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Rocket Booster Design and Launch Simulation Project

Project focuses on delivering takeoff mass to aircraft team through booster calculations using Excel. Detailed stage and motor database for booster design. Gravity and drag losses neglected.

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Rocket Booster Design and Launch Simulation Project

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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

  7. Rocket Motor Database

  8. 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)

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

  10. Stage Specifications

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

  12. Comparison to Pegasus Pegasus AirLaunch

  13. 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.

  14. 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

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

  16. 3D Orbit of Payload: • Matlab simulation produced the following orbit: Payload’s Low Earth Orbit Inclination: 51°

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

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