Simulation apparatus of pitching/jawing/rolling over three-freedom degree forced movement of aircraft

A pitching motion and yaw motion technology, applied in the aerospace field, can solve problems such as forced motion devices that have not yet been seen

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

At present, the forced exercise device that can realize this kind of function has not been seen at home and abroad.

Method used

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  • Simulation apparatus of pitching/jawing/rolling over three-freedom degree forced movement of aircraft
  • Simulation apparatus of pitching/jawing/rolling over three-freedom degree forced movement of aircraft
  • Simulation apparatus of pitching/jawing/rolling over three-freedom degree forced movement of aircraft

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Experimental program
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Embodiment Construction

[0015] figure 1 A realization method of the aircraft pitch / yaw / roll three-degree-of-freedom forced motion simulation device is given. Marks 1, 2 and 3 are roll struts, yaw struts and pitch shafts respectively, and marks 4, 5 and 6 are the center lines of the roll strut, the yaw strut and the pitch shaft respectively, and the three lines are perpendicular to each other and intersect at one point. Mark 7 is the air flow direction. The experimental model of the aircraft is installed on the rolling strut, facing the direction of the airflow. Mark 3.3 is the support of the experimental device, mark 3.1 is the "L" rocker arm, mark 3.2 is the motor driving the pitching shaft and the "L" rocker arm, and mark 3.4 is the counterweight of the "L" rocker arm. The "L"-shaped rocker arm is driven by a motor, which can change the pitch angle of the model by rotating the angle to achieve pitch movement. figure 2 It is a schematic diagram of the pitch / yaw / roll three-degree-of-freedom force...

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Abstract

The invention relates to an experiment apparatus for simulating a pitching / jawing / rolling over three-freedom degree forced movement of an aircraft in a wind tunnel. The apparatus comprises an experiment apparatus support, a pitching movement device, an L type rocking arm, a jawing movement supporting rod, and a rolling over movement supporting rod. The apparatus is mainly characterized in that: the central axis of the pitching movement device, the central axis of the jawing supporting rod, and the central axis of the rolling over supporting rod are perpendicular mutually; and the three central axises are intersected at one point. The pitching movement device is fixed on the experiment apparatus support and is connected with one end of the L type rocking arm, so that the L type rocking arm is driven to make pitching movements. The other end of the L type rocking arm is connected with the jawing movement supporting rod; a rotating shaft of the jawing movement supporting rod is connected with the rolling over movement supporting rod by a connection rod, so that the rolling over movement supporting rod is driven to make jawing movements; and a rolling-over rotating shaft of the rolling over movement supporting rod is fixedly connected with a model. The rolling over movement supporting rod, the jawing movement supporting rod, and the rotating shaft of the pitching movement device are driven by a motor; and a decelerator is added at the front end of the motor that is controlled by a computer. Therefore, the experimental model can make movements according to a given movement role; and a feedback control algorithm is used to improve control precision.

Description

technical field [0001] The invention is an experimental device for simulating and reproducing the pitching, yaw / rolling motion of an aircraft in a wind tunnel experiment. The motion of the aircraft model is realized by a forced simulation device driven by a motor, so that the aircraft moves according to a given motion. It belongs to the field of aerospace technology. Background technique [0002] In recent years, in order to develop a new generation of highly maneuverable fighters, in-depth research has been carried out on the aerodynamic phenomenon at high angles of attack, and the problem of yaw-roll coupling at high angles of attack has also been put on the research agenda. [0003] The lateral-direction coupling problem of the aircraft exists in the sense of small angle of attack and small disturbance linearization, that is, the yaw of the aircraft will cause roll, and the roll of the aircraft will also cause yaw. Its typical motion mode is Dutch roll Modal (Dutch roll)...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/02G01M9/08
Inventor 马宝峰邓学蓥魏龙坤王延奎田伟李岩
Owner BEIHANG UNIV
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