Systems Engineering and Electronics ›› 2018, Vol. 40 ›› Issue (3): 609-614.doi: 10.3969/j.issn.1001-506X.2018.03.19

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Guidance law estimation and trajectory prediction of interceptor missile

HU Zhiheng1, ZHOU Di1, ZOU Xinguang2   

  1. 1. School of Astronautics, Harbin Institute of Technology, Harbin 150001, China; 2. School of Electrical Engineering and Automation, Harbin Institute of Technology, Harbin 150001, China
  • Online:2018-02-26 Published:2018-02-24

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Abstract:

Guidance law estimation and trajectory prediction of interceptor missile are discussed. The engagement model is established in three dimensions, whose state variables are ranges, range rates, interceptor accelerations and guidance coefficients. The observability condition of the system is deduced by using the nonlinear local weak observability theory. Then, an extended Kalman filter is designed based on the condition. Using the filter results as initial values, the interceptor future position is predicted by fourth-order Runge-Kutta method with a model of proportional navigation. Simulation results show that when the line-of-sight rate is large enough, the filter can estimate well and the prediction can meet the requirement of convergence and accuracy.

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