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Central wing of horizontal tail of civil airplane

A technology of horizontal tail and civil aircraft, applied in aircraft parts, aircraft control, aircraft stability, etc., can solve the problems of poor fatigue performance, failure of pivot 5, etc., and achieve the effect of reducing mass, light weight and high strength

Inactive Publication Date: 2013-03-13
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The pivot 5 connected to the rear beam 4 adopts an integrated design extending from the hinge at one end to the hinge at the other end. The fatigue performance of the structure is poor, and crack propagation will cause the entire pivot 5 to fail.

Method used

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  • Central wing of horizontal tail of civil airplane
  • Central wing of horizontal tail of civil airplane
  • Central wing of horizontal tail of civil airplane

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Experimental program
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Effect test

Embodiment Construction

[0022] A kind of civil aircraft horizontal tail central wing of the present invention is described in detail below in conjunction with accompanying drawing.

[0023] (a), for attached figure 2 The working principle of the Boeing B737 horizontal tail adjustment installation angle mechanism shown is: the rear fuselage frame A is connected to the lower support of the screw, generally a little in front of the front beam of the horizontal stabilizer, and the specific position needs to be obtained after coordination. The screw rod 6 is driven by a servo motor or a hydraulic motor to rotate, and drives the screw support 1 connected to the screw rod 6 to move in the vertical direction. Since the rear beam 4 and the rear fuselage frame B8 are hinged by the pivot shaft 5, the actual horizontal tail center wing The movement is the change of the angle, and the movement mechanism of the adjustable horizontal tail installation angle;

[0024] (b), for attached image 3 Shown is a schemat...

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PUM

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Abstract

The invention discloses a central wing of a horizontal tail of a civil airplane, which belongs to the technical field of airplane structures, and is capable of lightening the structural weight of the conventional central wing of the horizontal tail, prolonging structural safety life of the conventional central wing and improving the structure reliability of the conventional central wing. According to the central wing of the horizontal tail of the civil airplane, a W-shaped web plate is used for connecting a front beam and a rear beam of the central wing of the horizontal tail and is subjected to tape laying through composite materials to finish an integral processing process, and thus the structure weight is lightened; and rear beam connecting lugs and rear body reinforcing frame lugs are connected with one another by a pivot, the functions of the pivot of the rear beam is realized by virtue of an outer shaft and an inner shaft, endurance cracks of one shaft cannot expand to the other shaft, and when one shaft suffers from strength disruption due to load mutation, the other shaft still can be loaded, so that the safe service life of the pivot is prolonged, and the reliability of the pivot is improved.

Description

technical field [0001] The invention belongs to the technical field of aircraft structure design, and relates to a structural device capable of reducing the structural weight of a horizontal tail center wing and improving safety life and reliability. Background technique [0002] The structural design of large passenger aircraft is one of the key technologies in the development of large aircraft, and the empennage structure design is an important part of it. The development of large passenger aircraft in my country requires continuous innovation in structural design and empennage design to solve key technical problems. [0003] For subsonic civil aircraft, the most serious state that needs to be considered in the design of the horizontal tail is take-off and landing. During take-off and landing, lowering the flaps will generate a large nose-down moment. When the aircraft takes off and lands, in order to maintain stability, the horizontal tail must be deflected to the maximum...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C5/02
Inventor 王伟田云伍春波陈亚军何景武
Owner BEIHANG UNIV
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