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Development of the reentry flight dynamics simulator for evaluation of space shuttle orbiter entry systemsA nonlinear, six degree of freedom, digital computer simulation of a vehicle which has constant mass properties and whose attitudes are controlled by both aerodynamic surfaces and reaction control system thrusters was developed. A rotating, oblate Earth model was used to describe the gravitational forces which affect long duration Earth entry trajectories. The program is executed in a nonreal time mode or connected to a simulation cockpit to conduct piloted and autopilot studies. The program guidance and control software used by the space shuttle orbiter for its descent from approximately 121.9 km to touchdown on the runway.
Document ID
19800023921
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Rowell, L. F. (NASA Langley Research Center Hampton, VA, United States)
Powell, R. W. (NASA Langley Research Center Hampton, VA, United States)
Stone, H. W., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
October 1, 1980
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
L-13662
NASA-TP-1700
Accession Number
80N32429
Funding Number(s)
PROJECT: RTOP 506-63-13-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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