The dynamic pressure time history after thrust termination is shown to be represented by a simple analytical approximation derived from powered flight trajectory parameters. The approximation is correlated with the results of accurate trajectory simulations. The agreement is adequate for 'ride-out' abort escape studies. (Author)
Dynamic Pressure Decay after Thrust Termination
1965
11 pages
Report
No indication
English
Rocket Engines & Motors , Thrust termination systems , Pressure , Attenuation , Abort , Aerospace systems , Escape systems , Thrust reversal , Aerodynamic characteristics , Descent trajectories , Approximation(Mathematics) , Manned spacecraft , Launch vehicles , Space capsules , Gemini , Mol(Manned orbiting laboratories) , Titan 3