1 / 21

Lunar Lander Vehicle Design Overview

Lunar Lander Vehicle Design Overview. Wayne Lee Lunar Lander Industry Day 13 December 2007. Three Primary Elements Descent module Provides propulsion for LOI and powered descent Provides power during lunar transit, descent, and surface operations

Télécharger la présentation

Lunar Lander Vehicle Design Overview

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript


  1. Lunar Lander Vehicle Design Overview Wayne Lee Lunar Lander Industry Day 13 December 2007

  2. Three Primary Elements Descent module Provides propulsion for LOI and powered descent Provides power during lunar transit, descent, and surface operations Serves as platform for lunar landing and liftoff of ascent module Ascent module Provides propulsion for ascent from lunar surface after surface mission Provides habitable volume for four during descent, surface, and ascent operations Contains cockpit and majority of avionics Airlock Accommodates two astronauts per ingress/egress cycle Connected to ascent module via short tunnel Remains with descent module on lunar surface after ascent module liftoff Vehicle Architecture Airlock Ascent Module Descent Module

  3. Key Preliminary Specifications Number of Crew up to 4 Sortie Mission Duration 14 days LEO (unoccupied) 4 days trans-lunar coast 1 day LLO 7 days surface 7 hours ascent (including disposal) Total Mass at Lift-off 45,000 to 53,600 kg Total Propellant Mass 26,652 kg (sortie) Height of Vehicle Stack 10.52 m, legs uncrushed Height of DM Deck Above Surface 6.97 m, legs uncrushed Maximum Diameter of Vehicle 7.5 m, legs stowed Diameter of Landed Footprint 14.53 m, legs deployed Descent Propulsion LOX/LH2 Main, MMH/NTO RCS Ascent Propulsion MMH/NTO Main and RCS Total V Capability ~2960 m/s

  4. Configuration Variants • Vehicle will be configurable as three different variants • Sortie variant • Utilized for surface missions up to seven days where crew will use ascent module as living quarters and a base of operations for EVAs • Employs all major elements -- descent module, ascent module, airlock • Outpost variant • Utilized for surface missions up to 210 days where crew will work out of a lunar base • Configured similar to sortie variant, but without airlock; crew will depressurize ascent module upon landing and head directly for outpost • Keep-alive power assumed to be provided by outpost • Cargo variant • Utilized to deliver large, presumably outpost modules to the surface • No ascent module or crew; cargo will sit on upper deck of descent module • Vehicle components normally resident in ascent module will be attached to upper deck of descent module

  5. Configuration Variants Sortie Variant 45,000 kg Descent Module Ascent Module Airlock Outpost Variant 45,000 kg Descent Module Ascent Module Cargo Variant 53,600 kg Descent Module Cargo on Upper Deck

  6. Configuration Commonality • Design paradigm is to maximize commonality across variants • Descent module structure optimized to deliver maximum amount of payload mounted to the deck in cargo mode, but use same structure for all three • Descent propulsion is identical for all three with exception of propellant load • Launch mass allocation of 45,000 kg for sortie and outpost variants increased to 53,600 kg for cargo mission due to benefit of Ares V not needing to accelerate Orion vehicle through TLI burn • Tanks sized for propellant volume needed for 53,600 kg cargo mission, but only filled to level needed to support sortie and outpost variant mass • Ascent module structure and propulsion is identical for sortie and outpost variants • Other subsystems are identical in concept for all three variants • Choice of components and sizing are the same for all three variants • Minor variations in schematics and physical layout to account for mission-specific details

  7. Mass Distribution Comparison of Variants Outpost Mission Lander Uncrewed Cargo Mission Lander Sortie Mission Lander

  8. Descent Module Structure Cruciform truss configuration, four landing legs (stowed at launch) Aluminum construction Current mass w/o growth 2110 kg Ascent Module Structure Cylindrical-shaped pressure vessel Composite construction Current mass w/o growth 625 kg Airlock Structure Cylindrical-shaped pressure vessel Aluminum construction Current mass w/o growth 312 kg Structures Summary Ascent Module Airlock Landing Leg Launch Vehicle Adaptor (EDS)

  9. Descent Module Configuration Cruciform Primary Structure LH2 Tanks (4) LOX Tanks (4) Upper LH2 Support Struts (32) (tension rods) Lower LH2 Support Struts (16) (stabilizers) Lower LOX Tank Support Cones (4)

  10. Ascent Module Configuration Docking WindowFrame (2) LIDS Docking Adaptor (previous version shown) Top Flange (4) Front WindowFrame (2) MMH Tank (2) Tank Structure (24 struts) NTO Tank (2) Lower Interface Beam Separation System (Marmon Band) AM/DM Adapter Engine

  11. Airlock Configuration Pressure Shell Skin EVA Hatch Frame EVA Hatch Window AM / Airlock Tunnel Frame EVA Hatch AM / Airlock Tunnel Bottom Flange (4) Truss Structure Strut (8)

  12. Ascent Module Propulsion Single MMH/NTO main engine, 24,465 N (5,500 lbf) thrust 16 MMH/NTO RCS thrusters 2 MMH, 2 NTO tanks shared between main and thrusters Current dry mass w/o growth 666 kg Descent Module Propulsion Single LOX/LH2 main, 82787 N (18,627 lbf) thrust, restart capability, 3.3:1 throttle ratio 4 LOX, 4 LH2 tanks 16 MMH/NTO RCS thrusters Current dry mass w/o growth 2510 kg Propulsion Summary Thrusters (position TBD) MMH Tank NTO Tank Helium Tank Ascent Main Engine LH2 Tank LOX Tank Descent Main Engine

  13. VR VR VR VR VR VR VR VR VR s s s s s s s s s s s s s s LH2-2 LH2-3 LH2-4 LH2-1 GHe GHe GHe GHe TVS TVS TVS TVS TIVF1-P TIVF2-P TIVF3-P TIVF4-P TIVF1 TIVF2 TIVF3 TIVF4 P P P P P P P P P P P Engine #1 DM Main Propulsion Schematic Pneumatics/Purge Pneumatic Valve Pneumatic Vent/Relief Valve Power System Interface Relief Valve Press/Pre-press Solenoid Valve Check Valve GHe Fill/Vent Pressure Regulator Filter Thermodynamic Vent System TVS LOX Vent Diffuser LH2 Vent LOX Fill/Drain LH2 Fill/Drain LOX-2 LOX-3 LOX-4 LOX-1 TVS TVS TVS TVS TIVOx1-P TIVOx2-P TIVOx3-P TIVOx4-P TVCA-1a TIVOx1 TIVOx2 TIVOx3 TIVOx4 TVCA-1b

  14. GHe GHe GHe GHe p3 p6 p4 p5 p1 p2 S S S S S S S S Ascent Propulsion Schematic tHe1 Function: Service Hand Valve, HV High Pressure Latching Valve, HP Regulator, Rg Check Valve, CV Filter, F Low Pressure Latching Valve, LV Solenoid Valve S Burst Disk/ Relief Valve RV Heater Ht Pressure Sensor P Temperature Sensor T Fluids: Helium He Nitrogen Tetroxide (NTO) Ox Monomeythhydrazine (MMH) Fu tHe2 tHe1 tHe2 HVHe01 pHe1 HPHe1 FHe1 RgHe1 FHe5 FHe6 HVOx1 HVFu01 CVHe2 Thruster 5,6,7,8 CVHe1 Thruster 1,2,3,4 LVOx1 LVFu1 RVFu1 RVOx2 pp1 S S S S S S S S pp2 t16 t14 t15 t13 t12 t10 t11 t9 tp5 tp1 tp7 t5 tp3 HVFu4 MMH MMH NTO NTO HVOx4 t6 tp6 tp2 tp8 tp4 t3 t4 HVFu2 HVOx2 RCS Thruster Quads LVFu2 LVOx2 FFu1 FOx1 HVOx3 t1 HVOx5 t7 t2 HVFu5 t8 HVFu3 t20 t21 t24 t18 t19 t23 t22 t17 S S S S S S S S Ascent Engine Thruster 13, 14, 15, 16 Thruster 9,10,11,12

  15. Descent Module PEM fuel cell, 5.5 kW peak production Provides AM and DM power for LLO, surface operations Orion provides 1.5 kW when docked Propulsion residuals provide reactants for surface operations Current inert mass w/o growth 148 kg (sortie) Ascent Module and Airlock Single primary battery, LiSO2 chemistry, 14.2 kW-hr capacity Current mass w/o growth 139 kg Bus 28 V unregulated bus Power Summary

  16. Ascent Module and Airlock Inner loop with coldplates and sublimator Heat transferred to outer loop for rejection during cruise, LLO, surface MLI and black Kapton insulation on structure Current inert mass w/o growth 208 kg Descent Module Outer loop utilizes radiators for heat rejection SOFI insulation on propellant tanks, silverized teflon and MLI on structure Current inert mass w/o growth 974 kg (sortie), 990 kg (cargo) Thermal Summary Sublimator (attached to AM) Radiator (another on other side)

  17. Atmosphere Between 57 and 83 kPa Cabin loop provides for heat removal Suit loop provides for CO2, moisture, heat removal from suit umbilicals Suit loop also removes CO2 from cabin air via amine swing beds Water Internal tank holds one day of potable water with silver ion biocide External tank accumulates water from fuel cells for internal tank, EVA recharge, and thermal Waste Collection and disposal provided Current mass w/o growth 212 kg (sortie) Life Support Summary Ascent Module Components Airlock Components

  18. C&DH Design Status • Project strategy regarding C&DH has been not to instantiate a baseline design using available components • Over 10+ years to go until first flight • Relatively rapid progress in evolution of electronics may render today’s design obsolete • Baseline C&DH architecture is currently under study by a multi-NASA-center team with the following objectives • Determine functional properties of architectures that have favorable characteristics relative to Lander performance requirements • Develop candidate architectural concepts that satisfy the desired characteristics, but are expandable and extensible • Identify technology and/or component families suitable for use in populating the architecture • Develop a functional/mass equivalent design placeholder using existing parts, if available

  19. Sensor Suite Star tracker and MIMU data for propagation of attitude and position for all phases of flight Pulsed Doppler radar provides altitude and velocity during landing Lidar provides range and bearing to Orion during rendezvous Rendezvous camera used during terminal approach prior to docking Control Suite 16 thrusters on DM allows for attitude control during cruise, LLO, descent DM main engine gimbals by 6° to keep thrust aligned with c.g. 16 thrusters on AM allows for attitude control and main engine thrust vector pointing during ascent GN&C Summary Lidar and Camera (top front of AM) MIMU (inside AM) Star Tracker DM RCS Thruster Pod Radar Electronics (inside DM) Radar Antennas (not shown, mounted on lower edge of DM)

  20. Primary Radio S-band transponder for link with Orion and Earth SSPA with 40 W output power 2 ISS-heritage low-gain antennas with 120° field of view Link Performance 80 kbps to 18-m Earth network, 190 kbps to 34-m network 2.3 Mbps to Orion at 100 km range Significant fraction of data volume in minimal functional design occupied by overhead (headers, IP, etc.) EVA Radio 802.16 transceiver currently in development Telecom Summary SSPA (top face of AM) Low-Gain Primary Antennas

  21. Summary • Vehicle design shown today is from the first design cycle (LDAC-1) • Minimum functional design; not intended for flight • Design basis was the design reference mission as opposed to a detailed requirements set • Implementation choices should not be considered frozen with the exception of a few key architectural features • 4 crew, descent propellant, inclusion of an airlock, use of LIDS docking adaptor for Orion • Forward work for FY08 • Evaluate upgrades for safety and reliability • Evaluate upgrades for lunar global access and enhanced functionality • Mature preliminary design and develop requirement sets and specifications • Evaluate technologies for mass reduction

More Related