Final presentation

1. Mai Lee Chang Miguel Gallego Travis Marks Pete Penegor Miao Zhang EMA 569 Dr. Elder Prof. Hershkowitz

2. Design Intent To design an unmanned cargo transportation system to deliver materials from Low Earth Orbit to the lunar surface in support of a lunar base. Deliver at least 5 metric tons (mT) of cargo in 6 months or less. Product Design Specification

3. Mission Overview

4. What is Major Tom? Ion Propulsion System Lunar Lander Cargo Capsule

5. Mission Overview Engine Cargo Lander

6. Launch Vehicle SpaceX Falcon 9 Heavy 26.3 mT of cargo to LEO Launches to inclination of 28.5 degrees Total cost of $94.5 million

7. Launch Vehicle Fairing First launch: The engine and lander must fit inside of the fairing. Subsequent launches: Cargo capsule must fit inside of the fairing.

8. Low-Thrust Trajectory

9. Low-Thrust Trajectory Transfer Time = 158 days Dry Mass Delivered= 18 mT Fuel Required = 4.402 mT Delta-V = 7.51 km/s

10. Ion Propulsion System

11. Ion Propulsion Engine VASIMRVX-250(Variable Specific Impulse Magnetoplasma Rocket) Power = 250 kW Trip to LLO Isp= 3,500 s T = 12 N Trip back to LEO Isp= 3,000 s T = 14 N

12. Engine Structure The engine is supported by an aluminum structure 7075-T6 Members SAE AMS 4049K SAE AMS 4154N 2117-T4 Rivets MS20470 AD 3-9 3 m 1.8 m

13. Exterior of Engine Structure Whipple Shields Radiators

14. Fuel/Avionics Structure Aluminum/Titanium structure for fuel/avionic 6Al-4V Titanium bars per MIL-T-9046 7075-T6 Al plates per SAE AMS 4149K 2.75 m 3.2 m

15. Fuel System and Avionics 2 plates supporting 4 Argon fuel tanks each Composite Overwrap Pressure Vessels Each tank holds 655 kg 1 plate supporting avionics and RCS fuel tanks LOX, Methane tanks Helium tank AutoGNC

16. Exterior Components RCS Thrusters Avionics

17. Exterior of Fuel/Avionics Structure Stowed Solar Panels Whipple Shields Backside Active Docking System 6 m 4 m

18. Deployed Solar Arrays Deployed solar panels SLASR Arrays Two wings 18.4 m x 10.4 m each 30 mm of glass radiation protection PBOL = 298.5 kW PEOL = 268.7 kW Total weight = 500 kg

19. Cargo Capsule Major Tom

20. Cargo capsule Propulsion and Avionics Module 11.4 m Integrated Cargo Module 4 m

22. Titanium alloy honeycomb (Ti-3Al-2.5V) sandwich coreEgg-Crate Structure

23. Integrated cargo module Passive Docking System Guidance Cone 6 m Electrical Connector Fluidic Connector

24. Integrated cargo module Core Structure Releasable Cargo Pallet 96 Threaded Pin Puller Mechanism

25. Releasable cargo pallet Passive Flight Releasable Grapple Fixture

26. Releasable cargo pallet 5X Passive Flight Releasable Attachment Mechanism

27. Releasable cargo pallet 5X International Standard Payload Rack 5X Active Flight Releasable Attachment System

28. Integrated cargo module 2 Aluminum Plated Whipple Shield Al 2219-T851 (3 mm Thick) Al 5083 (1.2 mm Thick) Multi-Layer Insulation Intermediate Stuffing Layer 2 layers Ceramic Fabric (Nextel 312-AF-10) 3 Layers Kevlar (KM2 SEAL 364)

29. Cargo capsule: avionics & propulsion module Active Docking System Avionics 5.4m Liquid Methane Tanks 4.0m

30. Cargo Capsule: Propulsion Refuel VASIMR and Lunar Lander In-situ resource utilization (ISRU) Oxygen: refuel two ascent vehicles per year Methane: 2,160kg per year Propellant Tanks:

32. Thermal Control: multi-layerinsulation blankets

33. Sensors: pressure transducers, type T thermocouple internal probes

34. RCS Thrusters: LOX/Meth, XCOR

35. Fuel Transfer:

36. Diameter=3.0cm

37. 302 SS pipes per SAE J615Diameter=3.18m Methane tanks mounted with Al skirt on plate

38. Cargo Capsule: Avionics Guidance, Navigation, and Control GPS: General Dynamics Inertial Measurement Unit: Honeywell Star Tracker: Micro ASC Orstead DTU Communication S-Band UHF Band Computers Fault Tolerant Computer (FTC) FTC Electronic Boxes Monitoring and Safing Unit Power: Solar, lithium batteries Diameter=2.35m Diameter=1.25m

39. Cargo capsule: Active docking system Fluidic connector Retractable Probe Electrical connector Diameter=0.5m

40. Cargo Capsule Landing gear Based on Apollo Lunar Module Launch: stowed LEO: deployed Requirements: Structural Mechanical Landing performance Three main components: Primary Strut: Al 7075 per ASTM B221 Secondary Strut Al 7075 per ASTM B221 Footpad Aluminum Foam 2.07m 1.00m Dia=0.80m Deployed Position

41. Cargo Capsule: mass distribution

42. Lunar Lander

43. Lunar Lander: Descent and Ascent Low Lunar Orbit (LLO)- 100km Descent Initial De-Orbit Burn Powered Descent Vertical Landing Ascent Detach from cargo Continuous thrust Orbit Insertion Burn

44. Center Structure End plates 20mm Thick Aluminum 7075-T6as per AMS 4049K Vertical supports Aluminum 7075-T6 Fasteners 18/8 Stainless Steel Bolts as per ASTM F593

45. Center Structure Fuel Tanks 10mm Thick Al-Li 2090, Graphite Epoxy Various diameters Oxygen Tanks: 530mm, 480mm Methane Tanks: 260mm, 280mm, 320mm Notches for support 10mm spacing Fuel Tank Spacers/Holders 10mm Thick Aluminum 7075-T6

46. Skin Skin pieces 10 mm Aluminum 7075-T6as per AMS 4049K Fasteners 2117-T4 Aluminum Rivetsas per MS20470 Attached to vertical supports

47. Truss Structure Truss Aluminum 7075-T6 Swing out 90 deg Stowed area 0.3m x 0.6m x 1.0m

48. Truss Deployment Torsional spring SpaceDev’sSH-18010 Hinge Actuators SpaceDev’s EH-3525304 Stainless Steel Swing Arms Aluminum 7075-T6 Resting plate Aluminum 7075-T6 Hinges Sealed Deep Groove

49. Propulsion System Two CECE Engines Thrust: 80360 N Weight: 77 kg RCS Thrusters 20 XCOR CH4/LOX Double up in middle

50. Power/Avionics Power Solar Panel Stretched Lens Array Regenerative Fuel Cell Lithion Model L1147 Avionics Similar to VASIMR/Cargo Capsule ALHAT System Flash Lidar Altitude Velocity Terrain Relative Navigation Hazard Detection and Avoidance

51. Questions