A data-link end-of-link guidance method for seeker failure mode
A failure mode, seeker technology, applied in direction control systems, offensive equipment, projectiles, etc., can solve problems such as seeker failure, missile failure, inability to calculate guidance commands, and avoid huge losses.
Active Publication Date: 2021-07-20
中国北方工业有限公司
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Problems solved by technology
[0004] The present invention provides a data link end guidance method aimed at the failure mode of the seeker, and the technical problems to be solved are: the problem that the guidance command cannot be calculated due to the failure of the seeker; failure problem
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[0014] In order to make the purpose, content and advantages of the present invention clearer, the specific implementation manners of the present invention will be further described in detail below.
[0015] A kind of end-of-data-link guidance method for the seeker failure mode proposed by the present invention comprises the following steps:
[0016] S1. Use the medium guidance data link and missile navigation information to calculate the relative distance of the projectile and target, and judge whether the seeker is invalid. When the seeker is in an invalid state, send the failure flag to the launch platform according to the missile:
[0017] (a) Determine the position and velocity of the missile and the target in the line-of-sight coordinate system, and calculate the relative distance between the missile and the target
[0018] (b) When the projectile relative distance When it is less than the interception distance R of the seeker, the delay is 1s, the seeker sends the in...
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The present invention relates to a data link terminal guidance method in the seeker failure mode, which firstly judges the failure of the seeker; confirms the failure of the seeker, and switches the intermediate guidance data link to the terminal guidance matching the update cycle of the seeker in real time Data link; the missile flight control computer detects and corrects the position and velocity of the target in the line-of-sight coordinate system in real time in the terminal guidance data link; solves the line-of-sight angular velocity in the line-of-sight coordinate system and the overload command in the missile body coordinate system. The invention utilizes the motion information state of the target transmitted by the terminal guidance data link with a high update rate to guide and control the missile whose seeker fails, and avoids the problem that the guidance command cannot be calculated due to the failure of the seeker. The calculation is performed through the information of the data link to make it conform to the guidance law, and the failed missiles can be used to avoid the huge loss of missile scrapping, which brings good results.
Description
technical field [0001] The invention belongs to the technical field of guidance control, and in particular relates to a data link end guidance method for a seeker failure mode, which is suitable for intercepting high-speed and large maneuvering targets in the air. Background technique [0002] Brand-new weapons and equipment and battlefield information environment have led to a brand-new combat mode, which indicates that the combat methods of modern warfare will undergo fundamental changes. Driven by information technology, the form of warfare is changing from mechanized warfare to informationized warfare, and the transformation from platform-centric to network-centric is a fundamental change in the military field under the background of informationized warfare. In the modern warfare environment characterized by informatization, tactical missiles will be subject to a variety of compound interferences such as infrared or electromagnetic. Under the constraints and influence of...
Claims
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IPC IPC(8): F42B15/01F41G7/00
CPCF41G7/008F42B15/01
Inventor 梁晓庚马英男罗绪涛张浩强
Owner 中国北方工业有限公司