Attack-time-constraint guidance-law design method of intercepting maneuvering target

A time-constrained, maneuvering target technology, applied in design optimization/simulation, computing, special data processing applications, etc., can solve the problem of less research, attack time-constrained guidance law cannot be effectively applied to intercept maneuvering targets, and reduce the robustness of the guidance system and other problems to achieve good robustness

Active Publication Date: 2018-08-17
BEIHANG UNIV
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Problems solved by technology

However, there are relatively few studies on guidance laws with attack time constraints, especially the design of attack time-constrained guidance laws for maneuvering targets
This is mainly due to the fact that the maneuverability of the target brings a series of uncertainties to the guidance system and guidance information, so that the attack time-constrained guidance law for stationary/constant m

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  • Attack-time-constraint guidance-law design method of intercepting maneuvering target

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Embodiment Construction

[0047] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only used as examples and are not intended to limit the present application.

[0048] like figure 1 As shown, the steps of the attack time constraint guidance law design method for intercepting a maneuvering target of the present invention are:

[0049] First, based on the two-dimensional geometric relationship between the missile and the maneuvering target (see figure 2 ), establish the relative kinematics and dynamics model of the missile and the maneuvering target, and obtain the second-order dynamic equation of the line-of-sight angle of the missile; secondly, design a quadratic function based on time, as the reference line-of-sight rotation rate that the missile needs to track, and determine the reference The relations...

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Abstract

The invention provides an attack-time-constraint guidance-law design method of intercepting a maneuvering target. The method comprises the steps of: obtaining a second-order dynamic equation of a line-of-sight angle of a missile; designing a time-based quadratic function to use the same as a reference line-of-sight rate which the missile needs to track; and adopting a sliding-mode control method to design a guidance law with an attack time constraint on the basis of the second-order dynamic equation of the line-of-sight angle. The design method of the invention is a reference line-of-sight rate-based sliding-mode guidance-law design method, designs the guidance law which has anti-interference performance, and is capable of quickly tracking the expected line-of-sight rate and precisely hitting the target, and realizes the constraint on attack time through adjusting parameters of the reference line-of-sight rate.

Description

technical field [0001] The present application relates to the field of missile guidance system design, in particular but not exclusively, to a method for designing an attack time-constrained guidance law for intercepting maneuvering targets, which is mainly applied to multiple anti-ship missiles to complete the saturated attack task on maneuvering targets. Background technique [0002] At present, with the development of close-up defense systems for large ships on the sea surface, it is very risky to use a single anti-ship missile to attack such targets, and it is easy to be intercepted or destroyed by the opponent's defense system. In response to this problem, an effective attack strategy is to implement a saturation attack of multiple anti-ship missiles on surface ships to restrict the defense system with limited coverage. The most critical technology to implement this saturation attack is to put forward requirements on the attack time of the missiles, so that multiple mis...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 胡庆雷韩拓郭雷王陈亮
Owner BEIHANG UNIV
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