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Mission Design Requirements

Mission Design Requirements. First priority is to deliver takeoff mass to aircraft team. Desirable Booster Characteristics. Preliminary Booster Calculations. Created Excel Spreadsheet Database of rocket motors from trade studies Losses neglected: Gravity Drag Calculates:

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Mission Design Requirements

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  1. Mission Design Requirements First priority is to deliver takeoff mass to aircraft team.

  2. Desirable Booster Characteristics

  3. Preliminary Booster Calculations Created Excel Spreadsheet Database of rocket motors from trade studies Losses neglected: Gravity Drag Calculates: DV produced by each stage upper stage structural mass booster takeoff mass Max G-Force during launch Input Variables: Stage Specifications Payload Mass

  4. Booster Calculator

  5. Solid Rocket Motorstrade study

  6. Liquid Rocket Motors • 2 separated tanks • Can be stopped or restarted • High specific impulse • 3 types • RP-1 widely used for first stages such as Saturn V and Atlas V - Temperature of Combustion: 3,670 deg K. - Isp (sl): 300. - Fuel Density: 0.806 g/cc. - Fuel Freezing Point: -73 deg C. - Fuel Boiling Point: 147 deg C - Oxidiser Density: 1.140 g/cc. - Oxidiser Freezing Point: -219 deg C. - Oxidiser Boiling Point: -183 deg C.

  7. Upper Stage Motors Desired variable thrust, engine restart capability Compared hybrid and liquid rocket motors Hybrids quickly eliminated due to lower Isp, high structural mass, and poor commercial availability For system simplicity/reliability, pressure-fed liquid motor deemed desirable. Results of liquid motor trade study led to: SpaceX Kestrel 2 upper stage rocket motor Currently used as upper stage for SpaceX Falcon I booster Pressure-fed LOX-RP1 rocket motor 52kg motor and nozzle Isp of 330s Flight-proven design Currently in serial production 7

  8. Rocket Motor Database

  9. Booster Design • 3 stage Booster • 1st stage: ATK Orion 50XL (Solid) • 2nd stage: ATK Star 31 (Solid) • 3rd stage: SpaceX Kestrel 2 (LOX-RP1 liquid)

  10. Booster Design 3rd Stage SpaceX Kestrel 2 Fairing 2nd Stage ATK Star31 1st Stage ATK Orion50XL Interstages

  11. Stage Specifications

  12. Comparison to Pegasus • Payload for AirLaunch mission is 120kg fuel and 30kg satellite • Monopropellant hydrazine thruster for upper stage trajectory error correction

  13. Comparison to Pegasus Pegasus AirLaunch

  14. Gravity Turn Simulations: • Used Joe Mueller’s Matlab code to simulate gravity turn • Parameters that can be varied in code: • Flight Path Angle (FPA) • Height at which ignition 3 starts • Mass of Stage 3 Propellant Launch Flight Path Angle: 87.97 Deg.

  15. Launch Vehicle (LV) initial launch conditions: Launch Vehicle (LV) C-17 carrier aircraft LV initial launch conditions: t = 0 seconds V ≈ 0 m/s H ≈ 12 km FPA ≈ 88° FPA

  16. Launch trajectory: • Simulations produced the following direct launch trajectory to reach ISS: Targeted ISS perigee altitude of 334 km

  17. 3D Orbit of Payload: • Matlab simulation produced the following orbit: Payload’s Low Earth Orbit Inclination: 51°

  18. Detailed orbit simulations: Satellite Tool Kit (STK) orbit simulations:

  19. STK simulation: • Used STK to simulate orbit of payload relative to ISS • Apoapsis and Periapsis visible • Enjoy the excellent video

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