Stabilizing the elastic modes of the Space Shuttle vehicle during launch.The influence of vibration modes on the vehicle control system stabilization problem is examined with a conventional, nonadaptive, single-rate-sensor autopilot. The linear stability analyses are based upon symmetric and antisymmetric modal data generated from flexible-beam models. Primary emphasis is placed upon using only the three orbiter engines as control effectors. Principal control system variables considered are the effective autopilot rate and attitude gains, rate and attitude sensor locations, and lead/lag stability compensation. Results indicate that a multiple-sensor autopilot configuration will be necessary to achieve satisfactory vibration mode stability margins.
Document ID
19730040748
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Greiner, H. G. (General Dynamics Corp. Convair Aerospace Div., San Diego, Calif., United States)
Date Acquired
August 7, 2013
Publication Date
March 1, 1973
Subject Category
Space Vehicles
Report/Patent Number
AIAA PAPER 73-319
Meeting Information
Meeting: Dynamics Specialists Conference
Location: Williamsburg, VA
Start Date: March 19, 1973
End Date: March 20, 1973
Sponsors: American Institute of Aeronautics and Astronautics