Successfully reported this slideshow.
We use your LinkedIn profile and activity data to personalize ads and to show you more relevant ads. You can change your ad preferences anytime.

Major Tom: Lunar Cargo Transport

1,203 views

Published on

Final presentation

  • Be the first to comment

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 />

×