Research On Ascending Phase Control Methods For Sub-orbital Vehicle

Sub-orbital Vehicle is a aerocraft which can reach to the aerosphere's edge but cannot circle around the earth. Aiming at the engineering application, an in-depth research is carried out in this dissertation for the problem of ascending phase attitude control for the Sub-orbital Vehicle.Firstly, aiming at analyzing the dynamic characteristics for the Sub-orbital Vehicle, the six-degree dynamics model for the Sub-orbital Vehicle was established. Taking the designed Vehicle as an example, the linearization process for the dynamic model was clearly deduced. Subsequently, the linear equations of the pitching and lateral motions were obtained. With the flight data, the aerodynamics model and the rocket model was established. Based on the quantitative analysis of the dynamic coefficient, the equations were simplified. After that, the linear equations of the pitching, yawing and rolling motions were founded on the simplification. Finally, the simulation of dynamic characteristics was carried out for the designed Sub-orbital Vehicle.Secondly, the structure of the neural network is analyzed and a PID neural work controller was studied in detail. A parameter optimization based on neural network is proposed after the numerical model founded and a optimized PID controller which has a short settling time and little overshoot value was got at last.Thirdly, the mathematical model was obtained and the performance of Sub-orbital Vehicle attitude control system is simulated. A software platform for testing the attitude control algorithm is developed, and based on this platform the capability of the ascending phase control methods for the Sub-orbital Vehicle is analyzed. Finally, aiming at validating the mathematical model established in the paper, the rolling model of the solid launcher which designed by the students was established and its dynamic characteristics was analyzed. After the simulation of the small solid launcher control system, a hardware-in-the-Loop Simulation and the launch experimentation was carried out. And the data of flight testing was analyzed at last.The work presented in this dissertation can offer a technical foundation for the research and development of Sub-orbital Vehicle control system; meanwhile, it can be a beneficial reference for the control methods of small solid launcher.