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MAE 442 Design of Aerospace Vehicles II

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... with observation of Jupiter. Drill beneath Europa's ice ... Departure from Jupiter. Elevation to Jovian centered orbit. Burn to Earth. One year travel time ... – PowerPoint PPT presentation

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Title: MAE 442 Design of Aerospace Vehicles II


1
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

2
Design Parameters
  • Manned mission
  • Extraterrestrial body other than Earths moon
  • Mission begins in LEO
  • Mission objective definition
  • Some consideration must be given to cost

3
Self-Imposed Restrictions
  • Existing or soon to be realized technology
  • Total departure mass below 1 million kg
  • Mission duration under 8 years

4
(No Transcript)
5
Mission Names
  • Command Ship - Odysseus
  • Lander - Telemachus

6
Crew Members
  • Mission Commander
  • Pilot
  • Research Director
  • Agriculturalist/Nutritionist
  • Mechanical Engineer
  • Surgeon
  • Network Administrator
  • Life Support Engineer
  • Nuclear/Thermal Engineer

7
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

8
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

9
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

10
Propulsion Types
  • Chemical
  • Maximum Isp of 450 sec
  • Electrical
  • High Isp low thrust
  • Nuclear
  • Mid-range Isp high thrust

11
Nuclear Propulsion
  • Benefits
  • Relatively high Isp
  • High thrust
  • Only one engine needed
  • Low mass ratio
  • Disadvantages
  • Not yet fully developed
  • Very controversial

12
Propulsion Specifications
  • Nuclear Gas-Core Engine
  • Closed Cycle
  • Power - 6000 MW
  • Thrust - 445 kN
  • Mass - 56,800 kg
  • Isp - 2080 seconds

13
Gas-Core Engine
14
Layout
15
General Parameters
16
Configuration Considerations
  • Artificial Gravity
  • Communications and Sensors
  • Cooling Surfaces

17
Zero Gravity Effects
  • Bone loss up to 10 per month
  • Calcium loss
  • Vitamin D deficiency

18
Hydroponics Bays
  • Water-grown
  • Genetically engineered fruits and vegetables
  • Various beans and other legumes

19
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

20
Attitude Determination and Control
  • Measuring spacecraft orientation
  • Returning the spacecraft to the desired
    orientation
  • Control of the telecommunications devices

21
Disturbance Torques
  • Aerodynamic
  • Gravity Gradient
  • Solar Radiation Pressure
  • Magnetic
  • Internal
  • Orbit maneuvers

22
Attitude Hardware
  • Sensors
  • Sun sensors
  • Horizon sensors
  • Star sensors
  • Gyroscopes
  • Momentum and Reaction wheels
  • Gas jets

23
Attitude Thrusters
  • Thrusters
  • Fuel N204/MMH
  • Negligible mass
  • Cold gas jet
  • Minor attitude adjustments
  • Bang-Bang Control

24
Thermal Subsystems
  • Responsible for maintaining the temperature on
    board the spacecraft
  • Available tools
  • Cryogenics
  • Heat exchangers
  • Position of spacecraft
  • Radiators

25
Shielding
  • Hazards
  • Micro-meteors
  • Radiation
  • Solutions
  • Material shielding
  • Magnetic shielding

26
Power Requirements
  • Long term output capability
  • Lowest possible weight
  • Easy to maintain
  • 1 MW reactor required for lunar lander

27
Thermionic Nuclear Reactor
  • High thermal efficiency
  • No moving parts
  • Long life
  • Small size

28
Jovian Reactor
  • 4 MW initial output
  • 3.2 MW output after 7 years
  • 15,600 kg mass
  • 250 m2 radiator area

29
Jupiter Orbit
  • Decelerate upon arrival at Jupiter
  • Enter circular orbit outside Europas path
  • Hohmann transfer is then used to descend to the
    Europa orbit

30
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

31
Communications system
Antenna



Power
Command
Spacecraft
Receiver
Switching
Processor

Systems
Unit


Human Interface



Onboard
Onboard
Clock
Computer
Storage

32
Antenna Types
  • High-gain
  • Communication with Earth
  • Highly directional
  • Low-gain
  • Communication with probes and lander
  • Communication with satellite constellation
  • Omnidirectional

33
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

34
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

35
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

36
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

37
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

38
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

39
Mission Summary
  • Crew members - 9
  • Trip time - 5 years
  • Total cost - 60 billion dollars

40
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