| Summary: | 博士 === 國防大學中正理工學院 === 國防科學研究所 === 95 === In the research of air defense of a missile system, a target with a very high speed and evasive motion, it requires to be aimed alignment for getting an effective interception remotely becoming future main trend of defensive art. The war territory of air defense missile system is an example one. Taiwan often faces the threat of the tactics ballistic missile from the China Communist Party, it needs to explore this question even more. Consider the movement way in which the guided missile attacked may take the terminal spiral orbit, in order to avoid the interception against the tactical missile. If it takes the traditional command of sight line in its terminal phase, even it can follow the G required of target evasively, but it should be limited by the precision problem and hard to extend to the far distance. If it use the commonly proportion guidance, although it can reach to the far distance, but it can't produce a desired lateral acceleration which are several times as much as the target’s acceleration for intercepting, these two methods can’t get the satisfied miss distance by its use alone.
This thesis proposes the method of improving command to line of sight, it designs the feasible hardware for guidance, it is verified by computer simulation subject to the target interception of the spiral orbit. This thesis produces some basic parameters for guidance system, it will contribute to the research and development work of the antiballistic missile with the result of study, also offer some beneficial new thinking.
The theory of this thesis is the analytic research of discussing emphatically the guided missile of TVM to intercept the ballistic missile, the proposed guidance method uses CLOS in terminal phase that has different with traditional TVM with CLOS, its difference for consult point from ground place move to the expected engagement point, and the ratio of speed of guided missile and target is decreasedfrom 1.5 to 0.7~0.5, and the scenario of engagement is head-on. It derived again on the thesis for general analysis of Locke law, Jalali-Naini law, Wen’s law, and Shoucri law of studying traditional CLOS, make it accord with truth that guided missile of TVM intercepts the ballistic missile at a high speed. This thesis is estimated under the assumed conditions for the best expectancy interception and the angle of intercepting, it can reach the most accurate and greatest energy when the engagement happens. It set the expected interception point as the original point in a Cartesian coordinate system, including give the engagement mathematics at war, utilize the analytical method to guide TVM-CLOS for interception conditions, trajectory characteristic, and guidance command.
Finally, this thesis uses two points geometry method and substitute into three points guidance to give the closed form solution of CLOS missile trajectory problems, such as interception area, trajectory characteristic, lateral acceleration demand, etc., it provides the characteristic of physics meaning and easy to manipulation. A series of simulation also illustrate the feasibility of the TVM-CLOS method for the interception of the trajectory target.
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