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Trajectory Simulation and Validation of Drag Loss Model Post First Stage Launch

This study focuses on the trajectory simulation and validation of a drag loss model during the second and third stages of launch vehicles, maintaining a constant steering angle after the first stage. The findings indicate that smaller launch vehicles experience greater drag losses, while larger steering angles lead to reduced drag losses. Results are compared to established models like the Space Shuttle and Titan IV/Centaur, highlighting significant differences in drag loss performance. Supported by comprehensive references, this research contributes to optimizing space mission trajectories.

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Trajectory Simulation and Validation of Drag Loss Model Post First Stage Launch

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  1. Daniel Chua31 January 2008Trajectory SimulationValidation of Drag Loss Model – Constant Steering After First StageAssisted by Amanda Briden, Elizabeth Harknessand Brad Ferris

  2. Trajectory Simulation – Drag Loss • Expect smaller launch vehicles to suffer greater drag losses • Expect larger steering angles to result in lower drag losses • Keep steering angle constant after 1st stage • Run for 2nd and 3rd stage angles Trajectory Optimization

  3. Trajectory Simulation – Drag Loss • Results: • Compare to Shuttle (2029633 kg GLOM): 107 m/s Titan IV/Centaur (886420 kg GLOM): 156 m/s (from SMAD) Trajectory Optimization

  4. References • Wertz, J. R., and Larson, W. J., Space Mission Analysis and Design, 3rd ed., Microcosm, 1999 • Humble, R.W., and Henry, G.N., Space Propulsion Analysis and Design, 7th ed., McGraw-Hill, 1995 Trajectory Optimization

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