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Variable density high-speed aircraft flap rudder

A high-speed aircraft and variable density technology, which is applied in the direction of instruments, energy efficiency, process efficiency, etc., can solve the problems of rib layout restrictions, high production costs, thickness and spacing restrictions, etc., and achieve the effect of solving collapse deformation

Active Publication Date: 2017-04-19
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The material used in this structural design is limited to thin-walled plates, and the thickness is seriously reduced. The internal rib layout of the part is limited by the technical conditions of the process, and the thickness and spacing are limited; if the process parameters such as temperature and pressure are not well controlled, process defects will occur.
At the same time, the structure cannot meet the design requirements of high-speed aircraft in terms of light weight and heat insulation performance. Compared with advanced 3D printing technology, the manufacturing process has a long manufacturing cycle and high production costs.

Method used

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  • Variable density high-speed aircraft flap rudder
  • Variable density high-speed aircraft flap rudder
  • Variable density high-speed aircraft flap rudder

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Embodiment Construction

[0028] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0029] A variable density high-speed aircraft wing rudder, such as figure 1 , figure 2 and Figure 4 As shown, including wing rudder skeleton, wing rudder skin 8 and rudder shaft 9,

[0030] The wing rudder skeleton includes the outer leading edge 4, trailing edge 5, front tip 6, wing rudder bottom 7 and internal transverse wall 2, longitudinal wall 1 and wing rudder support 3, wherein the transverse wall 2 connects the leading edge 4 and the trailing edge 5. The longitudinal wall 1 connects the front tip 6 of the wing rudder and the bottom 7 of the wing rudder,

[0031] A wing rudder support 3 is provided at the intersection of the leading edge 4 and the wing rudder bottom 7, and a through hole is arranged inside the wing rudder support 3, and the rudder shaft 9 is placed in the through hole to connect with the wing rudder frame. The structure of the ru...

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Abstract

The invention discloses a variable density high-speed aircraft flap rudder. Pore structures associated with a topological optimization result are arranged on a longitudinal wall and a transverse wall, and hollow microstructures are arranged on flap rudder skin in an array, so that failures caused by too much high-temperature strength reduction of a rudder spindle due to the fact that a large quantity of heat is transferred to a rudder spindle through an aerothermal load can be effectively solved, and meanwhile more than 15% of weight reduction can be realized qualitatively compared with a traditional flap rudder structure.

Description

technical field [0001] The invention relates to a variable-density high-speed aircraft wing rudder, which is especially suitable for the structure of the high-speed aircraft wing rudder. Background technique [0002] When a high-speed aircraft is in service, the outer surface of the aircraft will be subjected to harsh loads of high temperature, high pressure and high enthalpy, especially the external movable parts of the aircraft such as wing rudders. The load environment is even harsher. At the same time, the structural design of the wing and rudder components needs to meet the requirements of light structure, high strength, and excellent heat insulation performance; Processing is difficult. Therefore, the design and processing of high-speed aircraft wing rudder structure is rarely reported in the world. [0003] The high-strength titanium alloy missile rudder wing adopts the structural characteristics of the rudder wing surface parts, and the internal structure adopts th...

Claims

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Application Information

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IPC IPC(8): G06F17/50B22F3/105B33Y80/00
CPCB33Y80/00G06F30/18G06F30/23G06F30/15B22F10/00B22F10/20B22F10/80Y02P10/25
Inventor 卢琦费王华申亮张沥娄依志赵山杉赵月惠俊鹏史锐杨旸
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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