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An Aircraft Follow-up Tab Mechanism with Variable Transmission Ratio

A technology of a follow-up adjustment piece and adjustment piece, which is applied in the field of flight control and can solve the problem that the increase ratio of the aircraft rod force cannot be achieved.

Active Publication Date: 2016-12-07
哈尔滨通用飞机工业有限责任公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The existing aircraft follow-up trim pieces are all designed according to a fixed transmission ratio. With the deflection of the rudder surface, the follow-up trim pieces always deflect in a fixed ratio to the rudder surface. However, this design makes the aircraft stick of the purely mechanical control system The force cannot achieve a linear increase ratio, the pilot's control stick force will not increase linearly with the increase of the rudder surface deflection, there will be a smooth area

Method used

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  • An Aircraft Follow-up Tab Mechanism with Variable Transmission Ratio
  • An Aircraft Follow-up Tab Mechanism with Variable Transmission Ratio

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Embodiment Construction

[0013] An aircraft follow-up tab mechanism with variable transmission ratio, characterized in that it includes a first fixed slide rail support 1, a first slide rail guide sleeve 2, a connecting rocker arm 3, an adjustable pull rod 4, and a second fixed slide rail Support 6, second slide rail guide sleeve 5, adjustment piece pull rod 7, rudder surface 8, follow-up adjustment piece 9, first fixed slide rail support 1 and second fixed slide rail support 6 are fixed on the aircraft stabilizer , the first slide rail guide sleeve 2 is installed on the slide rail of the first fixed slide rail support 1, the second slide rail guide sleeve 5 is installed on the slide rail of the second fixed slide rail support 6, the first slide rail guide The lower end of the sleeve 2 is hinged with one end of the connecting rocker arm 3, the other end of the connecting rocker arm 3 is hinged with the aircraft rudder surface 8, the upper end of the first slide rail guide sleeve 2 is hinged with the ad...

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Abstract

The invention provides an aircraft geared trim tab mechanism with a variable transmission ratio. The aircraft geared trim tab mechanism comprises a first fixed sliding rail support, a first sliding rail guide sleeve, a connecting rocker arm, an adjustable pull rod, a second fixed sliding rail support, a second sliding rail guide sleeve, a trim tab pull rod, a geared trim tab and a rudder surface.

Description

technical field [0001] The invention relates to the field of flight control. Background technique [0002] The rudder surface follow-up trim pieces during the test flight of the existing aircraft are all designed according to a fixed transmission ratio, which cannot be adjusted accordingly according to the flight response. The structure form of prior art is as figure 1 shown. [0003] The existing aircraft follow-up trim pieces are all designed according to a fixed transmission ratio. With the deflection of the rudder surface, the follow-up trim pieces always deflect in a fixed ratio to the rudder surface. However, this design makes the aircraft stick of the purely mechanical control system The force cannot achieve a linear growth ratio, and the pilot's control stick force will not increase linearly with the increase of the rudder surface deflection, and there will be a smooth zone. Contents of the invention [0004] The technical problem to be solved in the present inv...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C9/04
Inventor 王征朱恒阳马小伟李波李文龙王君
Owner 哈尔滨通用飞机工业有限责任公司