If a Space Shuttle Main Engine (SSME) fails during the initial 160 seconds of the Shuttle flight, a return-to-launch-site maneuver will be implemented. The period of concern for this task is the pitch-around maneuver when the vehicle is flying backward. The intent of this report is to identify and define the flowfield at the most critical locations from an environment perspective. The solution procedure used to predict the plume heating rates involves both computational analysis and engineering modeling.
External Tank Aerothermal Design Criteria Verification
1991
80 pages
Report
Keine Angabe
Englisch
Manned Spacecraft , Spacecraft Trajectories & Flight Mechanics , Space Safety , Fuel & Propellant Tanks , Abort trajectories , Computational fluid dynamics , External tanks , Flow distribution , Space shuttles , Spacecraft trajectories , Design analysis , Spacecraft maneuvers , Engine failure , Heating , Plumes , Space shuttle main engine , Space transportation system flights , Thermal analysis