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Rolling aircraft control method based on isolation online compensation

A control method and aircraft technology, applied in vehicle position/route/altitude control, attitude control, control/adjustment system, etc., can solve the problem of reducing the stability and guidance accuracy of the guidance system, untargeted solutions, and target line of sight Angular velocity error and other issues

Pending Publication Date: 2022-05-27
BEIJING INSTITUTE OF TECHNOLOGYGY +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] During the flight of the rolling aircraft, the attitude disturbance of the aircraft will be partially coupled to the seeker, so that there is an error in the output target line-of-sight angular velocity, which reduces the stability and guidance accuracy of the guidance system; The main factor of the disturbance torque loop is the disturbance torque loop, and the isolation degree caused by the online compensation disturbance torque loop of the rolling aircraft has not yet been targeted.

Method used

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  • Rolling aircraft control method based on isolation online compensation
  • Rolling aircraft control method based on isolation online compensation
  • Rolling aircraft control method based on isolation online compensation

Examples

Experimental program
Comparison scheme
Effect test

experiment example 1

[0090] Set the disturbance angular acceleration e as the amplitude A=1.5° / s 2 , a sinusoidal disturbance signal with frequency ω=1rad / s, K 1 =14,K 2 =123,k g = 1, R = 8Ω, K T =0.2344N·m·A -1 , J=0.002kg·m 2 .

[0091] Formula (1), formula (2) and formula (3) are used to compensate the line-of-sight angular velocity of the seeker,

[0092]

[0093] z 0 ,z 1 ,z 2 , v 0 and v 1 Both are intermediate variables with no specific physical meaning, means z 0 the derivative of , means z 1 the derivative of , means z 2 derivative of

[0094] y represents the input volume,

[0095] u Δ Indicates the armature voltage obtained by real-time measurement. In the experiment, the module is built by matlab / simulink for simulation, that is, U Δ The measured value is given by the module in real time;

[0096] λ 0 =10,λ 1 =14,λ 2 =19, L=4.

[0097] Calculate formula (1) multiple times in a row, when the obtained z 1 When it converges stably, the fixed value to whic...

experiment example 2

[0103] Set the target as a ground target with variable speed, and its trajectory is as follows Figure 4 and Figure 5 As shown by the solid line in , the launching aircraft is flying towards the target, and the aircraft is controlled by a rolling aircraft control method based on online compensation of isolation, specifically including the following steps:

[0104] Step 1. Use the drone to emit laser light to illuminate the target,

[0105] Step 2: Receive the laser signal diffusely reflected by the target through the laser seeker on the aircraft, and then obtain the measured target line-of-sight angular velocity information,

[0106] Step 3, correcting the measured target line-of-sight angular velocity information by compensating the isolation degree to obtain accurate target line-of-sight angular velocity information,

[0107] Step 4, based on the accurate target line-of-sight angular velocity information, control the aircraft through the proportional guidance guidance law. ...

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Abstract

The invention discloses a rolling aircraft control method based on isolation online compensation, and the method comprises the steps: obtaining a stable convergence value through continuous calculation, obtaining an interference angular acceleration caused by an interference torque, and carrying out the compensation of a sight angular velocity outputted by a platform seeker in real time on the basis, thereby achieving the real-time compensation of the sight angular velocity. And a more accurate target line-of-sight angular velocity is obtained, and an overload instruction is generated accordingly.

Description

technical field [0001] The invention relates to the field of aircraft guidance and control, in particular to a rolling aircraft control method based on isolation degree online compensation. Background technique [0002] In engineering practice, the common structure of the roll aircraft seeker is a platform seeker, whose function is to ensure the stability of the seeker's optical axis in space, and to complete the search, capture and tracking of the target. The single-channel control loop of the seeker system on the actual platform includes back electromotive force loop, disturbance torque loop, stability loop and tracking loop. The counter electromotive force circuit is generated due to the electromagnetic effect. During the rotation of the motor, the rotor cuts the magnetic force line, and generates an electromotive force opposite to the motor driving voltage; the disturbance torque circuit is caused by the pull of the wire and friction during the rotation of the platform s...

Claims

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Application Information

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IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0808G05D1/101
Inventor 王辉李涛林德福王伟王江宋韬轩永波袁亦方李玥婷王亚宁刘佳琪王治霖
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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