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首页> 外文期刊>International Journal of Innovative Computing Information and Control >An adaptive reaching law based three-dimensional guidance laws for intercepting hypersonic vehicle
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An adaptive reaching law based three-dimensional guidance laws for intercepting hypersonic vehicle

机译：基于自适应到达律的三维制导律，用于拦截高超声速飞行器

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摘要

The interception of hypersonic vehicles is a formidable challenge due to its high speed and strong maneuverability; besides, traditional guidance methods cannot guarantee interception accuracy. To solve this problem, three-dimensional sliding mode guidance laws are proposed in this paper based on the head pursuit guidance method. The first guidance law ensures that the dynamic system converges to head pursuit guidance conditions in finite time without the knowledge of external disturbances, and can also weaken the chattering phenomenon. In practical application, the capacity of dynamic actuators is limited. Therefore, a guidance law with input saturation is proposed using the hyperbolic tangent function and auxiliary system. This method is novel in which the system can be ensured finite-time and asymptotically stable. In theory, the two guidance laws can be proved using Lyapunov stability theory. The correctness and effectiveness of the methods are verified by numerical simulations.
机译：高超声速飞行器的拦截由于其高速和强大的机动性是一个巨大的挑战。此外，传统的制导方法不能保证拦截的准确性。为了解决这个问题，本文提出了一种基于头部跟踪指导方法的三维滑模指导律。第一制导律确保动态系统在有限的时间内收敛到头部追踪的制导条件，而无需外部干扰，也可以减弱抖动现象。在实际应用中，动态执行器的能力是有限的。因此，利用双曲正切函数和辅助系统，提出了一种具有输入饱和度的制导律。该方法是新颖的，其中可以确保系统是有限时间的并且渐近稳定的。从理论上讲，这两个制导律可以用李雅普诺夫稳定性理论证明。通过数值仿真验证了该方法的正确性和有效性。

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