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Reusable lunar lander

The document proposes a reusable lunar lander concept that would reduce costs by reusing the lander for crew rotations rather than abandoning it after each mission. Key elements include a propellant transfer module to provide fuel for lunar orbit insertion and resupply, and deployable lunar outpost modules that can be transported and stored in the lander. The initial flight would use the lander to perform lunar orbit insertion and deploy the first outpost module. Subsequent flights would use the propellant transfer module for orbit insertion while transporting additional outpost modules. The document provides details on the proposed lander design including mass estimates and equipment.

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Reusable Lunar Lander JSC-MOD/M. Interbartolo
Agenda • Introduction • Mass Allocations and Equipment List • Lander Schematics • Flight One and Two Sequence • Lunar Outpost Assembly Sequence and Crew Rotation • Conclusion
Introduction: Reusable Lander Concept
Concept • Instead of abandoning the Lunar Lander after ascent each flight reuse for crew change out. • Requires several development components. – Propellant Transfer Module • Provides Delta V to CEV for LOI since LSAM is no longer part of TLI stack • Provides Delta V to resupply Lander for descent and ascent • Provides Consumables to CEV and Lander – Lunar outpost modules that can be stowed in Lander • Based off Single Stage, Dual Hab design – concept #2 Lunar Surface Access Module Study, RFT0020.05JSC
Phased In approach • First flight consists of CEV and Lander – Lander performs LOI – Lander deploys first Outpost Module via attached Flat Bed Transport • Second and subsequent flights consist of CEV, PTM and Outpost Modules/Resupplies – CEV performs LOI with prop from PTM
Lander
Mass Allocations: Equipment List
Mass Allocations • Lander: 99,000 lb – Includes 10,000 outpost module capacity • CEV: 50,000 lb • PTM: 89,000 lb – Prop for CEV to perform LOI – Prop for Lander Descent and Ascent Resupply – Consumables for Lander • N2/O2 for cabin represses, Suit cooling H2O • Outpost Module #X: 10,000 lb max
Propellant Mass Estimates (FWD)Lander Total 99000 Gc = 32.174 ft/s^2 Propellant Temp/Press Density (lbm/ft^3) MR AR [6] Rho_avg (lbm/ft^3) Thrust (lbf) ISP CEV Mass (Wi) (lbm) DV (fps) Useable Prop [1] (%) Margin [1] [2] (%) Ullage [3] (%) LO2 (OMS) 162R / 250 psia 62.11 32310.0 5.3 CH4 (OMS) 170R / 250 psia 23.22 9502.9 5.3 LO2 (RCS) 162R / 250 psia 62.11 0.0 5.3 CH4 (RCS) 170R / 250 psia 23.22 0.0 5.3 Total Propellant Weight 41812.9 4 tanks per propellant Total Tank Weight 1615.4 8.31 [ft] NTO tank Length Total Prop plus Tank Weight 43428.3 6.82 [ft] MMH tank length LANDER PERFORMING LOI Total Helium Weight 1313.4 1 tanks per propellant Total Helium Tank Weight 1643.2 5.82 [ft] NTO He tank diameter Total Helium plus Tank Wt 2956.5 5.37 [ft] MMH He tank diameter Total He, Prop, & Tank Wt 46384.8 Lander Wet Mass Post LOI 55873.7 Gc = 32.174 ft/s^2 Propellant Temp/Press Density (lbm/ft^3) MR AR [6] Rho_avg (lbm/ft^3) Thrust (lbf) ISP CEV Mass (Wi) (lbm) DV (fps) Useable Prop [1] (%) Margin [1] [2] (%) Ullage [3] (%) LO2 (OMS) 162R / 250 psia 62.11 18807.9 5.3 CH4 (OMS) 170R / 250 psia 23.22 5531.7 5.3 LO2 (RCS) 162R / 250 psia 62.11 0.0 5.3 CH4 (RCS) 170R / 250 psia 23.22 0.0 5.3 Total Propellant Weight 24339.7 2 tanks per propellant Total Tank Weight 912.2 9.45 [ft] NTO tank Length Total Prop plus Tank Weight 25251.9 7.72 [ft] MMH tank length LANDER PERFORMING DESCENT Total Helium Weight 764.5 1 tanks per propellant Total Helium Tank Weight 1152.0 4.86 [ft] NTO He tank diameter Total Helium plus Tank Wt 1916.5 4.48 [ft] MMH He tank diameter Total He, Prop, & Tank Wt 27168.4 Lander Wet Mass Post Landing 20769.5 and post Module Deploy 10000 Gc = 32.174 ft/s^2 Propellant Temp/Press Density (lbm/ft^3) MR AR [6] Rho_avg (lbm/ft^3) Thrust (lbf) ISP CEV Mass (Wi) (lbm) DV (fps) Useable Prop [1] (%) Margin [1] [2] (%) Ullage [3] (%) LO2 (OMS) 162R / 250 psia 62.11 6991.3 5.3 CH4 (OMS) 170R / 250 psia 23.22 2056.3 5.3 LO2 (RCS) 162R / 250 psia 62.11 0.0 5.3 CH4 (RCS) 170R / 250 psia 23.22 0.0 5.3 Total Propellant Weight 9047.6 1 tanks per propellant Total Tank Weight 361.1 7.37 [ft] NTO tank Length Total Prop plus Tank Weight 9408.7 6.08 [ft] MMH tank length LANDER PERFORMING ASCENT Total Helium Weight 284.2 1 tanks per propellant Total Helium Tank Weight 603.5 3.49 [ft] NTO He tank diameter Total Helium plus Tank Wt 887.6 3.22 [ft] MMH He tank diameter Total He, Prop, & Tank Wt 10296.3 Lander Dry Mass (excludes Prop tanks) 5150.5 LO2 and Methane Wp (lbm) 3.4 150 44.99 900 362 149000 3600 98.0% 3.5% 41812.9 3.2 60 44.40 100 345 149000 0 100.0% 3.5% 0.0 LO2 and Methane Wp (lbm) 3.4 150 44.99 900 362 55873.7 6200 98.0% 3.5% 24339.7 3.2 60 44.40 100 345 55873.7 0 100.0% 3.5% 0.0 LO2 and Methane Wp (lbm) 3.4 150 44.99 900 362 20769.5 6200 98.0% 345 20769.5 0 100.0%3.2 60 44.40 100 3.5% 0.0 3.5% 9047.6 If estimates are correct only 5150 lb for all Lander systems except prop wet mass
Propellant Mass Estimates (Back) Gc = 32.174 ft/s^2 Propellant Temp/Press Density (lbm/ft^3) MR AR [6] Rho_avg (lbm/ft^3) Thrust (lbf) ISP CEV Mass (Wf) (lbm) DV (fps) Useable Prop [1] (%) Margin [1] [2] (%) Ullage [3] (%) Volume (FT3) LO2 (OMS)162R / 250 psia 62.11 10982.7 5.3 186.20 CH4 (OMS)170R / 250 psia 23.22 3230.2 5.3 146.49 LO2 (RCS)162R / 250 psia 62.11 0.0 5.3 0.00 CH4 (RCS)170R / 250 psia 23.22 0.0 5.3 0.00 Total Propellant Weight 14212.9 3 tanks per propellant Total Tank Weight 3819.2 27.36 [ft] NTO tank Length Total Prop plus Tank Weight 18032.2 21.81 [ft] MMH tank length Lander Performs Ascent Lander RNDZ Burnout weight 20,000 Total Helium Weight 1225.2 1 tanks per propellant Lander pre Ascent 35,438 Total Helium Tank Weight 1569.8 5.68 [ft] NTO He tank diameter Total Helium plus Tank Wt 2795.1 5.25 [ft] MMH He tank diameter Total He, Prop, & Tank Wt 20827.2 Gc = 32.174 ft/s^2 Propellant Temp/Press Density (lbm/ft^3) MR AR [6] Rho_avg (lbm/ft^3) Thrust (lbf) ISP CEV Mass (Wf) (lbm) DV (fps) Useable Prop [1] (%) Margin [1] [2] (%) Ullage [3] (%) Volume (FT3) LO2 (OMS)162R / 250 psia 62.11 24951.6 5.3 423.02 CH4 (OMS)170R / 250 psia 23.22 7338.7 5.3 332.80 LO2 (RCS)162R / 250 psia 62.11 0.0 5.3 0.00 CH4 (RCS)170R / 250 psia 23.22 0.0 5.3 0.00 Total Propellant Weight 32290.3 3 tanks per propellant Total Tank Weight 3819.2 27.36 [ft] NTO tank Length Lander Performs Descent Total Prop plus Tank Weight 36109.6 21.81 [ft] MMH tank length Lander Payload 10,000 Lander Touchdown weight 45,438 Total Helium Weight 1225.2 1 tanks per propellant Lander pre Deorbit Burn 78,954 Total Helium Tank Weight 1569.8 5.68 [ft] NTO He tank diameter Total Helium plus Tank Wt 2795.1 5.25 [ft] MMH He tank diameter Total He, Prop, & Tank Wt 38904.6 Gc = 32.174 ft/s^2 Propellant Temp/Press Density (lbm/ft^3) MR AR [6] Rho_avg (lbm/ft^3) Thrust (lbf) ISP CEV Mass (Wf) (lbm) DV (fps) Useable Prop [1] (%) Margin [1] [2] (%) Ullage [3] (%) Volume (FT3) LO2 (OMS)162R / 250 psia 62.11 36110.4 5.3 612.21 CH4 (OMS)170R / 250 psia 23.22 10620.7 5.3 481.64 LO2 (RCS)162R / 250 psia 62.11 0.0 5.3 0.00 CH4 (RCS)170R / 250 psia 23.22 0.0 5.3 0.00 Total Propellant Weight 46731.2 3 tanks per propellant Total Tank Weight 3819.2 27.36 [ft] NTO tank Length Lander Performs LOI Burn Total Prop plus Tank Weight 50550.4 21.81 [ft] MMH tank length Trans Lunar Stack 176,910 Post LOI Burn 128,954 Total Helium Weight 1225.2 1 tanks per propellant TLI Constraint 149,000 Total Helium Tank Weight 1569.8 5.68 [ft] NTO He tank diameter Lander Allocation 99000 Total Helium plus Tank Wt 2795.1 5.25 [ft] MMH He tank diameter Margin -27,910 Total He, Prop, & Tank Wt 53345.4 3.5% 0.0 LO2 and Methane Wp (lbm) 3.5% 46731.2 3.2 60 44.40 100 345 128954 0 100.0% 362 128954 3600 98.0%3.4 150 44.99 900 3.5% 0.0 3.5% 32290.3 3.2 60 44.40 100 345 45438 0 100.0% 362 45438 6250 98.0%3.4 150 44.99 900 3.5% 0.0 LO2 and Methane Wp (lbm) 3.5% 14212.9 3.2 60 44.40 100 345 20000 0 100.0% LO2 and Methane Wp (lbm) 3.4 150 44.99 900 362 20000 6250 98.0% Includes 50,000 for CEV
Lander Systems • Propulsion – 4 +Z Direction 10Klb engines • Lunar Descent and Ascent – 4 +X Direction 10lkb engines • For LOI and Deorbit Burn • Allows for g loads eyeballs in for LOI – 4 RCS Quads located on Engine Pods • 870 lb engines for attitude control and translation – 4 RCS Tris located on Engine Pods • 870 lb engines for attitude control and translation – Tanks not optimized for size and shape • 3 He tanks • 7 Lox tanks • 7 CH4 tanks
Lander Systems • GNC – 3 IMUs – 2 Star Camera for IMU alignments – RNDZ Sensors • IROC • SROC • LROC • Lidar • Aux Computers for image processing • Transponders for comm with CEV or outpost • Sensor redundancy is covered by the CEV that can rescue Lander for failed rndz – Descent Sensors • Ground Proximity sensors • Ground Radar • Power – Solar Arrays • It may be possible to oversize solar arrays such that post landing crew can remove arrays for use in outpost solar array farm – Battery backup for night pass and supplement arrays during peak loading – Three redundant buses
Lander Systems • DPS – 3 Computers – BIUS – AUX computers for rndz sensor navigation – 1553 Data Bus • ECLSS – Consumables to support two cabin depress/repress cycles • Nominally should only require one depress post descent and then repress for ascent – Suit Cooling and Recharge capabilities – Resupply consumables from PTM
Lander Schematics
Lander Descent/Ascent Cockpit with LIDS Lunar Orbit Insertion/ Deorbit Engines (10klb): QTY 4, 2 per AFT Pod Lunar Descent/Ascent Engine (10klb): QTY 4 1 per Pod RCS Quad Engines (870 lb) Lunar Outpost Module on Flatbed Solar Array Panels Propellant tanks Descent/Ascent Consumables tanks Propellant Pressurization tanks RMS Landing Gear: 4 Struts per Pod RCS TRI Engines
AFT Engine Pods Gimbaled 10 klb Engine RCS Tri 870 lb RCS Quad 870 lbTwo Gimbaled 10 klb Engines +X +Z +Y
AFT Engine Pods Internal Gimbal Electronics RCS Driver Electronics Battery BIU
FWD Engine Pods Gimbaled 10lkb Engine RCS Tri 870 lb RCS Quad 870 lb +X +Z +Y
FWD Engine Pods Internal RNDZ Sensor Electronics RCS Driver Electronics Battery BIU Gimbal Electronics IROC Sensor (port pod) SROC Sensor (starboard pod) LROC Sensor (port pod) LIDAR (starboard pod) RNDZ Aux Computer Ground Proximity Sensor
Cockpit Internal Side View Lids O2 Tank N2 Tank Propellant Transfer Lines Cockpit Displays Ground Radar Computer Porch and Ladder in Stowed Position Crew member in Eva Suit for Landing Star Tracker IMU
Cockpit Forward Facing GND Radar Propellant tanks Propellant Pressurization tanks Star Tracker Doors O2 TankN2 TankGround Radar Electronics IMUsH2O Tank Computers Star Tracker Assemblies Lids Transfer connections FU OX He ECLSS Stowage Computer Stowage
Lander Forward Facing Solar Array Panels RNDZ Sensors RNDZ Sensors GND Radar Porch and Ladder in Stowed Position Propellant tanks Propellant Pressurization tanks RCS Quad Landing Gear 4 per Pod Descent/Ascent Engine Star Tracker Doors
Flat bed Transport Battery Electric Drive Plow attachment for regolith movement RMS Flat Bed Attach Point Transport can be used without flat bed for rover ops Computer Solar Array Panel Suit O2 Supply tank for extended rover ops Outpost Solar Array Panel stowed in Flatbed Suit H2O Supply tank for extended rover ops Hatch to non- pressurized cockpit
Flight Sequence: Flights Ones and Two
Flight One Lander performs Lunar Orbit Insertion with 4 AFT Engines
Flight One Lander Lands on surface
Flight One Lander Releases Outpost Module and flat bed Outpost ModuleAirlock Rover cockpit RMS
Flight One flat bed deploys Outpost Module with RMS Lunar Regolith for Shielding
Flight Two CEV2 with Crew Rotation PTM with DeltaV for LOI and Lander resupply Outpost Module #2 CEV2 Performs Lunar orbit Insertion
Flight TwoCEV2 with Crew Rotation PTM with DeltaV for LOI and Lander resupply Outpost Module #2 CEV2 Station keeps with CEV1 awaiting Lander CEV1
Flight One Termination Crew egresses outpost and takes off in Lander Lunar Regolith for Shielding Solar Array Farm
Crew RotationCEV2 with Crew Rotation CEV2 Station keeps with CEV1 Lander docks to outpost module #2 CEV1
Crew Rotation CEV2 with Crew Rotation CEV2 Station keeps with CEV1 Lander grapples outpost module #2 CEV1
Crew Rotation CEV2 with Crew Rotation CEV2 Station keeps with CEV1 Lander with outpost module #2 grappled undocks at PTM separation planeCEV1
Crew Rotation CEV2 with Crew Rotation CEV2 Station keeps with CEV1 Lander stows outpost module #2 CEV1
Crew Rotation CEV2 with Crew Rotation CEV2 Station keeps with CEV1 Lander redocks with PTM PTM resupplies Lander with propellant and consumables CEV2 crew modes CEV2 to loiter and ingresses PTM CEV1
Crew RotationCEV2 CEV2 Station keeps with CEV1 Lander undocks with CEV2 at CEV separation plane CEV2 crew flies Lander while CEV1 crew loiters in PTM CEV1
Crew RotationCEV2 CEV2 Station keeps with CEV1 Lander docks with CEV1 with PTM attached CEV1 crew powers up CEV1 CEV1
Crew Rotation CEV2 CEV2 Station keeps with CEV1 Lander undocks with CEV1 at PTM separation plane CEV1 crew preps CEV1 for TEI CEV2 crew performs Lunar Descent in Lander CEV1
Flight Two Lunar Surface Crew egresses Lander and ingresses flat Bed Lunar Regolith for Shielding Solar Array Farm
Flight Two Lunar Surface Flat bed extracts Outpost Module #2 from Lander Lunar Regolith for Shielding
Flight Two Lunar Surface Flat bed installs Outpost Module #2 Lunar Regolith for Shielding
Lunar Outpost: Assembly Sequence and Crew Rotation
Lunar Outpost 1 2 3 4 5 N1 N2 Airlock Solar Array Farm Regolith Berm for radiation shielding Mini Supply Module Node Two Landers allows 8 person Outpost crew rotating 4 crew members every 3 months Future Add-on Point Future Add-on Point Node
Assembly Sequence and Crew Rotations [Jan 2016-April 2017] Crew 1 Crew 2 Crew 2 Crew 3 Crew 3 Crew 4 Crew 4 Airlock & Outpost Module #1 Outpost Module #2 Outpost Module #2 Node 1 & MSM Node 1 & MSM Outpost Module #3 Outpost Module #3 CEV #1 CEV #2 CEV #2 CEV #3 CEV #3 CEV #4 CEV #4 Lander #1 Lander #1 Lander #1 Lander #2 Lander #2 Lander #1 Lander #1 PTM #1 PTM # 1 PTM #2 PTM #2 JAN 2016 APR 2016 JULY 2016 OCT 2016 JAN 2017 APR 2017 Crew 5 CEV #5 Lander #2 Outpost Module #4 PTM #3
Assembly Sequence and Crew Rotations [Jan 2017-April 2018] Crew 4 Crew 6 Crew 6 Crew 7 Crew 7 Crew 8 Crew 8 Outpost Module#3 Outpost Module #5 CEV #4 CEV #6 CEV #6 CEV #7 CEV #7 CEV #8 CEV #8 Lander #1 Lander #1 Lander #1 Lander #2 Lander #2 Lander #1 Lander #1 PTM #4 JAN 2017 APR 2017 JULY 2017 OCT 2017 JAN 2018 APR 2018 Crew 5 Crew 5 CEV #5 CEV #5 Lander #2 Lander #2 Outpost Module #4 Outpost Module #4 Node 2 & MSMNode 2 & MSM Outpost Module #5 PTM #2 PTM #3 PTM #3 PTM #4 NOTE: It may be possible to send a third Lander with Node 2 & MSM which could be used for surface flying. Would also need surface refueling capability which could be Crew 8’s payload.
Conclusion
Total Mass Rollup • Prop Dry: 10,000 lb excluding valves/manifolds • GNC: 100 lb • DPS: 200 lb excluding wiring • Power: 2,000 lb • LIDS: 1,000 lb • Crew: 1,280 lb (4 crew, suits and accommodations) • RMS: 1000 lb • ECLSS: ? • Structure: ? • ATCS: ? • Total: CBE 20,000 (15,580 + ?) not including 10,000 for OM (outpost module) • Lander total: – CBE+ OM+PROP (fwd) = 107500 (8,500 Negative Margin) • Prop wet mass for Lander: ~77500 – CBE+ OM+PROP (Back) = 126,910 (28,000 Negative Margin) • Prop wet mass for Lander: ~96,910
Conclusion • Reusable Lander is Not closed Design – Significant Negative Margin (8,500-28,000) • Limits of current design – Based on limited tools from Smart Buyer Effort • Prop Sizing Generic 6.xls for prop budget • CEV SBT Master Workbook for equipment mass – Based on limited engineering development • MOD notional concept based on Smart Buyer experience • Is concept viable? – Necessitates further study

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Reusable lunar lander

  • 1.
  • 2.
    Agenda • Introduction • MassAllocations and Equipment List • Lander Schematics • Flight One and Two Sequence • Lunar Outpost Assembly Sequence and Crew Rotation • Conclusion
  • 3.
  • 4.
    Concept • Instead ofabandoning the Lunar Lander after ascent each flight reuse for crew change out. • Requires several development components. – Propellant Transfer Module • Provides Delta V to CEV for LOI since LSAM is no longer part of TLI stack • Provides Delta V to resupply Lander for descent and ascent • Provides Consumables to CEV and Lander – Lunar outpost modules that can be stowed in Lander • Based off Single Stage, Dual Hab design – concept #2 Lunar Surface Access Module Study, RFT0020.05JSC
  • 5.
    Phased In approach •First flight consists of CEV and Lander – Lander performs LOI – Lander deploys first Outpost Module via attached Flat Bed Transport • Second and subsequent flights consist of CEV, PTM and Outpost Modules/Resupplies – CEV performs LOI with prop from PTM
  • 6.
  • 7.
  • 8.
    Mass Allocations • Lander:99,000 lb – Includes 10,000 outpost module capacity • CEV: 50,000 lb • PTM: 89,000 lb – Prop for CEV to perform LOI – Prop for Lander Descent and Ascent Resupply – Consumables for Lander • N2/O2 for cabin represses, Suit cooling H2O • Outpost Module #X: 10,000 lb max
  • 9.
    Propellant Mass Estimates(FWD)Lander Total 99000 Gc = 32.174 ft/s^2 Propellant Temp/Press Density (lbm/ft^3) MR AR [6] Rho_avg (lbm/ft^3) Thrust (lbf) ISP CEV Mass (Wi) (lbm) DV (fps) Useable Prop [1] (%) Margin [1] [2] (%) Ullage [3] (%) LO2 (OMS) 162R / 250 psia 62.11 32310.0 5.3 CH4 (OMS) 170R / 250 psia 23.22 9502.9 5.3 LO2 (RCS) 162R / 250 psia 62.11 0.0 5.3 CH4 (RCS) 170R / 250 psia 23.22 0.0 5.3 Total Propellant Weight 41812.9 4 tanks per propellant Total Tank Weight 1615.4 8.31 [ft] NTO tank Length Total Prop plus Tank Weight 43428.3 6.82 [ft] MMH tank length LANDER PERFORMING LOI Total Helium Weight 1313.4 1 tanks per propellant Total Helium Tank Weight 1643.2 5.82 [ft] NTO He tank diameter Total Helium plus Tank Wt 2956.5 5.37 [ft] MMH He tank diameter Total He, Prop, & Tank Wt 46384.8 Lander Wet Mass Post LOI 55873.7 Gc = 32.174 ft/s^2 Propellant Temp/Press Density (lbm/ft^3) MR AR [6] Rho_avg (lbm/ft^3) Thrust (lbf) ISP CEV Mass (Wi) (lbm) DV (fps) Useable Prop [1] (%) Margin [1] [2] (%) Ullage [3] (%) LO2 (OMS) 162R / 250 psia 62.11 18807.9 5.3 CH4 (OMS) 170R / 250 psia 23.22 5531.7 5.3 LO2 (RCS) 162R / 250 psia 62.11 0.0 5.3 CH4 (RCS) 170R / 250 psia 23.22 0.0 5.3 Total Propellant Weight 24339.7 2 tanks per propellant Total Tank Weight 912.2 9.45 [ft] NTO tank Length Total Prop plus Tank Weight 25251.9 7.72 [ft] MMH tank length LANDER PERFORMING DESCENT Total Helium Weight 764.5 1 tanks per propellant Total Helium Tank Weight 1152.0 4.86 [ft] NTO He tank diameter Total Helium plus Tank Wt 1916.5 4.48 [ft] MMH He tank diameter Total He, Prop, & Tank Wt 27168.4 Lander Wet Mass Post Landing 20769.5 and post Module Deploy 10000 Gc = 32.174 ft/s^2 Propellant Temp/Press Density (lbm/ft^3) MR AR [6] Rho_avg (lbm/ft^3) Thrust (lbf) ISP CEV Mass (Wi) (lbm) DV (fps) Useable Prop [1] (%) Margin [1] [2] (%) Ullage [3] (%) LO2 (OMS) 162R / 250 psia 62.11 6991.3 5.3 CH4 (OMS) 170R / 250 psia 23.22 2056.3 5.3 LO2 (RCS) 162R / 250 psia 62.11 0.0 5.3 CH4 (RCS) 170R / 250 psia 23.22 0.0 5.3 Total Propellant Weight 9047.6 1 tanks per propellant Total Tank Weight 361.1 7.37 [ft] NTO tank Length Total Prop plus Tank Weight 9408.7 6.08 [ft] MMH tank length LANDER PERFORMING ASCENT Total Helium Weight 284.2 1 tanks per propellant Total Helium Tank Weight 603.5 3.49 [ft] NTO He tank diameter Total Helium plus Tank Wt 887.6 3.22 [ft] MMH He tank diameter Total He, Prop, & Tank Wt 10296.3 Lander Dry Mass (excludes Prop tanks) 5150.5 LO2 and Methane Wp (lbm) 3.4 150 44.99 900 362 149000 3600 98.0% 3.5% 41812.9 3.2 60 44.40 100 345 149000 0 100.0% 3.5% 0.0 LO2 and Methane Wp (lbm) 3.4 150 44.99 900 362 55873.7 6200 98.0% 3.5% 24339.7 3.2 60 44.40 100 345 55873.7 0 100.0% 3.5% 0.0 LO2 and Methane Wp (lbm) 3.4 150 44.99 900 362 20769.5 6200 98.0% 345 20769.5 0 100.0%3.2 60 44.40 100 3.5% 0.0 3.5% 9047.6 If estimates are correct only 5150 lb for all Lander systems except prop wet mass
  • 10.
    Propellant Mass Estimates(Back) Gc = 32.174 ft/s^2 Propellant Temp/Press Density (lbm/ft^3) MR AR [6] Rho_avg (lbm/ft^3) Thrust (lbf) ISP CEV Mass (Wf) (lbm) DV (fps) Useable Prop [1] (%) Margin [1] [2] (%) Ullage [3] (%) Volume (FT3) LO2 (OMS)162R / 250 psia 62.11 10982.7 5.3 186.20 CH4 (OMS)170R / 250 psia 23.22 3230.2 5.3 146.49 LO2 (RCS)162R / 250 psia 62.11 0.0 5.3 0.00 CH4 (RCS)170R / 250 psia 23.22 0.0 5.3 0.00 Total Propellant Weight 14212.9 3 tanks per propellant Total Tank Weight 3819.2 27.36 [ft] NTO tank Length Total Prop plus Tank Weight 18032.2 21.81 [ft] MMH tank length Lander Performs Ascent Lander RNDZ Burnout weight 20,000 Total Helium Weight 1225.2 1 tanks per propellant Lander pre Ascent 35,438 Total Helium Tank Weight 1569.8 5.68 [ft] NTO He tank diameter Total Helium plus Tank Wt 2795.1 5.25 [ft] MMH He tank diameter Total He, Prop, & Tank Wt 20827.2 Gc = 32.174 ft/s^2 Propellant Temp/Press Density (lbm/ft^3) MR AR [6] Rho_avg (lbm/ft^3) Thrust (lbf) ISP CEV Mass (Wf) (lbm) DV (fps) Useable Prop [1] (%) Margin [1] [2] (%) Ullage [3] (%) Volume (FT3) LO2 (OMS)162R / 250 psia 62.11 24951.6 5.3 423.02 CH4 (OMS)170R / 250 psia 23.22 7338.7 5.3 332.80 LO2 (RCS)162R / 250 psia 62.11 0.0 5.3 0.00 CH4 (RCS)170R / 250 psia 23.22 0.0 5.3 0.00 Total Propellant Weight 32290.3 3 tanks per propellant Total Tank Weight 3819.2 27.36 [ft] NTO tank Length Lander Performs Descent Total Prop plus Tank Weight 36109.6 21.81 [ft] MMH tank length Lander Payload 10,000 Lander Touchdown weight 45,438 Total Helium Weight 1225.2 1 tanks per propellant Lander pre Deorbit Burn 78,954 Total Helium Tank Weight 1569.8 5.68 [ft] NTO He tank diameter Total Helium plus Tank Wt 2795.1 5.25 [ft] MMH He tank diameter Total He, Prop, & Tank Wt 38904.6 Gc = 32.174 ft/s^2 Propellant Temp/Press Density (lbm/ft^3) MR AR [6] Rho_avg (lbm/ft^3) Thrust (lbf) ISP CEV Mass (Wf) (lbm) DV (fps) Useable Prop [1] (%) Margin [1] [2] (%) Ullage [3] (%) Volume (FT3) LO2 (OMS)162R / 250 psia 62.11 36110.4 5.3 612.21 CH4 (OMS)170R / 250 psia 23.22 10620.7 5.3 481.64 LO2 (RCS)162R / 250 psia 62.11 0.0 5.3 0.00 CH4 (RCS)170R / 250 psia 23.22 0.0 5.3 0.00 Total Propellant Weight 46731.2 3 tanks per propellant Total Tank Weight 3819.2 27.36 [ft] NTO tank Length Lander Performs LOI Burn Total Prop plus Tank Weight 50550.4 21.81 [ft] MMH tank length Trans Lunar Stack 176,910 Post LOI Burn 128,954 Total Helium Weight 1225.2 1 tanks per propellant TLI Constraint 149,000 Total Helium Tank Weight 1569.8 5.68 [ft] NTO He tank diameter Lander Allocation 99000 Total Helium plus Tank Wt 2795.1 5.25 [ft] MMH He tank diameter Margin -27,910 Total He, Prop, & Tank Wt 53345.4 3.5% 0.0 LO2 and Methane Wp (lbm) 3.5% 46731.2 3.2 60 44.40 100 345 128954 0 100.0% 362 128954 3600 98.0%3.4 150 44.99 900 3.5% 0.0 3.5% 32290.3 3.2 60 44.40 100 345 45438 0 100.0% 362 45438 6250 98.0%3.4 150 44.99 900 3.5% 0.0 LO2 and Methane Wp (lbm) 3.5% 14212.9 3.2 60 44.40 100 345 20000 0 100.0% LO2 and Methane Wp (lbm) 3.4 150 44.99 900 362 20000 6250 98.0% Includes 50,000 for CEV
  • 11.
    Lander Systems • Propulsion –4 +Z Direction 10Klb engines • Lunar Descent and Ascent – 4 +X Direction 10lkb engines • For LOI and Deorbit Burn • Allows for g loads eyeballs in for LOI – 4 RCS Quads located on Engine Pods • 870 lb engines for attitude control and translation – 4 RCS Tris located on Engine Pods • 870 lb engines for attitude control and translation – Tanks not optimized for size and shape • 3 He tanks • 7 Lox tanks • 7 CH4 tanks
  • 12.
    Lander Systems • GNC –3 IMUs – 2 Star Camera for IMU alignments – RNDZ Sensors • IROC • SROC • LROC • Lidar • Aux Computers for image processing • Transponders for comm with CEV or outpost • Sensor redundancy is covered by the CEV that can rescue Lander for failed rndz – Descent Sensors • Ground Proximity sensors • Ground Radar • Power – Solar Arrays • It may be possible to oversize solar arrays such that post landing crew can remove arrays for use in outpost solar array farm – Battery backup for night pass and supplement arrays during peak loading – Three redundant buses
  • 13.
    Lander Systems • DPS –3 Computers – BIUS – AUX computers for rndz sensor navigation – 1553 Data Bus • ECLSS – Consumables to support two cabin depress/repress cycles • Nominally should only require one depress post descent and then repress for ascent – Suit Cooling and Recharge capabilities – Resupply consumables from PTM
  • 14.
  • 15.
    Lander Descent/Ascent Cockpit with LIDS LunarOrbit Insertion/ Deorbit Engines (10klb): QTY 4, 2 per AFT Pod Lunar Descent/Ascent Engine (10klb): QTY 4 1 per Pod RCS Quad Engines (870 lb) Lunar Outpost Module on Flatbed Solar Array Panels Propellant tanks Descent/Ascent Consumables tanks Propellant Pressurization tanks RMS Landing Gear: 4 Struts per Pod RCS TRI Engines
  • 16.
    AFT Engine Pods Gimbaled 10klb Engine RCS Tri 870 lb RCS Quad 870 lbTwo Gimbaled 10 klb Engines +X +Z +Y
  • 17.
    AFT Engine PodsInternal Gimbal Electronics RCS Driver Electronics Battery BIU
  • 18.
    FWD Engine Pods Gimbaled10lkb Engine RCS Tri 870 lb RCS Quad 870 lb +X +Z +Y
  • 19.
    FWD Engine PodsInternal RNDZ Sensor Electronics RCS Driver Electronics Battery BIU Gimbal Electronics IROC Sensor (port pod) SROC Sensor (starboard pod) LROC Sensor (port pod) LIDAR (starboard pod) RNDZ Aux Computer Ground Proximity Sensor
  • 20.
    Cockpit Internal SideView Lids O2 Tank N2 Tank Propellant Transfer Lines Cockpit Displays Ground Radar Computer Porch and Ladder in Stowed Position Crew member in Eva Suit for Landing Star Tracker IMU
  • 21.
    Cockpit Forward Facing GND Radar Propellanttanks Propellant Pressurization tanks Star Tracker Doors O2 TankN2 TankGround Radar Electronics IMUsH2O Tank Computers Star Tracker Assemblies Lids Transfer connections FU OX He ECLSS Stowage Computer Stowage
  • 22.
    Lander Forward Facing SolarArray Panels RNDZ Sensors RNDZ Sensors GND Radar Porch and Ladder in Stowed Position Propellant tanks Propellant Pressurization tanks RCS Quad Landing Gear 4 per Pod Descent/Ascent Engine Star Tracker Doors
  • 23.
    Flat bed Transport BatteryElectric Drive Plow attachment for regolith movement RMS Flat Bed Attach Point Transport can be used without flat bed for rover ops Computer Solar Array Panel Suit O2 Supply tank for extended rover ops Outpost Solar Array Panel stowed in Flatbed Suit H2O Supply tank for extended rover ops Hatch to non- pressurized cockpit
  • 24.
  • 25.
    Flight One Lander performsLunar Orbit Insertion with 4 AFT Engines
  • 26.
  • 27.
    Flight One Lander ReleasesOutpost Module and flat bed Outpost ModuleAirlock Rover cockpit RMS
  • 28.
    Flight One flat beddeploys Outpost Module with RMS Lunar Regolith for Shielding
  • 29.
    Flight Two CEV2 withCrew Rotation PTM with DeltaV for LOI and Lander resupply Outpost Module #2 CEV2 Performs Lunar orbit Insertion
  • 30.
    Flight TwoCEV2 withCrew Rotation PTM with DeltaV for LOI and Lander resupply Outpost Module #2 CEV2 Station keeps with CEV1 awaiting Lander CEV1
  • 31.
    Flight One Termination Crewegresses outpost and takes off in Lander Lunar Regolith for Shielding Solar Array Farm
  • 32.
    Crew RotationCEV2 withCrew Rotation CEV2 Station keeps with CEV1 Lander docks to outpost module #2 CEV1
  • 33.
    Crew Rotation CEV2 withCrew Rotation CEV2 Station keeps with CEV1 Lander grapples outpost module #2 CEV1
  • 34.
    Crew Rotation CEV2 withCrew Rotation CEV2 Station keeps with CEV1 Lander with outpost module #2 grappled undocks at PTM separation planeCEV1
  • 35.
    Crew Rotation CEV2 withCrew Rotation CEV2 Station keeps with CEV1 Lander stows outpost module #2 CEV1
  • 36.
    Crew Rotation CEV2 withCrew Rotation CEV2 Station keeps with CEV1 Lander redocks with PTM PTM resupplies Lander with propellant and consumables CEV2 crew modes CEV2 to loiter and ingresses PTM CEV1
  • 37.
    Crew RotationCEV2 CEV2 Stationkeeps with CEV1 Lander undocks with CEV2 at CEV separation plane CEV2 crew flies Lander while CEV1 crew loiters in PTM CEV1
  • 38.
    Crew RotationCEV2 CEV2 Stationkeeps with CEV1 Lander docks with CEV1 with PTM attached CEV1 crew powers up CEV1 CEV1
  • 39.
    Crew Rotation CEV2 CEV2 Stationkeeps with CEV1 Lander undocks with CEV1 at PTM separation plane CEV1 crew preps CEV1 for TEI CEV2 crew performs Lunar Descent in Lander CEV1
  • 40.
    Flight Two LunarSurface Crew egresses Lander and ingresses flat Bed Lunar Regolith for Shielding Solar Array Farm
  • 41.
    Flight Two LunarSurface Flat bed extracts Outpost Module #2 from Lander Lunar Regolith for Shielding
  • 42.
    Flight Two LunarSurface Flat bed installs Outpost Module #2 Lunar Regolith for Shielding
  • 43.
  • 44.
    Lunar Outpost 1 2 3 4 5 N1N2 Airlock Solar Array Farm Regolith Berm for radiation shielding Mini Supply Module Node Two Landers allows 8 person Outpost crew rotating 4 crew members every 3 months Future Add-on Point Future Add-on Point Node
  • 45.
    Assembly Sequence andCrew Rotations [Jan 2016-April 2017] Crew 1 Crew 2 Crew 2 Crew 3 Crew 3 Crew 4 Crew 4 Airlock & Outpost Module #1 Outpost Module #2 Outpost Module #2 Node 1 & MSM Node 1 & MSM Outpost Module #3 Outpost Module #3 CEV #1 CEV #2 CEV #2 CEV #3 CEV #3 CEV #4 CEV #4 Lander #1 Lander #1 Lander #1 Lander #2 Lander #2 Lander #1 Lander #1 PTM #1 PTM # 1 PTM #2 PTM #2 JAN 2016 APR 2016 JULY 2016 OCT 2016 JAN 2017 APR 2017 Crew 5 CEV #5 Lander #2 Outpost Module #4 PTM #3
  • 46.
    Assembly Sequence andCrew Rotations [Jan 2017-April 2018] Crew 4 Crew 6 Crew 6 Crew 7 Crew 7 Crew 8 Crew 8 Outpost Module#3 Outpost Module #5 CEV #4 CEV #6 CEV #6 CEV #7 CEV #7 CEV #8 CEV #8 Lander #1 Lander #1 Lander #1 Lander #2 Lander #2 Lander #1 Lander #1 PTM #4 JAN 2017 APR 2017 JULY 2017 OCT 2017 JAN 2018 APR 2018 Crew 5 Crew 5 CEV #5 CEV #5 Lander #2 Lander #2 Outpost Module #4 Outpost Module #4 Node 2 & MSMNode 2 & MSM Outpost Module #5 PTM #2 PTM #3 PTM #3 PTM #4 NOTE: It may be possible to send a third Lander with Node 2 & MSM which could be used for surface flying. Would also need surface refueling capability which could be Crew 8’s payload.
  • 47.
  • 48.
    Total Mass Rollup •Prop Dry: 10,000 lb excluding valves/manifolds • GNC: 100 lb • DPS: 200 lb excluding wiring • Power: 2,000 lb • LIDS: 1,000 lb • Crew: 1,280 lb (4 crew, suits and accommodations) • RMS: 1000 lb • ECLSS: ? • Structure: ? • ATCS: ? • Total: CBE 20,000 (15,580 + ?) not including 10,000 for OM (outpost module) • Lander total: – CBE+ OM+PROP (fwd) = 107500 (8,500 Negative Margin) • Prop wet mass for Lander: ~77500 – CBE+ OM+PROP (Back) = 126,910 (28,000 Negative Margin) • Prop wet mass for Lander: ~96,910
  • 49.
    Conclusion • Reusable Landeris Not closed Design – Significant Negative Margin (8,500-28,000) • Limits of current design – Based on limited tools from Smart Buyer Effort • Prop Sizing Generic 6.xls for prop budget • CEV SBT Master Workbook for equipment mass – Based on limited engineering development • MOD notional concept based on Smart Buyer experience • Is concept viable? – Necessitates further study