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A Control Method for Multi-Missile Cooperative Operation

A technology of multiple missiles and control methods, applied in the field of guidance

Active Publication Date: 2014-10-15
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the problem of simultaneously enhancing the defense penetration capability and the target strike capability during multi-missile coordinated operations

Method used

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  • A Control Method for Multi-Missile Cooperative Operation
  • A Control Method for Multi-Missile Cooperative Operation
  • A Control Method for Multi-Missile Cooperative Operation

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Embodiment Construction

[0093] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0094] At present, in the field of multi-missile cooperative combat research, how to control the missiles to achieve position coordination, attack time and attack angle coordination, and attack speed coordination in the process of attacking the target is the key to improving the missile's penetration capability and enhancing the missile's ability to target. important issue of strike capability.

[0095]In the present invention: firstly, a virtual guide point is introduced for each guided missile in cooperative operation, and the arc motion track of the guide point is designed. Then, aiming at the requirements of missile coordinated operations: during the attack process, several missiles approach the target synchronously; at the end of the attack, several missiles hit the target at the same time from different angles at the required speed, and...

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Abstract

The invention provides a method for controlling coordinated operation of multiple missiles, which can accurately control the position, attack time, attack angle and attack velocity of each of the multiple missiles. The method comprises the following steps: selecting one missile from the multiple missiles to serve as a driving missile, and defining the rest missiles as driven missiles; assigning a virtual lead point to the driving missile as well as each of the driven missiles, and designing the path of motion of each lead point; determining the law of motion of the lead points in an arc coordinate system; establishing a model of relative motion of missiles and the lead points; designing the relative distances xr, yr and zr between the missles and the virtual lead points according to the needs of the missiles for cooperation in terms of position, attack angle and attack velocity; and designing a tracking controller based on the relative kinetics theory and allowing the missiles to fly in a way of tracking the virtual lead points with the designed relative distances, so as to perform coordinated operation. The method has the advantages of convenience in application and flexibility in use and has broad application prospects in the military field.

Description

technical field [0001] The invention relates to a method for realizing coordination of flight position, attack time, attack angle and attack speed when controlling a plurality of missiles for coordinated operations, and belongs to the field of guidance technology. Background technique [0002] With the development of science and technology, the main weapons on the modern battlefield are no longer conventional guns, but various precision-guided weapons with multi-platform and coordinated operations. Multi-missile coordinated operations overcome the shortcomings of traditional single-missile operations that cannot meet the requirements of multi-system and multi-system confrontation operations in modern warfare. It is one of the development directions of future missiles. [0003] In the process of multi-missile coordinated operations, position coordination can enhance its defense penetration capability, and simultaneously hitting the target from different angles with an ideal a...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F42B15/01
Inventor 王晓芳郑艺裕林海
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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