MAE 442 Design of Aerospace Vehicles II

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MAE 442 Design of Aerospace Vehicles II

• J. Cameron Systems Engineer
• J. Finkbeiner/B. Lassu Astrodynamics/Telecommuni
  cations
• L. Marszalek Propulsion
• L. McDaniel Configuration Structures
• U. Khan Attitude Determination Control
• K. Kietzman Life Support
• H. Nichelson Thermal Subsystems
• M. Buonanno Power

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Design Parameters

• Manned mission
• Extraterrestrial body other than Earths moon
• Mission begins in LEO
• Mission objective definition
• Some consideration must be given to cost

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Self-Imposed Restrictions

• Existing or soon to be realized technology
• Total departure mass below 1 million kg
• Mission duration under 8 years

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Mission Names

• Command Ship - Odysseus
• Lander - Telemachus

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Crew Members

• Mission Commander
• Pilot
• Research Director
• Agriculturalist/Nutritionist
• Mechanical Engineer
• Surgeon
• Network Administrator
• Life Support Engineer
• Nuclear/Thermal Engineer

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Astrodynamics Definitions

• ??V Change in orbital velocity generally
  associated with a rocket burn
• Apoapsis The point of largest radius and lowest
  velocity of an orbit
• Periapsis The point of smallest radius and
  highest velocity of an orbit

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Astrodynamics Definitions

• Hohmann Transfer An orbital transfer which
  requires minimum ?V requires the initial and
  final orbits to be coplanar
• Lamberts Solution Time and energy optimized
  transfer orbit faster than Hohmann Transfer

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Odysseus Trajectory

• Earth to Jupiter
• Jan. 18, 2030 to Jan. 7, 2032
• 719 days
• Jupiter
• Jan. 7, 2032 to Nov. 1, 2033
• 664 days
• Jupiter to Earth
• Nov. 1, 2033 to Jan 10, 2035
• 435 days

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Propulsion Types

• Chemical
• Maximum Isp of 450 sec
• Electrical
• High Isp low thrust
• Nuclear
• Mid-range Isp high thrust

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Nuclear Propulsion

• Benefits
• Relatively high Isp
• High thrust
• Only one engine needed
• Low mass ratio
• Disadvantages
• Not yet fully developed
• Very controversial

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Propulsion Specifications

• Nuclear Gas-Core Engine
• Closed Cycle
• Power - 6000 MW
• Thrust - 445 kN
• Mass - 56,800 kg
• Isp - 2080 seconds

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Gas-Core Engine
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Layout
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General Parameters
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Configuration Considerations

• Artificial Gravity
• Communications and Sensors
• Cooling Surfaces

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Zero Gravity Effects

• Bone loss up to 10 per month
• Calcium loss
• Vitamin D deficiency

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Hydroponics Bays

• Water-grown
• Genetically engineered fruits and vegetables
• Various beans and other legumes

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Life Support Systems

• Ventilation built into the habitats
• Water supply 50kg/person/day
• Air and water filtered and recycled through
  hydroponics
• Total power required 500kW

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Attitude Determination and Control

• Measuring spacecraft orientation
• Returning the spacecraft to the desired
  orientation
• Control of the telecommunications devices

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Disturbance Torques

• Aerodynamic
• Gravity Gradient
• Solar Radiation Pressure
• Magnetic
• Internal
• Orbit maneuvers

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Attitude Hardware

• Sensors
• Sun sensors
• Horizon sensors
• Star sensors
• Gyroscopes
• Momentum and Reaction wheels
• Gas jets

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Attitude Thrusters

• Thrusters
• Fuel N204/MMH
• Negligible mass
• Cold gas jet
• Minor attitude adjustments
• Bang-Bang Control

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Thermal Subsystems

• Responsible for maintaining the temperature on
  board the spacecraft
• Available tools
• Cryogenics
• Heat exchangers
• Position of spacecraft
• Radiators

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Shielding

• Hazards
• Micro-meteors
• Radiation
• Solutions
• Material shielding
• Magnetic shielding

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Power Requirements

• Long term output capability
• Lowest possible weight
• Easy to maintain
• 1 MW reactor required for lunar lander

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Thermionic Nuclear Reactor

• High thermal efficiency
• No moving parts
• Long life
• Small size

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Jovian Reactor

• 4 MW initial output
• 3.2 MW output after 7 years
• 15,600 kg mass
• 250 m2 radiator area

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Jupiter Orbit

• Decelerate upon arrival at Jupiter
• Enter circular orbit outside Europas path
• Hohmann transfer is then used to descend to the
  Europa orbit

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Telecommunications

• Reliable communication with Earth
• High bandwidth
• Allows for transmission of great amounts of data
• Light speed delay of 45 minutes
• Earth control capabilities
• Spacecraft can be controlled from Earth in
  emergency

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Communications system
Antenna



Power
Command
Spacecraft
Receiver
Switching
Processor

Systems
Unit


Human Interface



Onboard
Onboard
Clock
Computer
Storage

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Antenna Types

• High-gain
• Communication with Earth
• Highly directional
• Low-gain
• Communication with probes and lander
• Communication with satellite constellation
• Omnidirectional

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Why a Manned Mission?

• Possibility of life on Europa
• Robotic probes lack decision capabilities
• Scientific survey of Jovian system
• In-depth survey of Galilean moons
• Probes combined with observation of Jupiter
• Drill beneath Europas ice

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Lander

• TransHab Module
• Larger than command ship habitats
• Room for hydroponics and experiments
• Garage
• Rover - Bob
• Little Drill Dude
• Reusable launch vehicle
• One megawatt reactor

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Europa Lander - First Phase

• Departure to Europa
• Solid rockets
• Reusable launch vehicle attached
• Five crew members
• Reactor inactive powered by fuel cells
• Departure from Europa
• NRX nuclear rocket
• Reusable launch vehicle only

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Life Support on Europa

• Life support systems similar to those of the main
  ship
• Low gravity effects need to be considered
• Specially designed EVA suits

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Europa Lander - Second Phase

• Rendezvous with command ship
• Data processing
• Reusable launch vehicle turn around
• Crew swap
• Second landing
• Final rendezvous
• Reusable launch vehicle release

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Departure from Jupiter

• Elevation to Jovian centered orbit
• Burn to Earth
• One year travel time
• Burn to Earth capture (LEO)
• Shuttle (or replacement) transport to the surface

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Mission Summary

• Crew members - 9
• Trip time - 5 years
• Total cost - 60 billion dollars

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Any Questions?