Three-dimensional guidance law based on adaptive integral sliding mode control

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• 作者：Junhong Song ^{hitsjh@163.com" class="auth_mail" title="E-mail the corresponding author}Author Vitae ; Shenmin Song ; ^{songshenmin@hit.edu.cn" class="auth_mail" title="E-mail the corresponding author}Author Vitae
• 关键词：Adaptive control ; Finite-time convergence ; Integral sliding mode control ; Missile ; Three-dimensional guidance law
• 刊名：Chinese Journal of Aeronautics
• 出版年：2016
• 出版时间：February 2016
• 年：2016
• 卷：29
• 期：1
• 页码：202-214
• 全文大小：2536 K

文摘

For the terminal guidance problem of missiles intercepting maneuvering targets in the three-dimensional space, the design of guidance laws for non-decoupling three-dimensional engagement geometry is studied. Firstly, by introducing a finite time integral sliding mode manifold, a novel guidance law based on the integral sliding mode control is presented with the target acceleration as a known bounded external disturbance. Then, an improved adaptive guidance law based on the integral sliding mode control without the information of the upper bound on the target acceleration is developed, where the upper bound of the target acceleration is estimated online by a designed adaptive law. The both presented guidance laws can make sure that the elevation angular rate of the line-of-sight and the azimuth angular rate of the line-of-sight converge to zero in finite time. In the end, the results of the guidance performance for the proposed guidance laws are presented by numerical simulations. Although the designed guidance laws are developed for the constant speed missiles, the simulation results for the time-varying speed missiles are also shown to further confirm the designed guidance laws.