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Bionic aircraft rudder surface preparation method

A bionic aircraft and rudder surface technology, applied in chemical instruments and methods, layered products, lamination devices, etc., can solve the problems of heavy structure and inapplicability of aircraft rudder surfaces

Active Publication Date: 2021-07-06
BEIJING RES INST OF MECHANICAL & ELECTRICAL TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The technical problem to be solved in the present invention is to provide a preparation method for applying light, high-temperature-resistant bionic TiAl plate to the rudder surface of an aircraft, so as to solve the problem that the existing aircraft rudder surface has a heavy structure and is not suitable for use in a long-range high-temperature environment

Method used

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  • Bionic aircraft rudder surface preparation method
  • Bionic aircraft rudder surface preparation method
  • Bionic aircraft rudder surface preparation method

Examples

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preparation example Construction

[0035] The invention provides a method for preparing a rudder surface for an aircraft. The rudder surface mainly includes: a skeleton and a skin.

[0036] The skeleton is the main load-bearing structure of the rudder surface. It is located inside the rudder surface. The two sides of the rudder skeleton are designed as skin structures. The skeleton and skin of the rudder together constitute the main structure of the rudder surface.

[0037] The outer structure of the rudder surface skin is adapted to the outer shape of the aircraft. The structural design of the rudder frame can be a transverse and longitudinal beam structure, a radial structure, etc., which can be selected according to the specific load form and working environment.

[0038] The skeleton preparation process of the rudder includes but not limited to: casting, powder metallurgy, welding, machining, etc. The selection of the process form is a well-known technology in the art.

[0039] In some embodiments of the ...

Embodiment 1

[0059] by figure 1 The rudder surface structure of an aircraft shown in the example is mainly composed of the skeleton of the rudder ( figure 2 ) and skinning ( image 3 )composition. The skeleton of the rudder is TiAl alloy, with a maximum thickness of 60mm. It is composed of ribs, rudder leading edge, rudder trailing edge and the upper and lower bottom plates of the rudder. The thickness of the ribs is 3-10mm. . The skin of the rudder is TiAl alloy with a thickness of 1mm. The outer surface is an aerodynamic surface, and the inner surface is closely attached to the skeleton rib of the rudder, and the surrounding is closely attached to the front and rear edges of the rudder and the upper and lower bottom plates. The skin of the rudder is composed of left and right parts. After the rudder frame and skin are installed in place, there will be no reverse airflow step along the airflow direction at the butt joint gap, and the step along the airflow should not be greater than ...

Embodiment 2

[0065] by Figure 4 The rudder surface structure of an aircraft shown is mainly composed of the skeleton of the rudder ( Figure 5 ) and skinning ( Figure 6 ) composed of auxiliary screw connections. The skeleton of the rudder is TiAl alloy, with a maximum thickness of 30mm. It is composed of ribs, rudder leading edge, rudder trailing edge and the upper and lower bottom plates of the rudder. The thickness of the ribs is 2-5mm. . The skin of the rudder is TiAl alloy with a thickness of 0.5mm. The outer surface is an aerodynamic surface, and the inner surface is closely attached to the skeleton rib of the rudder, and the surrounding is closely attached to the front and rear edges of the rudder and the upper and lower bottom plates. The skin of the rudder is composed of left and right parts. The rudder frame and skin are auxiliary connected by screws. After the rudder frame and skin are installed in place, there is no reverse air flow step along the airflow direction at the...

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Abstract

The invention provides a bionic aircraft rudder surface preparation method, which comprises the following steps: carrying out mould pressing deformation on a titanium plate and an aluminum plate in advance to form a multi-layer titanium and aluminum alternate laminated plate, carrying out reaction heat treatment in a forming mould of a rudder skin to prepare a TiAl-based alloy skin, connecting the TiAl-based alloy skin with a framework, and conducting heating and pressurizing in the mould to form a bionic aircraft rudder surface; or inlaying unreacted titanium and aluminum alternate laminated plates after mould pressing deformation into the two sides of a rudder skeleton, and conducting heating and pressurizing in the mould to form the bionic aircraft rudder surface. The thickness of a heat-proof layer can be effectively reduced, the use of high-temperature alloy is reduced, the structural weight of the aircraft is obviously reduced, and the voyage index of the aircraft is improved.

Description

technical field [0001] The invention relates to a method for preparing an aircraft air rudder surface, and belongs to the technical field of aircraft structure design. Background technique [0002] During transatmospheric reentry or flight within the atmosphere, the aircraft needs to withstand continuous aerodynamic heating for a long time. At the same time, as the speed of the aircraft becomes faster and faster, the aircraft needs a lower structural weight. This puts forward higher requirements for the air control surface of the aircraft. While providing the aircraft with flight lift and deflection force, it needs to bear complex air loads and aerodynamic heating. Therefore, the rudder surface needs to meet the requirements of low weight, high strength and high temperature resistance. . [0003] Most of the rudder surfaces of traditional aircraft are made of aluminum alloy and titanium alloy and other materials suitable for non-high-temperature environments. High-density m...

Claims

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Application Information

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IPC IPC(8): B32B15/01B32B15/20B32B15/00B32B37/06B32B37/10B32B38/18
CPCB32B15/017B32B15/00B32B37/06B32B37/10B32B38/1866Y02T50/40
Inventor 王庆伟李晶冯蕾蕾吕文亮韩乐黄正石刘鹏范国华
Owner BEIJING RES INST OF MECHANICAL & ELECTRICAL TECH
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