major tom: lunar cargo transport
DESCRIPTION
Final presentationTRANSCRIPT
Mai Lee Chang
Miguel Gallego
Travis Marks
Pete Penegor
Miao Zhang
EMA 569
Dr. Elder
Prof. Hershkowitz
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
MISSION OVERVIEW
WHAT IS MAJOR TOM?
Ion Propulsion System Lunar Lander
Cargo Capsule
MISSION OVERVIEW
Engine Cargo Lander
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
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.
LOW-THRUST TRAJECTORY
LOW-THRUST TRAJECTORYTransfer Time = 158 daysDry Mass Delivered= 18 mTFuel Required = 4.402 mTDelta-V = 7.51 km/s
ION PROPULSION SYSTEM
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
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
EXTERIOR OF ENGINE STRUCTURE
Whipple Shields
Radiators
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
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
EXTERIOR COMPONENTS
RCS Thrusters
Avionics
EXTERIOR OF FUEL/AVIONICS STRUCTURE
Stowed Solar Panels
Whipple Shields
Backside
Active Docking System
4 m
6 m
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
CARGO CAPSULE
Major Tom
CARGO CAPSULE
Propulsion and Avionics Module
Integrated Cargo Module4 m
11.4 m
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
INTEGRATED CARGO MODULE
Passive Docking System
6 m
Electrical Connector
Guidance Cone
Fluidic Connector
INTEGRATED CARGO MODULE
96 Threaded Pin Puller Mechanism
Core Structure
Releasable Cargo Pallet
RELEASABLE CARGO PALLET
Passive Flight Releasable Grapple Fixture
RELEASABLE CARGO PALLET
5X Passive Flight Releasable Attachment Mechanism
RELEASABLE CARGO PALLET
1. 5X International Standard Payload Rack
2. 5X Active Flight Releasable Attachment System
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)
CARGO CAPSULE: AVIONICS & PROPULSION MODULE
Avionics
Active Docking System
Liquid Methane Tanks
5.4m
4.0m
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
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
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
CARGO CAPSULE: ACTIVE DOCKING SYSTEM
Retractable Probe
Fluidic connector
Electrical connector
Diameter=0.5m
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
CARGO CAPSULE: MASS DISTRIBUTION
Mass (kg)
Structure 5,034
Propulsion 3,073
Avionics 96
Cargo Capacity 8,297
Total 16,500
LUNAR LANDER
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
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
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
SKIN
Skin pieces 10 mm Aluminum 7075-T6
as per AMS 4049K Fasteners
2117-T4 Aluminum Rivetsas per MS20470
Attached to vertical supports
TRUSS STRUCTURE
Truss Aluminum 7075-T6 Swing out 90 deg
Stowed area 0.3m x 0.6m x 1.0m
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
PROPULSION SYSTEM
Two CECE Engines Thrust: 80360 N Weight: 77 kg
RCS Thrusters 20 XCOR CH4/LOX Double up in middle
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
QUESTIONS