Active defense sight policy collaborative guidance law design method based on IMM filter

A design method and active defense technology, applied in design optimization/simulation, instrumentation, calculation, etc., can solve problems such as the reduction of guidance accuracy, achieve the effect of improving guidance accuracy and alleviating chattering

Active Publication Date: 2018-04-13
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to solve the problem in the prior art that the pursuer of the opponent intercepting aircraft will use different navigation constants in different guidance stages, resulting in changes in the motion model, which will reduce the guidance accuracy of the MMAE filtering method in this case, and propose Cooperative guidance law design method for active defense line-of-sight strategy based on IMM filter

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  • Active defense sight policy collaborative guidance law design method based on IMM filter
  • Active defense sight policy collaborative guidance law design method based on IMM filter
  • Active defense sight policy collaborative guidance law design method based on IMM filter

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specific Embodiment approach 1

[0028] Specific implementation mode one: a kind of IMM filter-based active defense line-of-sight strategy cooperative guidance law design method of this embodiment specific process is as follows:

[0029] Step 1: Establish a pursuer motion model;

[0030] The pursuer motion model includes the pursuer motion model relative to the evader and the pursuer motion model relative to the defender;

[0031] The pursuer is the opponent's intercepting aircraft, the evader is the target aircraft, and the defender is the aircraft protecting the evader;

[0032] Step one one, establish the relative motion equation of evader and pursuer and the relative motion equation of defender and pursuer;

[0033] Step 12, based on step 11, establish a pursuer motion model relative to the evader;

[0034] Step 13, based on step 1, establish a pursuer motion model relative to the defender;

[0035] Step 2. Based on the pursuer motion model established in step 1, design the IMM filter on the evader and...

specific Embodiment approach 2

[0042] Specific embodiment two: the difference between this embodiment and specific embodiment one is: the relative motion equation of evader and pursuer and the relative motion equation of defender and pursuer are established in the step one by one; the specific process is:

[0043] Define the scene inertial coordinate system OXY as the initial sight coordinate system of the aircraft evader; figure 1 It shows the relative motion relationship of evader, pursuer and defender on the plane.

[0044] Aircraft evader, opposing intercepting aircraft pursuer and aircraft defender protecting evader are denoted by e, p and d respectively;

[0045]The evader inertial coordinate system and the defender inertial coordinate system coincide with the scene inertial coordinate system; the origin and y-axis of the pursuer inertial coordinate system coincide with the scene coordinate system, and the x-axis direction of the pursuer inertial coordinate system is opposite to the x-axis direction ...

specific Embodiment approach 3

[0054] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is that: in the step one and two, based on the step one by one, the pursuiter motion model relative to the evader is established; the specific process is:

[0055] Suppose the pursuer uses PN guidance law to intercept the evader. We call the motion of the pursuer in this case the PN motion model. Let the pursuer state vector relative to the evader be

[0056] x e =[r x,e ,r y,e ,v x,e ,v y,e ,a px ,a py ] T (3)

[0057] where r x,e is the component of the relative position vector of the evader relative to the pursuer along the x-axis in the scene inertial coordinate system, r y,e is the component along the y-axis of the relative position vector of the evader relative to the pursuer in the scene inertial coordinate system; v x,e is the component of the relative velocity vector of the evader relative to the pursuer along the x-axis in the scene inertial coordi...

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Abstract

The invention discloses an active defense sight policy collaborative guidance law design method based on an IMM filter, relates to an active defense sight policy collaborative guidance law based on the IMM filter and aims at solving the problem that in the prior art, a motion model is changed and under the condition, the guidance precision of an MMAE filtering method is reduced due to the fact that a pursuer (opposite interception aircraft) employs different navigation constants in different guidance phases. The method comprises the steps of 1, establishing pursuer motion models; 2, designingthe IMM filter on an evader and a Kalman filter on a defender; and 3, establishing a super twisting sight guidance law based on the IMM filter. The method is applied to missile active defense guidancerate involved filed.

Description

technical field [0001] The invention relates to a cooperative guidance law of an active defense line of sight strategy based on an IMM filter. Background technique [0002] In the problem of aircraft defense penetration, improving the aircraft's defense penetration ability and reducing the probability of being intercepted by the opponent's defense aircraft is a problem of great significance. Since the aircraft flying according to the ballistic trajectory has poor maneuverability in the middle flight, it is easy to be intercepted by the opponent, so it is very important to study and improve the penetration ability of this type of aircraft. [0003] In order to improve the penetration capability of the aircraft, various methods such as electronic jamming, stealth technology, release of decoys, middle and terminal guidance, multi-warhead attack, and maneuvering orbit change are currently used. These methods can be attributed to passive defense techniques. In contrast, aircraf...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20
Inventor 邹昕光周荻
Owner HARBIN INST OF TECH
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