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Device for simulating free yawing/rolling movement under pitching movement of aircraft

An aircraft and rolling technology, applied in the aerospace field, can solve the problems of inconvenience in free motion experiments

Inactive Publication Date: 2012-06-13
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the current experimental institutions for virtual flight research are basically aimed at missile research, and the tensioned structure is used, which is very inconvenient for the two-degree-of-freedom free motion experiment of the aircraft

Method used

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  • Device for simulating free yawing/rolling movement under pitching movement of aircraft
  • Device for simulating free yawing/rolling movement under pitching movement of aircraft
  • Device for simulating free yawing/rolling movement under pitching movement of aircraft

Examples

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Embodiment Construction

[0012] figure 1 It is the yaw / roll free motion simulation device under the pitching motion of the aircraft. The marks 1 and 2 are the free rolling motion strut and the free yaw motion strut respectively. The mark 3 is the rocker arm connected to the angle of attack mechanism, and the marks 4, 5 and 6 are roll axis, yaw axis and pitch axis, the three axes are perpendicular to each other, and the three axes intersect at the reference center of the model. Mark 7 is a connecting rod, which is used to connect the free-rolling motion strut and the free yaw motion strut when the model is in motion. Mark 8 is a counterweight, which is used to adjust the center of gravity during yaw motion to be on the yaw axis to eliminate the influence of gravity. Mark 9 is the incoming flow direction of the wind, and the model faces the incoming flow direction at a certain angle.

[0013] figure 2 A cross-sectional view of a free-rolling strut. Marks 1.2 and 1.4 are deep groove ball bearings, a...

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Abstract

An experimental device for simulating free yawing / rolling movement of an aircraft in two degrees of freedom in an air tunnel mainly comprises a free yawing support rod and a free rolling support rod which are fixedly connected with a pitching mechanism. The experimental device is mainly characterized in that the central axis of the free yawing support rod and the central axis of the free rolling support rod are perpendicular to that of a pitching movement device, the three axes are intersected at one point, a rotary shaft of the yawing support rod is connected with the rolling support rod through a connecting rod and drives the rolling support rod to yaw, a rolling rotary shaft of the rolling support rod is fixedly connected with a model, and the rotary shaft of the yawing support rod and the rotary shaft of the rolling support rod are supported by bearings in the corresponding support rods and can freely move without being restrained. In order to realize yawing of the yawing support rod, a counterweight block needs to be placed on the connecting rod between the yawing support rod and the rolling support rod, and the centers of mass of the connecting rod and the rolling support rod are adjusted onto the axis of the yawing rotary shaft.

Description

technical field [0001] The invention relates to a device for simulating the yaw / roll free motion of an aircraft under forced pitching motion in a wind tunnel experiment. The device is used for wind tunnel experiment simulation research and belongs to the aerospace technology field. Background technique [0002] Now fighter jets need to have good flight performance at high angles of attack, and at high angles of attack, due to the mutual coupling between the vortex separation flow and the movement of the aircraft body, a series of uncontrollable flight phenomena will occur, such as wing rocking, Phenomena such as nose deviation and heavy wings seriously affect flight safety and flight performance. And this uncommanded instability movement is usually a coupling movement in the transverse direction. Therefore, the aerodynamic design of the high angle of attack of the aircraft presents many new features. At small angles of attack, the theory of small disturbance linearization ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/00G01M9/08
Inventor 马宝峰邓学蓥魏龙坤王延奎田伟李岩
Owner BEIHANG UNIV
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