An Approximate Solution for Rocket Flight with Linear-Tangent Thrust Attitude Control
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CENTER
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This note presents an approximate solution to the equations of motion written with linear-tangent thrust attitude control. The usefullness of this solution is evaluated by comparison with accurate numerical integration. This comparison shows that the solution gives accuracies sufficient for preliminary calculations for satellite boost vehicles and has a four speed advantage over numerical integration of the same accuracy level.
- Numerical Mathematics
- Rocket Engines
- Spacecraft Trajectories and Reentry