| Summary: | 碩士 === 逢甲大學 === 自動控制工程所 === 91 === How to develop a missile guidance law that can effectively against very high-speed incoming targets, such as ballistic missiles, has been a major concern in the defense technique. It has been unveiled recently in the literature that the most effective way for a lower speed interceptor to successfully engage an incoming target with very high speed is to limit the aspect angle between the missile and target flight path to within 180 deg plus or minus a few degrees. On the basis of this requirement, a new integrated fuzzy guidance law is developed in this thesis such that the design missile can effectively intercept the very high-speed maneuverable target in the three-dimensional space. The integrated fuzzy type guidance law is explored for midcourse and terminal phases. Simulation results show that the integrated guidance scheme offers excellent tracking performance as well as performance robustness.
We also consider more stringent situations on the scenarios when the missile intercepts the ballistic target at higher altitude. We show that a conventional missile guidance system with only an aerodynamically controlled mechanism cannot effectively encounter a high-speed target. To overcome the difficulty due to insufficiently of aerodynamic control, a fuzzy-logic-based side force control mechanism, which is realized by two additional auxiliary thrusters, is proposed to offer additional transverse acceleration to the missile body. Numerical simulations also show that the auxiliary thruster can efficient improve the missile’s engagement performance and extend the defensible volume.
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