A design method, based on a systematic approach to aircraft attitude control parameters, was developed and tried on the design of a pitch controller for the Do28D Skyservant aircraft. The method takes into consideration the entire range of in-flight requirements posed by the guidance characteristics of the aircraft, including appropriate response (damping) to air turbulence. The controller is independent of radical changes in flight conditions and thus responds to the special problem of low speed elevator control as a harmonic progression of the elevator deflection angle. The influence of an onboard computer on flight behavior is examined and flight test results are compared with computer simulation results.
An in-Flight Controller Insensitive to Parameters Variation
1978
80 pages
Report
Keine Angabe
Englisch
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