High angle of attack control law development for a free-flight wind tunnel model using direct eigenstructure assignmentFlight-control laws are developed for a wind-tunnel aircraft model flying at a high angle of attack by using a synthesis technique called direct eigenstructure assignment. The method employs flight guidelines and control-power constraints to develop the control laws, and gain schedules and nonlinear feedback compensation provide a framework for considering the nonlinear nature of the attack angle. Linear and nonlinear evaluations show that the control laws are effective, a conclusion that is further confirmed by a scale model used for free-flight testing.
Document ID
19910064980
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wendel, Thomas R. (McDonnell Aircraft Co. Saint Louis, MO, United States)
Boland, Joseph R. (McDonnell Aircraft Co. Saint Louis, MO, United States)
Hahne, David E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1991
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 91-2627
Meeting Information
Meeting: AIAA Guidance, Navigation and Control Conference