An aircraft with low wing loading, such as the deHavilland, Twin Otter, exhibits a relatively large acceleration sensitivity to wind gusts. These undesirable aircraft motions can be reduced using an automatic ride control system. In this paper, the techniques of quadratic optimal control theory are utilized to investigate the capabilities of such a ride control system. The effects of the wind gusts on the aircraft can be modeled by a vector stochastic process containing seven states. The impact of this disturbance model on the optimal control system structure is assessed and comparison is made to a system without gust feedback.
Optimal ride control for the Twin Otter, STOL aircraft
Annual Asilomar Conference on Circuits, Systems, and Computers ; 1975 ; Pacific Grove, CA
1976-01-01
Miscellaneous
No indication
English
Engineering Index Backfile | 1964
Design of a lateral ride control system for STOL aircraft
TIBKAT | 1983
|Twin tilt nacelle V/STOL aircraft
NTRS | 1984
|STOL ride control feasibility study
AIAA | 1973
|