The application of a technique described as the model-controlled method (termed adaptive or semi-adaptive when applied to autopilots) for providing aircraft with variable stability and control characteristics is described. The development of a variable-stability helicopter using this method is treated in some detail to illustrate the significant design parameters and to demonstrate the advantages of the method over the more customary approach. The method allows for versatility in regard to simulation of complex equations of motion in that use may be made of standard computing components to construct an electrical analogue of the equations of motion of the simulated aircraft in a manner similar to that employed with ground simulation. An accurate knowledge of the test aircraft stability derivatives and their variation with speed and altitude is not required since the test aircraft response is independent of significant variations in its own characteristics. In the case of application of the method to helicopters, in-flight adjustment of the control loop parameters is not required to ensure this independence over the full speed range of the helicopter. Use of the method for variable-stability fixed-wing aircraft may require in-flight adjustment of the control loop gain if the inherent control sensitivity changes by more than about 50% owing to speed and/or altitude changes during the test. (Author)
The Model-Controlled Method for the Development of Variable-Stability Aircraft
1962
40 pages
Report
Keine Angabe
Englisch
Model-controlled method for development of variable-stability aircraft
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