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Method for inhibiting rocking movement of aerofoil of wing body assembly by using artificial perturbation of tip part

A composite, artificial technique used in aerospace to solve problems such as no-wing rock research

Inactive Publication Date: 2012-02-22
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, experts and scholars at home and abroad have not studied the flow of this type of wing rock and the method of suppressing this type of rock motion.

Method used

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  • Method for inhibiting rocking movement of aerofoil of wing body assembly by using artificial perturbation of tip part
  • Method for inhibiting rocking movement of aerofoil of wing body assembly by using artificial perturbation of tip part
  • Method for inhibiting rocking movement of aerofoil of wing body assembly by using artificial perturbation of tip part

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Experimental program
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Embodiment Construction

[0033] The present invention can be carried out according to the following embodiments:

[0034] 1) Choose an artificial disturbance with a higher machining accuracy than the tip of the head, in this case choose an artificial disturbance with a diameter of 0.2mm;

[0035] 2) Set the position of artificial disturbance: the circumferential position of artificial disturbance is selected near the longitudinal symmetrical plane of the windward side and the leeward side of the tip of the head (the disturbance circumferential angle is 0° and 180°, within the range of ±15°); the axial position is from the tip of the head Counting from the front, within 20mm backward;

[0036] 2) After setting the artificial disturbance, there is no need to apply any measures afterwards. If the aircraft does not roll at the beginning, the aircraft will not roll after the artificial disturbance is set; if the aircraft initially rolls, it will automatically converge to the 0° roll angle balance position ...

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Abstract

The invention relates to a method for controlling rocking of an aerofoil of a wing body assembly. A forebody vortex of a fuselage and a wing vortex are antiphase by setting head artificial perturbation with the dimension with precision higher than the machining precision of a tip part close to a longitudinal symmetry plane of a windward side and a leeward side of the tip part (a perturbation circumferential angle is between 0+ / -15 DEG and 180 + / -15 DEG), and then any measures are not required to be taken. An aircraft cannot rock after the artificial perturbation is set if not initially rocking; and the aircraft is automatically converged to a place close to a 0-DEG roll angle balance position if initially rocking, so that the rocking movement of a wing is effectively controlled, and a new technology for inhibiting rocking of the wing is successfully developed. Experimental results show that the method is simple and convenient and obvious control effects and a control time course is short.

Description

technical field [0001] The invention relates to a method for suppressing wing rocking of a wing-body assembly by setting artificial disturbance at the tip of the head, which is mainly used in the research of aircraft flight control and belongs to the field of aerospace technology. Background technique [0002] The requirements for the maneuverability and agility of modern fighter jets require that the aircraft still have strong controllability in the range of large angle of attack. When the aircraft enters a large angle of attack, due to the strong effect of the vortex separation flow on the front body of the fuselage or the wing, the aircraft may produce a typical nonlinear self-excited oscillation, that is, the rocking motion of the wing, which is mainly reflected in the movement around the aircraft body. The limit ring oscillation of the shaft, this common non-command motion seriously affects the handling characteristics and flight safety of fighter jets. Therefore, expe...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/38
Inventor 邓学蓥王延奎竹军闻静田伟徐思文
Owner BEIHANG UNIV