Hypersonic Vehicles Boosterseparation Section Trajectory Optimization And Antiinterference Desing

The most important feature of hypersonic aircraft guidance and control system is that the trajectory of motion has nonlinearity and uncertainty, while the anti-jamming design of attitude control system is the most important issue to be solved. The thesis takes a type hypersonic vehicle model as the basic object of study, by using convex optimization tool CVXGEN to solve longitudinal trajectory optimization problems in its booster separation section. Meanwhile, the paper makes use of the robust parameters approach to solve the anti-interference design problem of attitude control system.Firstly, analyzed the force of the hypersonic vehicle in the booster separation section, and established simplified equations of motion under the trajectory coordinates; hypersonic vehicle trajectory optimization problem in the phase of booster separation, including the optimization index function, equation of state constraints, nonlinear constraints, state variable constraints, control variables constraints, and then established six freedom degrees attitude model of the aircraft.Secondly, described the specific process from nonlinear problem with constraints into convex optimization problem. Put forward theorized fundamental basis, indicating the feasibility of the use of linear systems to approximate nonlinear systems; further completed track optimization problem convex processing in its separation section; the specific quadratic mathematical description of convex optimization was given, and then used convex optimization tool to the final calculation solved.Thirdly, solved the anti-interference design problems of the hypersonic vehicle in booster separation section. Designed respectively from the pitch channel and yaw channel two aspects to solve specific problems of interference controller, and then simulation verification.Finally, given the simulation analysis of pitch channel, the third chapter trajectory optimization resulting controlled variable angle of attack as to be tracked program signal, in the role of the sinusoidal interference signal, conducted a controller parameter optimization, after the best indicators of the controller are met, conducted program compilation, and then conducted simulation analysis.The results show that by using convex optimization tool CVXGEN can ensure real-time nature of the solution process of the hypersonic vehicle longitudinal trajectory optimization in its booster separation section; at the same time, the use of robust parametric approach of control system design can solve pitch channel and yaw channel anti-interference design problems in its booster separation section.