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Suspension structure of control surface of large aircraft

A rudder surface and aircraft technology, applied in aircraft parts, aircraft control, transportation and packaging, etc., can solve the problems of low force transmission efficiency, reduced aerodynamic efficiency of the rudder surface, high structural weight cost, and achieve reliable work and avoid aerodynamic efficiency. The effect of reducing and saving weight

Active Publication Date: 2018-05-29
中航通飞华南飞机工业有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In order to prevent the rudder surface from colliding with the diagonal stay rod when the rudder surface rotates, this structure needs to set a large opening on the leading edge of the rudder surface, which seriously reduces the aerodynamic efficiency of the rudder surface; Low efficiency, high structural weight penalty

Method used

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  • Suspension structure of control surface of large aircraft
  • Suspension structure of control surface of large aircraft
  • Suspension structure of control surface of large aircraft

Examples

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Embodiment Construction

[0035] The specific embodiment of a kind of large-scale aircraft rudder surface suspension structure of the present invention is described now in conjunction with accompanying drawing.

[0036] see figure 1 Shown, a kind of large aircraft rudder surface suspension structure of the present invention is used for the connection between rudder surface 3 and stabilizer 4; Hinge line load-bearing structure 1 is used for bearing the inertial load of rudder surface along hinge line; Aerodynamic load bearing force Structure 2 is used to bear the aerodynamic load of the rudder surface.

[0037] see figure 1 with figure 2 As shown, the hinge line load-bearing structure 1 includes a box-shaped beam 11 directly connected to the rear beam of the stabilizer 4, an axial joint 12 and a bolt shaft 13 located in the rudder surface 3; the box-shaped beam 11 includes a vertical diaphragm 111 , a lower end rib 112 , an upper end rib 113 , a transverse diaphragm 114 and a box beam joint 115 loca...

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PUM

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Abstract

The invention provides a suspension structure of a control surface of a large aircraft. The suspension structure of the control surface of the large aircraft is comprised of a hinged line load bearingstructure (1) and an aerodynamic load bearing structure (2). Hinged line load is independently borne by the hinged line load bearing structure (1), wherein the hinged line load bearing structure (1)is comprised of box-shaped beams (11), bolt shafts (13), and an axial joint (12). The box-shaped beams (11) are arranged in a stabilizing plane (4), the bolt shafts (13) are arranged in the box-shapedbeams (11), and the axial joint (12) is arranged in the control surface (3). Aerodynamic load is independently borne by the aerodynamic load bearing structure (2), wherein the aerodynamic load bearing structure (2) is comprised of a suspension support arm (21) and a suspension joint (22). The suspension support arm (21) is arranged in the stabilizing plane (4), and the suspension joint (22) is arranged in the control surface (3). The hinged line load bearing structure (1) is arranged on the root portion of the control surface and the lower portion of the stabilizing plane, so that a large opening in the front of the control surface is avoided, and the aerodynamic efficiency of the control surface is enhanced; the box-shaped beams (11) are directly connected with butt joints on a tail wing, the force transmission is simple and direct, and the weight is light; and through the combination of a bushing and a bearing and a clearance which is arranged reasonably, different degrees of freedom are released, and the work of each structure is non-interference and reliable.

Description

technical field [0001] The invention relates to an aircraft suspension structure, in particular to a large-scale aircraft rudder surface suspension structure. Background technique [0002] In addition to bearing the aerodynamic load of the rudder surface, the large aircraft rudder surface suspension structure must also be able to withstand the 36Wg inertial load of the rudder surface along the hinge line. Most of the existing large-scale aircraft rudder surface hinge-line load-bearing structures use diagonal stay rods combined with rudder surface cantilevers to bear the rudder surface hinge-line load. In order to prevent the rudder surface from colliding with the diagonal stay rod when the rudder surface rotates, a large opening needs to be set on the leading edge of the rudder surface, which seriously reduces the aerodynamic efficiency of the rudder surface; Low efficiency and high structural weight penalty. Contents of the invention [0003] In order to solve the defec...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C9/02
CPCB64C9/02
Inventor 胡海波张石柱张建华刘东辉刘木君余修坤刘岩
Owner 中航通飞华南飞机工业有限公司
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