Abstract
In recent years, the strapdown system has become the significant trend of the development of precision guided weapons. In order to effectively hit the lightly armored targets, researchers have done a series of studies on the impact angle control. However, most of them ignored the field-of-view constraint of the strapdown seeker. The existing impact angle control guidance laws with the field-of-view constraint have obvious drawbacks to some extent. For example, most of them are only applicable against nonmaneuvering targets and some of them suffer sudden hopping of guidance command due to the use of switching logic. Taking the strapdown seeker missile as the research object, this paper studies the field-of-view constrained impact angle control guidance problem against stationary targets, constant speed targets and maneuvering targets. According to the sliding mode control theory, two kinds of sliding surfaces are designed to make the missile achieve high precision attack under a desired impact angle within the field-of-view constraint. A quadratic barrier Lyapunov function and a logarithm barrier Lyapunov function are used to guarantee that the sliding surfaces designed for the impact angle constraint and the field-of-view constraint can converge to zero in finite time respectively. Then, a nonlinear extended state observer is proposed to estimate the unmeasurable disturbance of the system and alleviate the undesirable chattering by compensating it with the estimation of the disturbance. Finally, the feasibility of the proposed law is verified by numerical simulations.
Highlights
Precision guided weapons appear under the demand of modern war
In order to solve this problem, we propose a FOV constrained impact angle control guidance (IACG) law based on the sliding mode control (SMC) theory, VOLUME 8, 2020 which can steer the missile to strike the target with zero miss distance under the desired impact angle rapidly without violating the FOV constraint during the whole reaching phase
Qe and Vq are selected as the state variables to construct the state equations, and this problem is converted into a stabilization problem of a nonlinear system with state constrained
Summary
Precision guided weapons appear under the demand of modern war. In order to improve the damage effect of the missile, multiple constraints should be considered in the design of guidance laws. Researchers have done a series of studies on the impact angle control in order to enable the missile to hit weak points of the target and enhance the lethality of warheads to the most extent. There exist numerous studies on the impact angle control guidance (IACG) law, including three main categories. The first one is based on the optimal control theory [1]–[3]. Kim et al proposed a suboptimal guidance based IACG law for the reentry vehicle in [1], which is the first attempt to solve this problem.
Sign-in/Register to view highlights & summary Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
