Vertical tail structure of a carrier-based transport aircraft

Abstract

The invention belongs to an airplane design technology, and relates to improvement of a vertical fin structure of ship-borne transportation airplanes. A vertical fin front control plane (15) is arranged at the front end of a vertical fin wing box (1) through a vertical fin front control surface rotating shaft (16), and a vertical fin rear control surface and vertical fin front control surface control rod system consisting of a first vertical fin rear control surface hinge (4), a second vertical fin rear control surface hinge (5), a first vertical fin rear control surface pull rod (6), a second vertical fin rear control surface pull rod (7), a first vertical fin front control surface pull rod (8), a second vertical fin front control surface pull rod (9), a cross-shaped rocker arm (10), a cross-shaped arm shaft (11), an actuator unit (12), a first vertical fin front control surface hinge (13) and a second vertical fin front control surface hinge (14) is arranged inside the vertical fin wing box (1). The vertical fin structure of the ship-borne transportation airplanes, provided by the invention, is high in control efficiency, has dual-control redundancy, and is increased in heading control efficiency and redundancy of the ship-borne transportation airplanes.

Description

technical field [0001] The invention belongs to the aircraft design technology and relates to the improvement of the vertical tail structure of carrier-borne transport aircraft. Background technique [0002] The vertical tail structure of the current carrier-based transport aircraft is composed of a vertical tail box, a vertical tail rear rudder surface and a vertical tail rear rudder shaft, and the vertical tail rear rudder surface is installed on the rear end of the vertical tail box through the vertical tail rear rudder shaft. . Its disadvantages are: first, only relying on the deflection of the rear rudder surface of the vertical tail to provide the directional deflection moment of the aircraft, the control efficiency is low, and it is not enough for the aircraft to recover under certain abnormal flight conditions, which may easily lead to flight accidents; , There is only one set of control levers, and the margin is low. Once the control fails, it will easily lead to f...

AI Technical Summary

Problems solved by technology

Its disadvantages are: first, only relying on the deflection of the rear rudder surface of the vertical tail to provide the directional deflection moment of the aircraft, the control efficiency is low, and it is not enough for the aircraft to recover under certain abnormal flight conditions, which may easily lead to flight accidents; second , There is only one set of control levers, and the margin is low. Once the control fails, it will easily lead to flight accidents

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