Abstract
Terminal guidance law for missiles intercepting high maneuvering targets considering the limited available acceleration and autopilot dynamics of interceptor is investigated. Conventional guidance laws based on adaptive sliding mode control theory were designed to intercept a maneuvering target. However, they demand a large acceleration for interceptor at the end of the terminal guidance, which may have acceleration saturation especially when the target acceleration is close to the available acceleration of interceptor. In this paper, a terminal guidance law considering the available acceleration and autopilot dynamics of interceptor is proposed. Then, a fuzzy system is utilized to approximate and replace the variable structure term, which can handle the unknown target acceleration. And an adaptive neural network system is adopted to compensate the effects caused by the designed overlarge acceleration of interceptor such that the interceptor with small available acceleration can intercept the high maneuvering target. Simulation results show that the guidance law with available acceleration and autopilot dynamics (AAADG) is highly effective for reducing the acceleration command and achieving a small final miss distance.
Highlights
In recent years, the hypersonic flight vehicles with high maneuverabilities have been widely developed [1]
The widely used proportional navigation guidance (PNG) law [2, 3] and its variants [4,5,6,7,8] would fail to satisfy the requirement of high accuracy for the task of intercepting the hypersonic flight vehicles with high maneuverabilities [9]
To guarantee a good performance of the guidance system when the missile intercepts the hypersonic flight vehicle with a high maneuverability, the gain of switching term needs to be chosen larger than the upper bound of target acceleration, which is hard to choose in advance and will cause the chattering problem
Summary
The hypersonic flight vehicles with high maneuverabilities have been widely developed [1]. Li et al [28] took both the autopilot dynamics and uncertainties into consideration and proposed a finite-time-convergent guidance law to intercept a maneuvering target. To guarantee a good performance of the guidance system when the missile intercepts the hypersonic flight vehicle with a high maneuverability, the gain of switching term needs to be chosen larger than the upper bound of target acceleration, which is hard to choose in advance and will cause the chattering problem. A sliding mode guidance law considering the available acceleration and autopilot dynamics of missile for intercepting a high maneuvering target is proposed. At last, compared with proportional navigation guidance (PNG) and finite-time convergence guidance (FTCG), simulation results demonstrate the effectiveness of AAADG
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