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研究了一种用于拦截卫星的中制导和末制导方法。首先在已有卫星运行轨道上适当选择一点作为预定拦截点。拦截飞行器先采取垂直上升,然后进入中制导过程,采用Lambert制导中的最小能量策略,将其导入一个含预定拦截点的椭圆轨道,直到拦截飞行器上的导引头捕获并持续跟踪目标时转入末制导,末制导过程选用滑模变结构制导律进行控制。最后对设计的制导方法进行仿真分析,验证了该方法的正确性和有效性。
A mid-level and final guidance method for intercepting satellites was studied. Firstly, select a suitable point on the existing satellite orbit as a predetermined interception point. The interceptor vehicle first takes a vertical ascent and then enters the mid-course guidance process, using the Lambert guidance’s minimum energy strategy, introducing it into an elliptical orbit with a predetermined intercept point until the interceptor’s seeker captures and continuously tracks the target Terminal guidance, guidance system selection sliding mode variable structure guidance law to control. Finally, the guidance method of the design is simulated and analyzed to verify the correctness and effectiveness of the method.