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| Engineering Design of Guidance Law for Intercepting Near Space Targets |
| ZHANG Jialiang1， LI Xinjie2， CAI Zhijun1， LIU Yiji1， LIANG Gu1 |
| 1. Shanghai Electro-Mechanical Engineering Institute， Shanghai 201109， China； 2. The First Military Representative Office of Air Force Equipment Department in Shanghai， Shanghai 201109， China |
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Abstract For the problem of early divergence of the guidance control loop when the missile intercepts near space targets, the impact of radome error slope is analyzed in this paper from perspective of engineering application. To reduce this impact, the compensation of effective navigation ratio is proposed, and the known time constant information of control loop is introduced into the design of guidance law. The guidance law is obtained by nonlinear inversion method. The simulation results show that the new guidance law can not only ensure the effective navigation ratio by suppressing the influence of radome error slope, but also delay the divergence of missile line of sight (LOS) angular speed by reducing the equivalent time constant of system dynamics, so as to improve the guidance accuracy of missile.
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Received: 24 February 2020
Published: 21 June 2021
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2021, Vol. 4 
