The effect of normal atmospheric variability on Space Shuttle Orbiter entry performanceThe Space Shuttle Orbiter is controlled during entry by a combination of aerodynamic surfaces composed of elevons, a body flap, and a rudder that flares as a speedbrake, and a reaction control system that uses 16 small rocket thrusters. To determine the effects of realistic atmospheric density variations on reentry, a series of Monte Carlo trajectories were generated for each season. The performance parameters analyzed include maximum hinge moments experienced by the aerodynamic control surfaces, the maximum deflections experienced by the aerodynamic control surfaces, a range of angle-of-sideslip values, maximum dynamic pressure, maximum stagnation point heat rate, and state conditions at touchdown. The results of the investigation indicate that the Orbiter guidance and control systems could tolerate atmospheric variability without failures in the control system hardware.
Document ID
19790043552
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Powell, R. W. (NASA Langley Research Center Hampton, VA, United States)
Campbell, J. W. (NASA Langley Research Center Hampton, VA, United States)
Kanoy, V. M. (NASA Langley Research Center Hampton, Va., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1978
Subject Category
Space Transportation
Meeting Information
Meeting: Conference on Atmospheric Environment of Aerospace Systems and Applied Meteorology