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Method for determining multi-state tracking guidance parameters

A guidance parameter, multi-state technology, applied in attitude control, non-electric variable control, altitude or depth control, etc., can solve problems such as inability to achieve decoupling control

Inactive Publication Date: 2016-08-17
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Since the control quantity and the state quantity are not exactly one-to-one correspondence, there is coupling and correlation between the multi-states, so decoupling control cannot be realized, which puts forward high requirements for the design of multi-state tracking guidance parameters
[0003] However, the prior art has not been able to provide a better method for determining multi-state tracking guidance parameters, so this problem needs to be solved urgently

Method used

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  • Method for determining multi-state tracking guidance parameters

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Embodiment Construction

[0045] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and examples.

[0046] This embodiment provides a method for determining multi-state tracking and guidance parameters, which is suitable for the guidance process of the gliding aircraft in the balanced gliding segment, thereby solving the design and coordination problems of multi-state tracking and guidance parameters, and providing guidance for the design of guidance parameters and gliding guidance. The realization provides design basis and support.

[0047] figure 1 It is a schematic flowchart of a method for determining multi-state tracking and guidance parameters in an embodiment of the present invention. Such as figure 1 As shown, the method for determining multi-state tracking guidance parameters in the embodiment of the present invention includes: .

[0048] ...

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Abstract

The invention discloses a method for determining multi-state tracking guidance parameters. The method includes the steps that a multi-state motion model of aircraft flight process reentry is established, small-deviation linear processing is carried out on the multi-state motion model, and a processed linear equation is obtained; based on the linear equation, a guidance equation is obtained; based on a linear quadratic regulator (LQR), an LQR tracking controller is designed, and a corresponding feedback control rule is obtained; according to the multi-state tracking requirement, a controller weighting matrix is selected; according to the controller weighting matrix and the guidance equation, the guidance parameters are obtained through calculation. By means of the method, tracking control over multiple state quantities can be achieved according to the determined guidance parameters, and mutual influences in tracking of multiple state quantities are reduced.

Description

technical field [0001] The invention relates to the technical field of lift aircraft guidance, in particular to a method for determining multi-state tracking guidance parameters. Background technique [0002] The lift aircraft is limited by various constraints such as overload, dynamic pressure, and heat flow at the stagnation point in the balanced gliding section. Therefore, its flight trajectory must meet the process and terminal constraints, and has high precision requirements. The guidance problem is a typical multi-input multi-output control problem. The input control quantity is two states: the roll angle and the attack angle. Considering the needs of the lift aircraft for large maneuvering tasks, the state quantities that need to be controlled are five Variables: altitude, speed, ballistic inclination, heading angle, lateral position. Since the control quantity and the state quantity are not exactly one-to-one correspondence, and there are couplings and correlations ...

Claims

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Application Information

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IPC IPC(8): G05D1/08G05D1/04G05D1/10G05D13/62
CPCG05D1/042G05D1/0825G05D1/105G05D13/62
Inventor 黄万伟杨业包为民马卫华祁振强吴浩刘毅郭涛梁禄扬徐国强
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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