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Differential motion operation mechanism for follow-up spoilers of airplane

A control mechanism and follow-up technology, which is applied in the field of aircraft flight control systems, can solve the problems of difficult installation and debugging, occupying the inner space of the wing, and high cost, so as to achieve small space occupation of the wing, improve lateral maneuverability, and simple installation and debugging Effect

Inactive Publication Date: 2019-03-26
SHAANXI AIRCRAFT CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The active control system is complex in composition, high in cost, and difficult to install and debug; the disadvantage of the existing simple follow-up spoiler is that it is always linked with the aileron control line. When the spoiler is used as the compensation control of the aileron, it is located The spoiler on the wing with the aileron up extends out, while the spoiler on the other wing moves from the position of the wing surface to the inside of the wing, which will not only occupy the space inside the wing and cause damage to other system components. Difficult to arrange and will affect the aerodynamic shape of the wing surface

Method used

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  • Differential motion operation mechanism for follow-up spoilers of airplane

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Embodiment Construction

[0011] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0012] On the side of the wing where the aileron is deflected upward, when the aileron deflects 2.5°~4°, the upper ends of the two spoilers begin to protrude from the upper surface of the wing; when the aileron deflects 25°±1°, The spoiler fully protrudes from the upper airfoil, and its height is 140±5mm. The protruding spoiler separates part of the airflow from the surface of the wing to reduce the lift of the wing and increase the aileron effect.

[0013] Spoiler is contained on the rotating shaft (5) by two support rocker arms (2), wherein a support rocker arm is equipped with lug. The rotating shaft is mounted on two bearings (3) with ball bearings and rotates around its axis. Adjustable small pull bar (7) one end links to each other with the lug of support rocking arm, and the other end links to each other with binaural rocking arm (6). ...

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Abstract

The invention discloses a differential motion operation mechanism for follow-up spoilers of an airplane. According to the differential motion operation mechanism, the lateral controllability of the airplane at a high attack angle is improved, and the aileron effect is increased. The differential motion operation mechanism adopts a follow-up operation manner and can automatically stretch or retractalong the motions of ailerons, when the ailerons lean downwards from a neutral position, the spoilers are still adhered to the surface of wings, and the aerodynamic configurations of the surfaces ofthe wings are maintained, so that the occupied space of the wings is small, and a system is convenient to configure and easy to mount and debug.

Description

technical field [0001] The invention relates to an aircraft flight control system, in particular to an aircraft follow-up spoiler differential control mechanism. It is used to improve the lateral maneuverability of the aircraft at high angle of attack, increase the aileron effect, and improve the high roll performance of the aircraft. Background technique [0002] The role of the spoiler is to assist the control system to provide lift power for takeoff and landing and increase the aerodynamic drag on the ground or in flight, improving the handling performance of the aircraft. It mainly includes spoiler and speed brake system. The control of the spoiler is divided into active type and follow-up type, and the active type is generally divided into electric drive or hydraulic servo drive. The active control system is complex in composition, high in cost, and difficult to install and debug; the disadvantage of the existing simple follow-up spoiler is that it is always linked wi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C13/00B64C13/24B64C7/00
CPCB64C13/00B64C7/00B64C13/24
Inventor 杨涛史振良宋娟妮车意彬吕明杨曦徐坚齐海东陈丰华骆李平朱永岗石强军戴畅崔津铭
Owner SHAANXI AIRCRAFT CORPORATION
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