Abstract
This thesis studies the problem of three-dimensional guidance considering maneuvering acceleration and input saturation based on the background of missile intercepting maneuvering target. On the basis of the three-dimensional guidance model with impact angle constraints, a three-dimensional guidance law is designed by using the integral sliding mode control and adaptive control. To solve the problem of input saturation, an adaptive anti-saturation integral sliding mode three-dimensional guidance law is designed by introducing an auxiliary system. The stability of the designed guidance law is proved by Lyapunov theory, which ensures that the sliding mode manifold converges to zero in finite time. The effectiveness of the designed guidance law is verified by simulation analysis.
Highlights
With the complexity of the war environment and the increasing improvement of the performance of high maneuvering targets, the missile has the ability to intercept air maneuvering targets [1]
In [22,23], by introducing an adaptive algorithm to estimate the upper bound of target acceleration online, an adaptive threedimensional guidance law with acceleration constraint is designed by using adaptive algorithm and dynamic control method, but the state of the guidance system can only be guaranteed to be uniformly bounded
(3) Compared with [15], this paper considers input saturation and finite time stability, which is of more practical engineering significance
Summary
With the complexity of the war environment and the increasing improvement of the performance of high maneuvering targets, the missile has the ability to intercept air maneuvering targets [1]. In order to achieve the best damage effect, a three-dimensional proportional guidance law with angle constraint is designed for the relative motion model of three-dimensional missile and target [5,6]. In [10,11], based on the sliding mode control theory, an adaptive sliding mode guidance law with impact angle constraints is designed. In [14], the linear sliding mode three-dimensional guidance law with impact angle constraints and terminal sliding mode three-dimensional guidance law are designed for maneuvering target interception. In [15], an adaptive terminal sliding mode guidance law with impact angle constraints is designed for intercepting maneuvering targets based on adaptive control and nonsingular terminal sliding mode control theory. A terminal sliding mode 3D guidance strategy with impact angle constraints is designed based on the integral terminal sliding mode theory and adaptive. Combining and (9), the threedimensional guidance system described as follows x F Bu+D (10)
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