This simulation enables one to compute the influence of the spinning atmosphere on the recovery devices used in a returning spacecraft: retarding rocket, lifting panels and retarding parachute. The computer simulation determines location, velocity vector, and landing spot. Two articles on the subject were published by the author. The first dealt with the influence of lifting panels on a spacecraft trajectory and the second dealt with the influence of retarding rocket burn time on energy dissipation rate in a spacecraft trajectory. The influence of the retarding rocket burn time on the maximum values along the trajectory of five output parameters is shown. The following items are the five output parameters: maximum rate of heat dissipation; maximum skin temperature; maximum deceleration; and overall trajectory time.
Influence of a Retarding Rocket on Parameter Limits for Reentry Trajectories
1991
3 pages
Report
Keine Angabe
Englisch
Spacecraft Trajectories & Flight Mechanics , Burning time , Panels , Reentry trajectories , Retrorocket engines , Spacecraft trajectories , Parachutes , Computerized simulation , Cooling , Deceleration , Energy dissipation , Position (Location) , Skin temperature (Non-biological) , Foreign technology
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