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Guidance law for simultaneously attacking static target by multiple missiles based on proportional guidance law

A proportional guidance, multi-missile technology, applied in the field of guidance law, can solve problems such as limited time control, and achieve the effect of easy implementation and simple structure

Active Publication Date: 2021-03-30
NANJING UNIV OF SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, when the initial state of the multi-missile system cannot be obtained accurately, it will limit the use of time-limited control techniques

Method used

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  • Guidance law for simultaneously attacking static target by multiple missiles based on proportional guidance law
  • Guidance law for simultaneously attacking static target by multiple missiles based on proportional guidance law
  • Guidance law for simultaneously attacking static target by multiple missiles based on proportional guidance law

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Embodiment 1

[0045] The guidance law of the multi-missile attacking static target based on the proportional guidance law of the present invention, the steps are as follows:

[0046] Step 1: In the expression (1) of the remaining flight time of the missile, since the attacked target is a static target, the proportional coefficient N0 can be taken as 3, so Can be expressed as:

[0047]

[0048] In order to achieve the consistency of the whole projectile group, through such as image 3 The inter-missile network shown, each missile transmits the remaining flight time to the missile that has a network connection relationship with itself The consistency deviation is calculated by formula (2):

[0049]

[0050] where N i is the adjacent ammunition quantity set of the i-th missile, a ij is the connectivity coefficient, if the i-th missile can receive information from the j-th missile, then a ij =1, otherwise it is 0, there is no self-loop, that is, a ii =0.

[0051] Step 2: Judge th...

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Abstract

The invention discloses a guidance law for simultaneously attacking a static target by multiple missiles based on a proportional guidance law. The method comprises the steps that when n missiles simultaneously attack the same static target, r, V and phi of the i missile are obtained; then the consistency deviation xi<t,i> of the n missiles in the remaining flight time is obtained; whether theconsistency deviation xi<t,i>=0 is true or not is judged, and if yes, the current flight state of each missile is maintained; if not, the current consistency deviation xi<t,i> is input into the guidance law of fixed time convergence, and tangential control input a<n,i> and normal control input a<t,i> of a multi-missile system are obtained; and a missile kinetic model is established, r, V and phi at the next moment are obtained through the missile kinetic model, and the initial step is returned to. According to the method, by adding additional items, the situation that the convergence completion time of the system tends to be infinite due to the fact that the included angle between the missile flight direction and the missile visual line is 0 before the multi-missile system completes stateconsistency is avoided.

Description

technical field [0001] The invention belongs to the field of automatic cooperative control, and in particular relates to a proportional guidance law-based guidance law for multiple missiles to simultaneously attack a static 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 de...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B15/01
CPCF42B15/01
Inventor 戴可人于航李豪杰刘鹏张合马少杰
Owner NANJING UNIV OF SCI & TECH
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