Missile guidance law for simultaneously attacking maneuvering target by multiple missiles

A technology of maneuvering targets and multiple missiles, applied in the field of missile guidance laws, can solve problems such as limited applications, and achieve the effects of easy algorithm, fast response and robustness, and simple structure

Active Publication Date: 2021-05-18
NANJING UNIV OF SCI & TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, for finite-time control techniques, the stabilization time of the control system is clearly related to the initial state of the system, which limits the application of this technique to situations where the initial state is not available

Method used

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  • Missile guidance law for simultaneously attacking maneuvering target by multiple missiles
  • Missile guidance law for simultaneously attacking maneuvering target by multiple missiles
  • Missile guidance law for simultaneously attacking maneuvering target by multiple missiles

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Embodiment 1

[0057] Step 1: When 5 missiles attack the same moving target at the same time, in order to study the flight state of each missile, take the i-th missile as the research object. Assume that the on-board sensor of the i-th missile detects the distance r from the target i , own motion speed V i , heading angle λ i , and projectile viewing angle γ i , the target velocity V T and the angle φ between the target flight direction and the projectile line of sight direction T ,;according to figure 2 The missile dynamics relation shown (V r,i =V T cosφ T -V i cos(γ i -λ i ), V q,i =V T sinφ T -V i sin(γ i -λ i )), the relative velocity V along the direction perpendicular to the projectile line of sight can be obtained r,i with V q,i . Then the distance r from each missile to the target i , the relative velocity V along the projectile line of sight r,i , to obtain the consistency deviation ξ of 5 missiles r,i , ξ Vr,i , i=1,2,...,5; go to step 2;

[0058] In order...

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Abstract

The invention discloses a missile guidance law for simultaneously attacking a maneuvering target by multiple missiles, and aims to provide a guidance law for the missiles when the multiple missiles attack the maneuvering target, wherein the stabilization time of the guidance law does not depend on initial conditions of a system. In order to realize rapid response and robustness of the system, a non-singular rapid terminal sliding mode surface with fixed time convergence is designed, and the sliding mode surface has the characteristic of rapid convergence of a traditional terminal sliding mode and also has non-singular property. According to the designed sliding mode surface, the guidance laws which converge in the fixed time direction and the direction perpendicular to the missile visual line direction are constructed, two guide law design parameters are mutually independent, the parameters can be matched according to system performance requirements, a saturation function is introduced into the guidance law to avoid system buffeting, and the guidance law is simple in structure and easy to achieve.

Description

technical field [0001] The invention belongs to the field of automatic coordinated control, and in particular relates to a missile guidance law used for multiple missiles to simultaneously attack a maneuvering target. Background technique [0002] With the development of military technology, more and more important targets are equipped with anti-missile defense systems such as short-range weapon systems to improve defense capabilities. Due to the existence of the defense system, for the traditional single missile attack strategy, the defense system is easy to intercept the attacker's missile, which will seriously affect the success rate and reliability of the target attack. Therefore, in order to break through the defense system, it is necessary to develop missiles with high static performance, so as to improve the success rate of attacking the target. However, the cost and technical requirements of such high-static missiles are very high, which hinders the development of a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B15/01
CPCF42B15/01
Inventor 张合于航刘鹏戴可人李豪杰马少杰
Owner NANJING UNIV OF SCI & TECH
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