| This dissertation studies further on the design of flight control system for several vehicles. Firstly, the guidance and control law of the space shuttle is studied. Then the structure configuration and control law of carrier-based aircraft based on GPS in the landing phrase are studied, and made simulation test effectively. Thirdly, design a helicopter flight control system based on state feedback and feedforward compensator to decouples the dynamics and handlings, and meet the required handlings characteristics. At last, a real-time visual simulation system of the longitudinal semi-automatic carrier landing navigation system is established.Firstly, the Entry guidance law is studied, various guidance law are compared, and the guidance law based on a drag vs energy profile is confirmed. The profile is obtained by optimization method. Then the flight reference is obtained, and the guidance law is derived to track this reference. At the same time, an alpha profile and bank angle profile are designed.Secondly, the automatic landing navigation system for carrier-based aircraft based on GPS is studied, and the coordinate conversion is achieved by quaternion. The structure configuration, guidance and control law for longitude and lateral system are established, and then made a digital simulation for the whole system.To meet the required handlings characteristics, design a carrier-based helicopter flight control system based on state feedback and feedforward compensator to decouples the dynamics, and track the four independent channels.Lastly, the longitudinal semi-automatic carrier landing system based on Instrumental System is discretized, and the real-time simulation application software is designed in C++ language. Then a visual demonstrate system of the longitudinal semi-automatic carrier landing navigation system is developed.The achievements of this dissertation contribute to the academic research and engineering application of the research programs described above.
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