| Summary: | 碩士 === 國立交通大學 === 電機與控制工程系所 === 96 === The thesis investigates three-dimensional midcourse and terminal guidance laws for missile interceptor and the associated divert and attitude control system design. Since the commanded guidance acceleration, in both the midcourse phase and terminal phase, is achieved using divert thrusters and in the terminal phase the infrared seeker needs to continuously lock-on to the target, true proportional navigation guidance law seems to be the most appropriate choice among the various guidance laws. We derive the three-dimensional true proportional navigation guidance law and analyze, via simulations, various system parameters such as radar measurement errors, seeker lock-on range, and flight control system bandwidth, have on the performance of the interceptor. Divert and attitude control system use on-off thrusters as actuators. Divert control achieves the command guidance acceleration using pulse width modulation (PWM), in which the pulse duration is proportional to the magnitude of acceleration command. Attitude control system is linear and designed using linearized model, it uses angle and rate feedback, achieves three-axis stabilization and is implemented using PWM. Simulations for both guidance and control use Standard Missile III as a prototype. Results from this research should be useful for future system and hardware development.
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