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Mission Design Requirements

The first priority of the mission's design requirements is to deliver the takeoff mass to the aircraft team. The booster design includes desirable characteristics and preliminary calculations created in an Excel spreadsheet. The database comprises rocket motors from trade studies, neglecting losses like gravity and drag. It calculates the delta-v produced by each stage, upper stage structural mass, booster takeoff mass, and maximum G-Force during launch. Input variables include stage specifications, payload mass, booster calculator, and types of rocket motors used. The booster design consists of a 3-stage setup with specific rocket motor models assigned to each stage. A comparison to the Pegasus rocket system is included, with details on the payload, propellant type, and upper stage trajectory correction methods.

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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

  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

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