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A Variable Parameter Guidance Method with Large Fall Angle Constraint Based on Measurement Information

A technology for measuring information and falling angle, applied in the field of guided aircraft, can solve the problems that the project cannot be realized, and the adaptive change of the parameters of the guidance law is not considered, so as to achieve the effect of improving the fault tolerance of information

Active Publication Date: 2021-10-29
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the existing guidance law design methods usually require additional information such as remaining time information, which cannot be realized in engineering, and does not consider the adaptive change of guidance law parameters when the flight altitude changes

Method used

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  • A Variable Parameter Guidance Method with Large Fall Angle Constraint Based on Measurement Information
  • A Variable Parameter Guidance Method with Large Fall Angle Constraint Based on Measurement Information
  • A Variable Parameter Guidance Method with Large Fall Angle Constraint Based on Measurement Information

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Experimental program
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Effect test

Embodiment 1

[0086] An adaptive variable structure terminal guidance method with drop angle constraints based on measurement information, the implementation method is as follows figure 1 As shown, the specific implementation steps are as follows:

[0087] 1. Taking the air-to-ground strike guided aircraft as an example, the implementation process of the present invention is introduced. It is known that the altitude of the target point is 1000m, the target is located at a horizontal distance of 12000m from the guided aircraft, and the expected fall angle is -70°. The two methods shown in Table 1 are used for comparison.

[0088] Table 1 Serving Conditions

[0089]

[0090]

[0091] 2. Use the integrated navigation system to measure the velocity V of the missile in three directions in the navigation coordinate system in real time e ,V n ,V s , position x n ,y n ,z n , yaw angle Pitch angle and roll angle γ.

[0092] 3. Utilize the real-time measurement of missile position, ...

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Abstract

The invention relates to the technical field of guided aircraft, in particular to a guidance method with drop angle constraints and variable parameters based on measurement information. The object of the present invention is to propose a method of self-adaptive variable structure terminal guidance with drop angle constraints based on measurement information, which is based on the relative line-of-sight angular velocity information measured by the seeker and the position, velocity and attitude information of the missile measured by inertial navigation , combined with the preset and real-time adjustment parameters, the normal overload command is calculated to ensure the guidance accuracy and the fall angle constraint at the same time, so as to realize the efficient damage and directional guidance of the guided aircraft.

Description

technical field [0001] The invention relates to the technical field of guided aircraft, in particular to a guidance method with drop angle constraints and variable parameters based on measurement information. Background technique [0002] With the continuous improvement of air-to-ground strike capabilities, countries and regions around the world have generally adopted deep-buried and reinforced defense measures in order to further improve the defense capabilities of high-value military targets. The ability is obviously insufficient. For example, during the Gulf War, the U.S. military had to solve the problem of attacking military targets that were defended under reinforced concrete above 6 meters or under clay above 30 meters. The confrontation and ebb and flow of offensive and defensive capabilities urgently require our military to continuously enrich its strike methods and enhance its strike capabilities, especially the ability to precisely strike the enemy's solid and de...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/10G05B13/04F42B15/01
CPCF42B15/01G05B13/042G05D1/101G05D1/105
Inventor 刘永善刘俊辉单家元贾庆忠丁艳
Owner BEIJING INSTITUTE OF TECHNOLOGYGY