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A Constrained Medium Guidance Ballistic Optimization Method

An optimization method and ballistic technology, applied in the direction of guidance methods, offensive equipment, weapon accessories, etc., can solve the problems of mid-terminal guidance failure and other problems, and achieve the effect of improving the interception accuracy.

Active Publication Date: 2021-10-12
AIR FORCE UNIV PLA
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Problems solved by technology

[0004] Aiming at the problem of failure of mid-to-terminal guidance handover caused by excessive relative speed when intercepting high-speed targets, the present invention provides a constraint-based medium-to-terminal guidance ballistic trajectory optimization method. The terminal guidance flight state improves the interception accuracy

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  • A Constrained Medium Guidance Ballistic Optimization Method
  • A Constrained Medium Guidance Ballistic Optimization Method
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Embodiment Construction

[0062] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0063] The present invention provides a method for optimizing the mid-guidance trajectory with constraints. The trajectory optimization method is used to reduce the transition speed of the mid-term guidance of the interceptor bomb. The method comprises the following steps:

[0064] S1. According to the set mid-guidance optimized trajectory with constraints, establish the full trajectory motion equation of the interceptor missile in the longitudinal plane including trajectory constraints and terminal constraints, and construct the trajectory optimization model of the interceptor missile.

[0065] In...

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Abstract

The invention discloses a trajectory optimization method with constraints for intermediate guidance. The trajectory optimization method is used to reduce the transition speed of the terminal guidance of interceptors. The method includes the following steps: optimizing the trajectory according to the set intermediate guidance with constraints , establish the full trajectory motion equation of the interceptor missile in the longitudinal plane including trajectory constraints and terminal constraints, and construct the trajectory optimization model of the interceptor missile; use the hp adaptive pseudospectral method to solve and optimize the trajectory. The invention can reduce the transition speed of the terminal guidance of the interceptor bomb, provide a good flight state of the terminal guidance, and improve the interception accuracy, and is a very promising ballistic mode.

Description

technical field [0001] The invention belongs to the field of ballistic optimization of missiles, in particular to a method for optimizing ballistics of intermediate guidance with constraints. Background technique [0002] When traditional interceptors face high-speed targets, they are limited by the performance of missile time constants, steering gear response time, and guidance control system response speed. If the relative speed is too high, it will lead to the failure of the mid-to-terminal guidance shift; even if the shift is successful, Guidance accuracy is bound to decrease, thereby affecting interception effectiveness. [0003] In view of the characteristics of large flight span and obvious characteristics of high-speed targets, the flight trajectory of the interceptor missile in the guidance stage can be optimized. By designing the climbing trajectory, gravity can be used to reduce the speed of the interceptor missile flying to the handover area, thereby reducing the...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F41G3/00
CPCF41G3/00
Inventor 伍友利杨鹏飞郑垚宇张丹旭彭维仕徐洋董昕瑜
Owner AIR FORCE UNIV PLA
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