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Major Tom: Lunar Cargo Transport
 

Major Tom: Lunar Cargo Transport

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Major Tom: Lunar Cargo Transport Major Tom: Lunar Cargo Transport Presentation Transcript

  • 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 Trajectory
    Transfer Time = 158 days
    Dry Mass Delivered= 18 mT
    Fuel Required = 4.402 mT
    Delta-V = 7.51 km/s
  • Ion Propulsion System
  • 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
  • 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 plates
    per SAE AMS 4149K
    2.75 m
    3.2 m
  • 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
  • Exterior Components
    RCS Thrusters
    Avionics
  • Exterior of Fuel/Avionics Structure
    Stowed Solar Panels
    Whipple
    Shields
    Backside
    Active Docking
    System
    6 m
    4 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
    11.4 m
    Integrated Cargo
    Module
    4 m
  • Cargo capsule: Integrated cargo module
    6Al-4V Titanium alloy angles per SAE ASM9046J
    • 24-ply toughened graphite bismaleimide composite facesheet (IM7/5260)
    • Titanium alloy honeycomb (Ti-3Al-2.5V) sandwich core
    Egg-Crate Structure
  • Integrated cargo module
    Passive Docking System
    Guidance Cone
    6 m
    Electrical Connector
    Fluidic Connector
  • Integrated cargo module
    Core Structure
    Releasable Cargo Pallet
    96 Threaded Pin Puller Mechanism
  • Releasable cargo pallet
    Passive Flight Releasable Grapple Fixture
  • Releasable cargo pallet
    5X Passive Flight Releasable Attachment Mechanism
  • Releasable cargo pallet
    5X International Standard Payload Rack
    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
    Active Docking System
    Avionics
    5.4m
    Liquid Methane Tanks
    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:
  • Cargo Capsule: Propulsion
    • 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
    Diameter=3.18m
    Methane tanks mounted with Al skirt on plate
  • 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
    Fluidic connector
    Retractable Probe
    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
    2.07m
    1.00m
    Dia=0.80m
    Deployed Position
  • Cargo Capsule: mass distribution
  • Lunar Lander
  • 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
  • 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
  • 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-T6as 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’sSH-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