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Linearized model aircraft in a certain range of conditions is segmented effective when the aircraft operating in nonlinear range, such as a large angle of attack , quick maneuvering , the linear model is no longer applicable , the need to make use of nonlinear dynamic inversion processing model . This article deals with real-time flight simulation system is a semi -physical simulation system, which is mainly based on MATLAB and LABVIEW platform to build, using real-time network communications will servos , attitude angle , engine, atmospheric pressure , etc. is difficult to establish accurate mathematical model of a system in kind way to join the flight control simulation loop, in order to more accurately test the flight control system performance. This paper is structured as follows : First, create a nonlinear model of the aircraft , and it conducted a small perturbation linearization, to decouple the two groups for the horizontal and vertical linear equations , the equations in each division according to the flight status further simplified , so that become the single-input single -output system (SISO), to facilitate the controller design. Secondly, a linear model fighter the conventional PID controller design and designed on the basis of the intelligent PID controller , and were applied to the nonlinear model aircraft for testing , comparing the two PID control methods quality and robustness. Again, for fast maneuvering aircraft at high angles of attack linear model is no longer applicable , the use of nonlinear dynamic inversion of a global linear model , on the basis of the design of a linear controller. Finally , real-time flight simulation system introduced the basic structure and working principle . And flight control system design semi -physical simulation experiments.
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