Air rudder riveting process method

A process method and air rudder technology, applied in the field of air rudder, can solve problems such as damage, cracks, delamination, etc., and achieve the effect of ensuring the quality and accuracy of riveting and solving delamination

Active Publication Date: 2020-04-28
HUBEI SANJIANG AEROSPACE GRP HONGYANG ELECTROMECHANICAL
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0004] The embodiment of the present invention provides an air rudder riveting process, which is used to solve the problems of delamination, damage, cracks, etc. during the riveting and forming of aluminum matrix composite air rudders

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Embodiment Construction

[0033] The embodiment of the present invention provides an air rudder riveting process, which is used to solve the problems of delamination, damage, cracks and the like generated during riveting and forming of an aluminum-based composite material air rudder. The air rudder includes a titanium alloy rudder yoke, an aluminum matrix composite material rudder plate, a titanium alloy transitional rudder plate and a C / SiC leading edge, and the method includes: comparing the titanium alloy rudder yoke with the aluminum matrix composite material rudder When the plates are riveted, a taper pin rivet is installed in the first rivet hole corresponding to the titanium alloy rudder yoke and the aluminum-based composite material rudder plate, and the small end of the taper pin rivet protrudes from the corresponding first rivet hole , heating the protruding part of the small end, and after heating to a preset state, performing pneumatic riveting on the small end; when riveting the aluminum ma...

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Abstract

The embodiment of the invention provides an air rudder riveting process method. The air rudder riveting process method comprises the steps that when a titanium alloy rudder fork and an aluminum matrixcomposite rudder plate are riveted, a taper pin rivet is installed in a corresponding first rivet hole in the titanium alloy rudder fork and the aluminum matrix composite rudder plate, and the smallends of the taper pin rivet protrude out of the corresponding first rivet hole, then the protruding parts of the small ends are heated, and after the protruding parts are heated to be in a preset state, pneumatic riveting is conducted on the small ends; when the aluminum matrix composite rudder plate and a titanium alloy transition rudder plate are riveted, a first rivet is inserted into a corresponding second rivet hole in the aluminum matrix composite rudder plate and the titanium alloy transition rudder plate, static pressure riveting is conducted on the first rivet, and then pneumatic riveting is conducted on the first rivet; and when the titanium alloy transition rudder plate and a C / SiC front edge are riveted, a second rivet is inserted into a corresponding third rivet hole in the titanium alloy transition rudder plate and the C / SiC front edge, static pressure riveting is conducted on the second rivet, and then the second rivet is riveted through hammer riveting.

Description

technical field [0001] The invention relates to the technical field of air rudders, in particular to an air rudder riveting process method. Background technique [0002] Composite materials have a series of advantages such as high specific strength, high specific modulus, good fatigue resistance, corrosion resistance, etc., and are widely used in modern aerospace structures. Although composite materials have advantages that ordinary metals do not have, they also have certain weaknesses: brittleness, low interlayer strength, and poor impact resistance. For composite materials, there are two commonly used mechanical connection methods: bolt connection and rivet connection. Compared with screw connection, riveted joints are light in weight and low in cost, and are widely used in modern aerospace structures. [0003] The aluminum matrix composite air rudder is composed of four parts: titanium alloy rudder yoke, aluminum matrix composite rudder plate, titanium alloy transition r...

Claims

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Application Information

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IPC IPC(8): B21J15/08B21J15/14B21J15/18B64C9/32
CPCB21J15/08B21J15/142B21J15/18B64C9/32
Inventor 吕天明赵俊庄玉蓉聂绪胜闫安翟永卉肖群王春艳冯凯
Owner HUBEI SANJIANG AEROSPACE GRP HONGYANG ELECTROMECHANICAL
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