Abstract
Recently, multiple constraints have been considered in the design of guidance laws. Most of the existing impact angle control guidance laws considering the seeker's field-of-view constraint are only applicable to constant speed missiles and have other limits to some extent. This paper is concerned with the field-of-view constrained impact angle control guidance law applied to variable speed missiles based on the sliding mode control theory. In the design of the sliding mode controller, we use a quadratic Lyapunov function to achieve the impact angle control. Moreover, we introduce an integral barrier Lyapunov function with an adaptive control item to address the field-of-view constraint and prevent the undesirable chattering caused by the disturbance of the nonlinear system. Then, the asymptotic stability of this close-looped system is verified. Eventually, numerical simulations are provided to demonstrate the performance of the proposed guidance law.
Highlights
In recent years, with the development of the high-tech industry, precision-guided missiles have become a significant trend for sophisticated weapons
Impact angle control guidance (IACG) laws presented in the previous literatures can be classified into three types: optimal control based IACG laws, proportional navigation guidance (PNG) based IACG laws and sliding mode control (SMC) based IACG laws
Ryoo et al presented a generalized formulation of optimal IACG laws in [2] and extended this formulation to a polynomial IACG law by minimizing the energy cost weighted by time-to-go power in [3]
Summary
With the development of the high-tech industry, precision-guided missiles have become a significant trend for sophisticated weapons. In [17], Wang et al proposed a SMC based guidance law considering the FOV constraint by using an integral barrier Lyapunov function to make the constrained state reach the sliding mode in finite time. The SMC based guidance laws proposed in [17]–[19] are verified to have perfect performance in achieving the impact angle control and addressing the FOV constraint, they are only designed for constant speed missiles. Taking the strap-down seeker missile as the research object, we derive a SMC based IACG law considering the seeker’s FOV constraint applied to variable speed missiles in this paper. We view this problem as a state-constrained stabilization problem of the nonlinear system.
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