Study Of Morphing Aircraft Based On The Newly Control Algorithm

Morphing aircraft is a new concept of modern aircraft, which is multi-purpose, polymorphousand has unconventional layout. Because of its excellent performance, morphing aircraft has becomean important research direction in the field of aerospace. According to the different needs of flyingmission, morphing aircraft can largely change the shape to adjust the flight velocity and flight attitude,which has caused the uncertainties of model structures and parameters.The unfalsified control is one type of newly model-free adaptive control which is based on thedata driving control theory. The control strategy enables one to design a controller that is consistentwith a performance objective and to measure past input and output online data without plant modelsor assumptions on the plant. This paper based on the characteristic of the morphing aircraft,researches the unfalsified control question of the system with the model structures and parametersuncertainties. The main contents of this paper can be summarized as follows:1. A newly digital PID parameter adaptive control method is proposed based on the unfalsifiedcontrol. Simulation is conducted both when there is disturbance and none disturbance with the system.And the results show that the unfalsified control algorithm can always make the controller with goodperformance and stability switches to the loop quickly. It’s also indicated that the algorithm has strongadaptability and simple application.2. For variable structures of the morphing aircraft, specifically considering a transformation ofmorphing aircraft from loiter to dash, the unfalsified adaptive control techniques and algorithms basedon multiple-controllers are studied. At the same time the set of controllers is determined. Then on thebasis of theory, the simulation is carried on for research and analysis.3. According to one morphing parameter-dependent model, the unfalsified control algorithmbased on the different wing spans is researched. The simulation is carried on for different morphingparameters. And the simulation result shows that the research can solve the problem of controlleradjustment when the wing span is changed during flight.