I SP ) Mass Ratio (M i / M f ) Burn Propellant Fraction Initial Thrust / Weight Final Thrust / Weight Mass (kg) Operating Empty Mass 9,333 2,668 9,286 2,644 9,296 2,649 Main Propellant 12,632 3,382 1,334 2,819 1,824 2,96 Total Mass 21,965 6,5 19,62 5,463 2,12 5,555 1 Nominal descent (2 crew) is sizing case. 2 Rescue ascent (3 crew) is sizing case. 3 Includes a plane change of 5. degrees during both descent and ascent. 4 Referenced to the acceleration of gravity at surface: (1.428 m/s 2 Ganymede; m/s 2 Callisto; 1.62 m/s 2 Earth s Moon). Slide 18 of 18 Slides