Mai Lee Chang<br />Miguel Gallego<br />Travis Marks<br />Pete Penegor<br />Miao Zhang<br />EMA 569<br />Dr. Elder<br />Pro...
Design Intent<br />	To design an unmanned cargo transportation system to deliver materials from Low Earth Orbit to the lun...
Mission Overview<br />
What is Major Tom?<br />Ion Propulsion System		    Lunar Lander<br />				Cargo Capsule<br />
Mission Overview<br />Engine<br />Cargo<br />Lander<br />
Launch Vehicle<br />SpaceX Falcon 9 Heavy<br />26.3 mT of cargo to LEO<br />Launches to inclination<br />	of 28.5 degrees ...
Launch Vehicle Fairing<br />First launch:<br />The engine and lander must fit inside of the fairing.<br />Subsequent launc...
Low-Thrust Trajectory<br />
Low-Thrust Trajectory<br />Transfer Time = 158 days<br />Dry Mass Delivered= 18 mT<br />Fuel Required = 4.402 mT<br />Delt...
Ion Propulsion System<br />
Ion Propulsion Engine<br />VASIMRVX-250(Variable Specific Impulse Magnetoplasma Rocket)<br />Power = 250 kW<br />Trip to L...
Engine Structure<br />The engine is supported by an aluminum structure<br />7075-T6 Members<br />SAE AMS 4049K<br />SAE AM...
Exterior of Engine Structure<br />Whipple Shields<br />			Radiators<br />
Fuel/Avionics Structure<br />Aluminum/Titanium structure for fuel/avionic<br />6Al-4V Titanium bars <br />per MIL-T-9046<b...
Fuel System and Avionics<br />2 plates supporting 4 Argon fuel tanks each<br />Composite Overwrap Pressure Vessels<br />Ea...
Exterior Components<br />RCS 								Thrusters<br />Avionics<br />
Exterior of Fuel/Avionics Structure<br />  Stowed Solar Panels<br />		  Whipple<br />		   Shields<br /> Backside<br />		  ...
Deployed Solar Arrays<br />Deployed solar panels<br />SLASR Arrays<br />Two wings<br />18.4 m x 10.4 m each<br />30 mm of ...
Cargo Capsule<br />Major Tom<br />
Cargo capsule<br />Propulsion and Avionics Module<br />11.4 m<br />Integrated Cargo <br />Module<br />4 m<br />
Cargo capsule: Integrated cargo module<br />6Al-4V Titanium alloy angles per SAE ASM9046J <br /><ul><li>24-ply toughened g...
Titanium alloy honeycomb (Ti-3Al-2.5V) sandwich core</li></ul>Egg-Crate Structure<br />
Integrated cargo module<br />Passive Docking System<br />Guidance Cone<br />6 m<br />Electrical Connector<br />Fluidic Con...
Integrated cargo module<br />Core Structure<br />Releasable Cargo Pallet<br />96 Threaded Pin Puller Mechanism<br />
Releasable cargo pallet<br />Passive Flight Releasable Grapple Fixture<br />
Releasable cargo pallet<br />5X Passive Flight Releasable Attachment Mechanism<br />
Releasable cargo pallet<br />5X International Standard Payload Rack<br />5X Active Flight Releasable Attachment System<br />
Integrated cargo module<br />2 Aluminum Plated Whipple Shield<br />Al 2219-T851 (3 mm Thick)<br />Al 5083 (1.2 mm Thick)<b...
Cargo capsule: avionics & propulsion module <br />Active Docking System<br />Avionics<br />5.4m<br />Liquid Methane Tanks<...
Cargo Capsule:  Propulsion<br />Refuel VASIMR and Lunar Lander<br />In-situ resource utilization (ISRU)<br />Oxygen:  refu...
Cargo Capsule: Propulsion<br /><ul><li>Mount: Al skirt
Thermal Control:  multi-layerinsulation blankets
Sensors: pressure transducers, type T thermocouple internal probes
RCS Thrusters: LOX/Meth, XCOR
Fuel Transfer:
Diameter=3.0cm
302 SS pipes per SAE J615</li></ul>Diameter=3.18m<br />Methane tanks mounted with Al skirt on plate<br />
Cargo Capsule: Avionics<br />Guidance, Navigation, and Control<br />GPS: General Dynamics<br />Inertial Measurement Unit: ...
Cargo capsule: Active docking system<br />Fluidic connector<br />Retractable Probe<br />Electrical connector<br />Diameter...
Cargo Capsule Landing gear<br />Based on Apollo Lunar Module<br />Launch: stowed<br />LEO: deployed<br />Requirements: <br...
Cargo Capsule: mass distribution<br />
Lunar Lander<br />
Lunar Lander: Descent and Ascent<br />Low Lunar Orbit (LLO)- 100km<br />Descent<br />Initial De-Orbit Burn<br />Powered De...
Center Structure<br />End plates<br />20mm Thick Aluminum 7075-T6as per AMS 4049K<br />Vertical supports<br />Aluminum 707...
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  • Major Tom: Lunar Cargo Transport

    1. 1. Mai Lee Chang<br />Miguel Gallego<br />Travis Marks<br />Pete Penegor<br />Miao Zhang<br />EMA 569<br />Dr. Elder<br />Prof. Hershkowitz<br />
    2. 2. Design Intent<br /> To design an unmanned cargo transportation system to deliver materials from Low Earth Orbit to the lunar surface in support of a lunar base.<br />Deliver at least 5 metric tons (mT) of cargo in 6 months or less.<br />Product Design Specification<br />
    3. 3. Mission Overview<br />
    4. 4. What is Major Tom?<br />Ion Propulsion System Lunar Lander<br /> Cargo Capsule<br />
    5. 5. Mission Overview<br />Engine<br />Cargo<br />Lander<br />
    6. 6. Launch Vehicle<br />SpaceX Falcon 9 Heavy<br />26.3 mT of cargo to LEO<br />Launches to inclination<br /> of 28.5 degrees <br />Total cost of $94.5 million<br />
    7. 7. Launch Vehicle Fairing<br />First launch:<br />The engine and lander must fit inside of the fairing.<br />Subsequent launches:<br />Cargo capsule must fit inside of the fairing.<br />
    8. 8. Low-Thrust Trajectory<br />
    9. 9. Low-Thrust Trajectory<br />Transfer Time = 158 days<br />Dry Mass Delivered= 18 mT<br />Fuel Required = 4.402 mT<br />Delta-V = 7.51 km/s<br />
    10. 10. Ion Propulsion System<br />
    11. 11. Ion Propulsion Engine<br />VASIMRVX-250(Variable Specific Impulse Magnetoplasma Rocket)<br />Power = 250 kW<br />Trip to LLO<br />Isp= 3,500 s<br />T = 12 N<br />Trip back to LEO<br />Isp= 3,000 s<br />T = 14 N<br />
    12. 12. Engine Structure<br />The engine is supported by an aluminum structure<br />7075-T6 Members<br />SAE AMS 4049K<br />SAE AMS 4154N<br />2117-T4 Rivets<br />MS20470 AD 3-9<br />3 m<br />1.8 m<br />
    13. 13. Exterior of Engine Structure<br />Whipple Shields<br /> Radiators<br />
    14. 14. Fuel/Avionics Structure<br />Aluminum/Titanium structure for fuel/avionic<br />6Al-4V Titanium bars <br />per MIL-T-9046<br />7075-T6 Al plates<br />per SAE AMS 4149K<br />2.75 m<br />3.2 m<br />
    15. 15. Fuel System and Avionics<br />2 plates supporting 4 Argon fuel tanks each<br />Composite Overwrap Pressure Vessels<br />Each tank holds 655 kg<br />1 plate supporting<br /> avionics and RCS fuel<br /> tanks<br />LOX, Methane tanks<br />Helium tank<br />AutoGNC<br />
    16. 16. Exterior Components<br />RCS Thrusters<br />Avionics<br />
    17. 17. Exterior of Fuel/Avionics Structure<br /> Stowed Solar Panels<br /> Whipple<br /> Shields<br /> Backside<br /> Active Docking<br /> System<br />6 m<br />4 m<br />
    18. 18. Deployed Solar Arrays<br />Deployed solar panels<br />SLASR Arrays<br />Two wings<br />18.4 m x 10.4 m each<br />30 mm of glass<br /> radiation protection<br />PBOL = 298.5 kW<br />PEOL = 268.7 kW<br />Total weight = 500 kg<br />
    19. 19. Cargo Capsule<br />Major Tom<br />
    20. 20. Cargo capsule<br />Propulsion and Avionics Module<br />11.4 m<br />Integrated Cargo <br />Module<br />4 m<br />
    21. 21. Cargo capsule: Integrated cargo module<br />6Al-4V Titanium alloy angles per SAE ASM9046J <br /><ul><li>24-ply toughened graphite bismaleimide composite facesheet (IM7/5260)
    22. 22. Titanium alloy honeycomb (Ti-3Al-2.5V) sandwich core</li></ul>Egg-Crate Structure<br />
    23. 23. Integrated cargo module<br />Passive Docking System<br />Guidance Cone<br />6 m<br />Electrical Connector<br />Fluidic Connector<br />
    24. 24. Integrated cargo module<br />Core Structure<br />Releasable Cargo Pallet<br />96 Threaded Pin Puller Mechanism<br />
    25. 25. Releasable cargo pallet<br />Passive Flight Releasable Grapple Fixture<br />
    26. 26. Releasable cargo pallet<br />5X Passive Flight Releasable Attachment Mechanism<br />
    27. 27. Releasable cargo pallet<br />5X International Standard Payload Rack<br />5X Active Flight Releasable Attachment System<br />
    28. 28. Integrated cargo module<br />2 Aluminum Plated Whipple Shield<br />Al 2219-T851 (3 mm Thick)<br />Al 5083 (1.2 mm Thick)<br />Multi-Layer Insulation<br />Intermediate Stuffing Layer<br />2 layers Ceramic Fabric (Nextel 312-AF-10)<br />3 Layers Kevlar (KM2 SEAL 364)<br />
    29. 29. Cargo capsule: avionics & propulsion module <br />Active Docking System<br />Avionics<br />5.4m<br />Liquid Methane Tanks<br />4.0m<br />
    30. 30. Cargo Capsule: Propulsion<br />Refuel VASIMR and Lunar Lander<br />In-situ resource utilization (ISRU)<br />Oxygen: refuel two ascent vehicles per year<br />Methane: 2,160kg per year<br />Propellant Tanks:<br />
    31. 31. Cargo Capsule: Propulsion<br /><ul><li>Mount: Al skirt
    32. 32. Thermal Control: multi-layerinsulation blankets
    33. 33. Sensors: pressure transducers, type T thermocouple internal probes
    34. 34. RCS Thrusters: LOX/Meth, XCOR
    35. 35. Fuel Transfer:
    36. 36. Diameter=3.0cm
    37. 37. 302 SS pipes per SAE J615</li></ul>Diameter=3.18m<br />Methane tanks mounted with Al skirt on plate<br />
    38. 38. Cargo Capsule: Avionics<br />Guidance, Navigation, and Control<br />GPS: General Dynamics<br />Inertial Measurement Unit: Honeywell<br />Star Tracker: Micro ASC Orstead DTU <br />Communication<br />S-Band<br />UHF Band<br />Computers<br />Fault Tolerant Computer (FTC)<br />FTC Electronic Boxes<br />Monitoring and Safing Unit<br />Power: Solar, lithium batteries<br />Diameter=2.35m<br />Diameter=1.25m<br />
    39. 39. Cargo capsule: Active docking system<br />Fluidic connector<br />Retractable Probe<br />Electrical connector<br />Diameter=0.5m<br />
    40. 40. Cargo Capsule Landing gear<br />Based on Apollo Lunar Module<br />Launch: stowed<br />LEO: deployed<br />Requirements: <br />Structural<br />Mechanical<br />Landing performance<br />Three main components:<br />Primary Strut: <br />Al 7075 per ASTM B221<br />Secondary Strut<br />Al 7075 per ASTM B221<br />Footpad<br />Aluminum Foam<br />2.07m<br />1.00m<br />Dia=0.80m<br />Deployed Position<br />
    41. 41. Cargo Capsule: mass distribution<br />
    42. 42. Lunar Lander<br />
    43. 43. Lunar Lander: Descent and Ascent<br />Low Lunar Orbit (LLO)- 100km<br />Descent<br />Initial De-Orbit Burn<br />Powered Descent<br />Vertical Landing<br />Ascent<br />Detach from cargo<br />Continuous thrust<br />Orbit Insertion Burn<br />
    44. 44. Center Structure<br />End plates<br />20mm Thick Aluminum 7075-T6as per AMS 4049K<br />Vertical supports<br />Aluminum 7075-T6<br />Fasteners<br />18/8 Stainless Steel Bolts as per ASTM F593<br />
    45. 45. Center Structure<br />Fuel Tanks<br />10mm Thick <br />Al-Li 2090, Graphite Epoxy<br />Various diameters<br />Oxygen Tanks: 530mm, 480mm<br />Methane Tanks: 260mm, 280mm, 320mm<br />Notches for support<br />10mm spacing<br />Fuel Tank Spacers/Holders<br />10mm Thick Aluminum 7075-T6<br />
    46. 46. Skin<br />Skin pieces<br />10 mm Aluminum 7075-T6as per AMS 4049K<br />Fasteners<br />2117-T4 Aluminum Rivetsas per MS20470<br />Attached to vertical supports<br />
    47. 47. Truss Structure<br />Truss<br />Aluminum 7075-T6<br />Swing out 90 deg<br />Stowed area<br />0.3m x 0.6m x 1.0m<br />
    48. 48. Truss Deployment<br />Torsional spring<br />SpaceDev’sSH-18010 Hinge<br />Actuators<br />SpaceDev’s EH-3525304 Stainless Steel<br />Swing Arms<br />Aluminum 7075-T6<br />Resting plate<br />Aluminum 7075-T6<br />Hinges<br />Sealed Deep Groove<br />
    49. 49. Propulsion System<br />Two CECE Engines<br />Thrust: 80360 N<br />Weight: 77 kg<br />RCS Thrusters<br />20 XCOR CH4/LOX<br />Double up in middle<br />
    50. 50. Power/Avionics<br />Power<br />Solar Panel<br />Stretched Lens Array<br />Regenerative Fuel Cell<br />Lithion Model L1147<br />Avionics<br />Similar to VASIMR/Cargo Capsule<br />ALHAT System<br />Flash Lidar<br />Altitude<br />Velocity<br />Terrain Relative Navigation<br />Hazard Detection and Avoidance <br />
    51. 51. Questions<br />
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