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A control method for anti-crosswind landing of flying-wing UAV with small aspect ratio

A technology with small aspect ratio and control method, applied in attitude control, control/adjustment system, non-electric variable control, etc., can solve the problem of weak heading control ability, difficulty in quickly aligning the nose with the runway, and unsatisfactory crosswind landing process etc. to achieve high feedback gain, increased control accuracy and rapid response

Active Publication Date: 2022-07-15
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the flying-wing layout aircraft, especially the small-aspect-ratio flying-wing aircraft, the heading control ability is weak. If the above method is still used, it is difficult to quickly align the nose with the runway when approaching the ground, and the crosswind landing process is not ideal.

Method used

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  • A control method for anti-crosswind landing of flying-wing UAV with small aspect ratio

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Experimental program
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Effect test

Embodiment 1

[0025] like figure 1 As shown in the figure, a control method for anti-crosswind landing of a flying-wing UAV with a small aspect ratio is characterized by comprising the following steps:

[0026] a, Heading stabilization and control, the difference between heading stabilization and general heading stabilization is that the feedback from the sideslip angle to the resistance rudder has a cleaning network F1, and sideslip is introduced in the flight control to eliminate the adverse control effects caused by the coupled signal , in the feedback process, the cleaning network is applied to filter the signal, and the formula is as follows:

[0027] Dr=K r *r+F1*K β *β+[K ψ *△ψ+K ψ’ *∫△ψdt]

[0028] Among them, Dr: rudder out of rudder, r: yaw angle rate, β: sideslip angle, ψ: yaw angle, F1: cleaning network, filter architecture is s / (Ts+1), K: control parameter, △ψ : The difference between the yaw angle and the given value.

[0029] b, Lateral deviation control, using PID con...

Embodiment 2

[0043] A control method for anti-crosswind landing of a flying-wing UAV with a small aspect ratio, which is characterized by comprising the following steps:

[0044] a, Heading stabilization and control, the difference between heading stabilization and general heading stabilization is that the feedback from the sideslip angle to the resistance rudder has a cleaning network F1;

[0045] working process:

[0046]Brief description of control mechanism: UAV with flying-wing layout is statically unstable in lateral heading control in terms of body characteristics. Because there is no vertical tail, it cannot fly downwind after being disturbed by wind, and the aircraft moves in reverse, so sideslip is introduced in flight control. , to enhance the robustness of the aircraft. At the same time, due to the differential control of multiple rudder surfaces of the aircraft, there is coupling in the control signal. In order to eliminate the adverse control effect caused by the coupled sig...

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Abstract

The invention discloses a control method for anti-crosswind landing of a flying-wing UAV with a small aspect ratio, comprising the following steps: a, heading stabilization and control. The feedback of the resistance rudder has a cleaning network F1; b, the lateral deviation control, using the PID controller, when the crosswind exists, the controller gradually establishes a roll angle through the integral link; c, the roll angle control, at 1.5 At the height of m, before the main wheel touches the ground, the lateral control is converted from the lateral deviation control to the roll angle control through the switch S1. The roll angle and lateral deviation control are converted into roll angle control, so that when the small aspect ratio flying-wing UAV is landing in a crosswind, when it is close to the ground, the nose is quickly aligned with the runway, which is conducive to the crosswind landing. Able to automatically land safely.

Description

technical field [0001] The invention belongs to the technical field of UAV flight control, in particular to a control method for crosswind-resistant landing of a flying-wing UAV with a small aspect ratio. Background technique [0002] Landing anti-crosswind control is one of the key technologies of UAV autonomous landing technology. Conventional layout UAVs generally use no sideslip method for crosswind landing, that is, the nose is deviated from the runway direction to align with the incoming flow direction in the sliding phase. When approaching the ground, perform anti-bias flow control and quickly straighten the nose to align the nose with the runway. Due to the flying-wing layout, especially the small aspect ratio flying-wing aircraft, the heading control ability is weak. If the above method is still used, it is difficult to quickly align the nose to the runway when approaching the ground, and the crosswind landing process is not ideal. SUMMARY OF THE INVENTION [000...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0816G05D1/101
Inventor 胡羲陈伟金波张瞿辉
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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