| Summary: | 博士 === 中正理工學院 === 國防科學研究所 === 88 === Proportional navigation guidance law (PNG) has been widely employed in the guidance design of air-to-air homing missiles for its simplicity, efficiency, robustness and ease of implementation. The lateral acceleration command generated by PNG is proportional to the line of sight rate. While dealing with highly maneuvering targets, the lateral acceleration command increases with time and almost saturates in the final phase of engagement. Therefore, PNG induces large miss distances and then the target has an opportunity to escape. Taking some evasive tactics at some time, the target can evade the missile attack and survive.
The study is organized by two parts. First, we used more realistic 2D and 3D missile models and simulate some evasion tactics such as maximum G turn, jink, S turn and barrel roll against the PNG guided missiles. In addition, we presented a suggestion to show how to perform the evasive tactics. Second, Since proportional navigation guidance law can not cope with the highly maneuvering targets such as thrust-vector controlled fighter, the study presented two kinds of new guidance laws to improve the weakness of PNG. Both of the guidance laws, based on the optimal control theory choosing the different state variables and control variables, were derived here. The resulting guidance laws are time-minimum and control energy-minimum. Simulation results show that both of the guidance laws produce less miss distance and less interception time than the conventional proportional navigation guidance laws. They will be the promising candidates of future guidance law design.
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