Helicopter flight-control design using an H(2) methodRate-command and attitude-command flight-control designs for a UH-60 helicopter in hover are presented and were synthesized using an H(2) method. Using weight functions, this method allows the direct shaping of the singular values of the sensitivity, complementary sensitivity, and control input transfer-function matrices to give acceptable feedback properties. The designs were implemented on the Vertical Motion Simulator, and four low-speed hover tasks were used to evaluate the control system characteristics. The pilot comments from the accel-decel, bob-up, hovering turn, and side-step tasks indicated good decoupling and quick response characteristics. However, an underlying roll PIO tendency was found to exist away from the hover condition, which was caused by a flap regressing mode with insufficient damping.
Document ID
19910065087
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Takahashi, Marc D. (NASA Ames Research Center; U.S. Army, Aeroflightdynamics Directorate, Moffett Field CA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1991
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 91-2753
Meeting Information
Meeting: AIAA Guidance, Navigation and Control Conference