A Guidance Law Identification and Filtering Method for Proportional Guidance

A technology of proportional guidance and guidance law, applied in non-electric variable control, control/regulation system, three-dimensional position/course control, etc., can solve problems such as low estimation accuracy and inaccurate MMAE filter model, and achieve improved estimation accuracy Effect

Active Publication Date: 2018-04-24
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The existing method does not consider the above actual situation, which makes the MMAE filter model inaccurate and the estimation accuracy low. In view of the above problems, the present invention proposes a proportional guidance guidance law identification filtering method

Method used

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  • A Guidance Law Identification and Filtering Method for Proportional Guidance
  • A Guidance Law Identification and Filtering Method for Proportional Guidance
  • A Guidance Law Identification and Filtering Method for Proportional Guidance

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specific Embodiment approach 1

[0032] Specific implementation mode 1: A proportional guidance guidance law identification and filtering method in this implementation mode is specifically prepared according to the following steps:

[0033] Step 1: The pursuer has two motion models: the saturated motion model when the controller is saturated and the PN guidance law motion model when the controller is not saturated; establish the state equation of the PN guidance law motion model in the pitch plane, and the PN guidance law motion model in the The state equation of the yaw plane, the state equation of the controller saturation motion model in the pitch plane, and the state equation of the controller saturation motion model in the yaw plane; evader is a ballistic missile; pursuer is an intercept missile; PN guidance law is proportional guidance guidance law;

[0034] Step 2: According to the state equation of the PN guidance law motion model in the pitch plane in step 1, the state equation of the PN guidance law...

specific Embodiment approach 2

[0038] Embodiment 2: The difference between this embodiment and Embodiment 1 is that the pursuer in the step 1 has two motion models: a saturated motion model when the controller is saturated and a PN guidance law motion model when the controller is not saturated; Establish the state equation of the PN guidance law motion model in the pitch plane, the state equation of the PN guidance law motion model in the yaw plane, the state equation of the controller saturation motion model in the pitch plane, and the state equation of the controller saturation motion model in the yaw plane ; The specific process is:

[0039] In the missile penetration scenario, if the penetrating ballistic missile wants to evade the interception of the intercepting missile launched by the opponent’s missile defense system, it is the evader, called evader, and all physical quantities related to it contain the subscript e; the intercepting missile is the hunting party , called the pursuer, and all physical...

specific Embodiment approach 3

[0058] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is: in described step 2, according to the state equation of the PN guidance law motion model of step one in the pitch plane, the PN guidance law motion model in the yaw plane The state equation, the state equation of the controller saturation motion model in the pitch plane and the state equation of the controller saturation motion model in the yaw plane, calculate the state transition matrix of the PN guidance law motion model in the pitch plane, and the PN guidance law motion model in the yaw plane The state transition matrix of the plane, the state transition matrix of the controller saturation motion model in the pitch plane, and the state transition matrix of the controller saturation motion model in the yaw plane; the specific process is:

[0059] The state transition matrix of the PN guidance law motion model in the pitch plane is

[0060]

[0061]

[0062] ...

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Abstract

The invention relates to a proportion guide law recognition filtering method. The invention aims at solving problems that a conventional MMAE filer supposes that a model is not accurate because a PN guide law navigation constant is known and does not give consideration to the saturation condition of a pursuer controller, and the estimation precision is low. The method comprises the steps: firstly building state equations of PN guide law saturation and motion models in pitching and yam planes; secondly calculating a system state transfer matrix and designing a Kalman filter equation; thirdly calculating the posterior probabilities of the PN guide law motion and saturation motion models of a pursuer at the current moment; finally calculating the switching moment of the pursuer motion model according to the posterior probabilities, employing the estimation result of the saturation motion model Kalman filter equation, or else, employing the estimation result of a PN guide law motion Kalman filter equation. The method is suitable for the field of spaceflight.

Description

technical field [0001] The invention relates to a proportional guidance guidance law identification and filtering method. Background technique [0002] In the application of extra-atmospheric ballistic missile penetration, in order to improve the ballistic penetration capability, ballistic missiles can release defensive missiles outside the atmosphere to accompany them at the same speed. When the defensive missile finds the intercepting missile, the collision with it is controlled by the guidance law, thereby increasing the penetration probability of the ballistic missile. The optimal evasion strategy for ballistic missiles and the optimal guidance law for defensive missiles both assume that the guidance law for intercepting missiles is known. Although the maneuvering of the interceptor missile can be treated as an unknown external disturbance based on the sliding mode control guidance law, if the acceleration of the interceptor missile can be estimated, the performance of ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/10
CPCG05D1/107
Inventor 邹昕光周荻朱蕊蘋
Owner HARBIN INST OF TECH
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