Research On Multi-model Adaptive Control Low For Fixed-wing UAV

With the continuous development of Unmanned Aerial Vehicle (UAV) technology andthe expansion of its application scope, research of UAV related technology has become aworldwide hot topic. As the core of the UAV control system, research of the automaticcontrol algorithm is also in deepening. In this paper, based on the six-degree-of-freedomnonlinear model of fixed-wing UAV, combined with the flight test and the regulation resultsfor the multiple parameters set, the simulation model based on MATLAB of F-16fighteraircraft whose parameters are relatively open is established, which carries on thedecoupling, balancing and linearization to obtain the multiple linear models. On this basis,the multi-model control algorithm is researched to apply to UAV motion system. Andcombining the UAV flight dynamics characteristics, we select the appropriate multi-modelswitching strategy to ensure that the flight control system is stable. The simulation resultsshow that this control algorithm can guarantee the stability of fixed-wing UAV to achievethe desired effect.Firstly, this thesis introduces the development history of fixed-wing UAV, and a briefoverview of the UAV control system with some kinds of control algorithm. Then thepresent situation of the application of multi-model adaptive control law is discussed, whichleads to this topic research background and significance. And then the research content andthe overall structure of the thesis are summarized.Secondly, based on the analysis of basic motion parameters of UAV, through the forceanalysis and moment analysis of general fixed-wing UAV, the six-degree-of-freedomnonlinear mathematical model is established.Then, based on the design of the PID control algorithm of aeromagnetic UAV andother mature control algorithm, as well as in many flight tests and experiments, with theadjust of multiple parameters set, the switching of the controller parameters is furtherresearch.After all, based on the F-16fighter, the simulation model on MATLAB is built and themodel of decoupling, balancing and linearization are completed, and a set of multiple linear models is established. And then, the application of multi-model control law on the F-16fighter is researched. Both the longitudinal and lateral movement reach the expected effectthrough MATLAB simulation. And with the navigation algorithm proposed in this thesis,the simulation of flight line also shows the effect of control stability.Finally, the work in this thesis is summarized, at the same time we puts forward thefuture research direction.