The Space Shuttle Orbiter has conducted various flight test maneuvers during the Orbital Flight Test Program and beyond in order to establish heating rates at various angles of attack and center of gravity positions. The objective of this project was to investigating the heating effects on the body flap during the entry flight test maneuvers and determine the limits on the flap deflections for an aft center of gravity envelope on the Orbiter. An analysis program available from the Air Force Flight Test Center AFFTC) uses applicable simulation equations for the aerodynamic performance of the TPS in their flight simulator and data reduction program (HEATSET). The approach was to use the HEATSET program to determine the heating an one critical point on the body flap during the STS-2 entry flight test inputs (Flap Thermocouple V07T9508). From these results and other results on the outboard elevons, the maximum flap deflection angle and Orbiter aft center of gravity could be established. (Author)
Body Flap Heat Transfer Data from Space Shuttle Orbiter Entry Flight Test Maneuvers
1982
89 pages
Report
Keine Angabe
Englisch
Manned Spacecraft , Astronautics , Space shuttles , Flaps(Control surfaces) , Aerodynamic heating , Atmosphere entry , Deflection , Center of gravity , Angle of attack , Orbits , Flight simulation , Flight testing , Data reduction , Computer programs , Elevons , Reynolds number , Wind tunnel tests , Theses , HEATEST(Heat Estimation)