NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Simulation studies of alternate longitudinal control systems for the Space Shuttle Orbiter in the landing regimeSimulations of the Space Shuttle Orbiter in the landing task were conducted by the NASA Ames-Dryden Flight Research Facility using the Ames Research center vertical motion simulation (VMS) and the total in-flight simulator (TIFS) variable-stability aircraft. Several new control systems designed to improve the orbiter longitudinal response characteristics were investigated. These systems improved the flightpath response by increasing the amount of pitch-rate overshoot. Reduction in the overall time delay was also investigated. During these evaluations, different preferences were noted for the baseline or the new systems depending on the pilot background. The trained astronauts were quite proficient with the baseline system and found the new systems to be less desirable than the baseline. On the other hand, the pilots without extensive flight training with the Orbiter had a strong preference for the new systems. This paper presents the results of the VMS and TIFS simulations. A hypothesis is presented regarding the control strategies of the two pilot groups and how this influenced their control system preferences. Interpretations of these control strategies are made in terms of open-loop aircraft response characteristics as well as pilot-vehicle closed-loop characteristics.
Document ID
19860062935
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Powers, B. G.
(NASA Flight Research Center Edwards, CA, United States)
Sarrafian, S. K.
(NASA Flight Research Center Edwards, CA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1986
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 86-2127
Accession Number
86A47673
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available