Download - Major Tom: Lunar Cargo Transport
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Mai Lee Chang
Miguel Gallego
Travis Marks
Pete Penegor
Miao Zhang
EMA 569
Dr. Elder
Prof. Hershkowitz
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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
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MISSION OVERVIEW
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WHAT IS MAJOR TOM?
Ion Propulsion System Lunar Lander
Cargo Capsule
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MISSION OVERVIEW
Engine Cargo Lander
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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
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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.
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LOW-THRUST TRAJECTORY
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LOW-THRUST TRAJECTORYTransfer Time = 158 daysDry Mass Delivered= 18 mTFuel Required = 4.402 mTDelta-V = 7.51 km/s
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ION PROPULSION SYSTEM
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ION PROPULSION ENGINE
VASIMR VX-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
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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
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EXTERIOR OF ENGINE STRUCTURE
Whipple Shields
Radiators
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FUEL/AVIONICS STRUCTURE
Aluminum/Titanium structure for fuel/avionic
6Al-4V Titanium bars per MIL-T-9046
7075-T6 Al platesper SAE AMS 4149K
3.2 m
2.75 m
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FUEL SYSTEM AND AVIONICS
2 plates supporting 4 Argon fuel tanks each Composite Overwrap Pressure Vessels Each tank holds 655 kg
1 plate supportingavionics and RCS fueltanks LOX, Methane tanks Helium tank AutoGNC
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EXTERIOR COMPONENTS
RCS Thrusters
Avionics
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EXTERIOR OF FUEL/AVIONICS STRUCTURE
Stowed Solar Panels
Whipple Shields
Backside
Active Docking System
4 m
6 m
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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
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CARGO CAPSULE
Major Tom
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CARGO CAPSULE
Propulsion and Avionics Module
Integrated Cargo Module4 m
11.4 m
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CARGO CAPSULE: INTEGRATED CARGO MODULE
• 24-ply toughened graphite bismaleimide composite facesheet (IM7/5260)
• Titanium alloy honeycomb (Ti-3Al-2.5V) sandwich core
6Al-4V Titanium alloy angles per SAE ASM 9046J
Egg-Crate Structure
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INTEGRATED CARGO MODULE
Passive Docking System
6 m
Electrical Connector
Guidance Cone
Fluidic Connector
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INTEGRATED CARGO MODULE
96 Threaded Pin Puller Mechanism
Core Structure
Releasable Cargo Pallet
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RELEASABLE CARGO PALLET
Passive Flight Releasable Grapple Fixture
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RELEASABLE CARGO PALLET
5X Passive Flight Releasable Attachment Mechanism
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RELEASABLE CARGO PALLET
1. 5X International Standard Payload Rack
2. 5X Active Flight Releasable Attachment System
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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)
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CARGO CAPSULE: AVIONICS & PROPULSION MODULE
Avionics
Active Docking System
Liquid Methane Tanks
5.4m
4.0m
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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:
Material Unit Mass(kg) Press(Mpa) R(m) Tot.Mass(kg)
Liquid OxygenAl-Li 2090 liner & graphite epoxy composite 18 2.24 0.16 18
Liquid MethaneAl-Li 2090 liner & graphite epoxy composite 543 2.24 0.56 3,257
Helium
Inconel 718-liner, graphite epoxy composite 136 41.37 0.42 136
Gaseous ArgonTitanium liner & carbon fiber composite 904 31.03 0.47 5,424
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CARGO CAPSULE: PROPULSION Mount: Al skirt Thermal Control: multi-layer insulation 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
Methane tanks mounted with Al skirt on plate
Diameter=3.18m
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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
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CARGO CAPSULE: ACTIVE DOCKING SYSTEM
Retractable Probe
Fluidic connector
Electrical connector
Diameter=0.5m
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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 Deployed Position
2.07m
1.00m
Dia=0.80m
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CARGO CAPSULE: MASS DISTRIBUTION
Mass (kg)
Structure 5,034
Propulsion 3,073
Avionics 96
Cargo Capacity 8,297
Total 16,500
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LUNAR LANDER
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LUNAR LANDER: DESCENT AND ASCENT
Low Lunar Orbit (LLO)- 100km Descent
1. Initial De-Orbit Burn2. Powered Descent3. Vertical Landing
Ascent1. Detach from cargo2. Continuous thrust3. Orbit Insertion Burn
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CENTER STRUCTURE
End plates 20mm Thick Aluminum 7075-T6
as per AMS 4049K Vertical supports
Aluminum 7075-T6 Fasteners
18/8 Stainless Steel Bolts as per ASTM F593
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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
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SKIN
Skin pieces 10 mm Aluminum 7075-T6
as per AMS 4049K Fasteners
2117-T4 Aluminum Rivetsas per MS20470
Attached to vertical supports
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TRUSS STRUCTURE
Truss Aluminum 7075-T6 Swing out 90 deg
Stowed area 0.3m x 0.6m x 1.0m
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TRUSS DEPLOYMENT
Torsional spring SpaceDev’s
SH-18010 Hinge Actuators
SpaceDev’s EH-3525304 Stainless Steel
Swing Arms Aluminum 7075-T6
Resting plate Aluminum 7075-T6
Hinges Sealed Deep Groove
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PROPULSION SYSTEM
Two CECE Engines Thrust: 80360 N Weight: 77 kg
RCS Thrusters 20 XCOR CH4/LOX Double up in middle
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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
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QUESTIONS