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Aircraft radome connecting structure

A connection structure and radome technology, applied in aircraft parts, fuselage insulation, fuselage and other directions, can solve problems such as falling off, achieve reliable connection strength, avoid high-temperature carbonization and debonding of the adhesive layer, and avoid uncontrollable debonding. Effect

Pending Publication Date: 2022-07-05
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In view of the defects existing in the prior art, the purpose of the present invention is to provide a connection structure for the aircraft radome, which can solve the problem of using adhesives in the prior art or increasing the operating temperature by improving the adhesives, but there is still a risk of falling off. The problem

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  • Aircraft radome connecting structure
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Embodiment Construction

[0025] In order to make the purposes, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments It is a part of the embodiments of this application, but not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work shall fall within the protection scope of the present application.

[0026] The embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0027] figure 1 It is a schematic structural diagram of a connecting structure of an aircraft radome in an embodiment of the present invention; figure 2 It is a schematic structural diagram ...

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Abstract

The invention relates to the technical field of head covers and thermal protection of hypersonic aircrafts, in particular to an aircraft radome connecting structure which comprises a radome, a nut and a heat insulation screw corresponding to the nut, and the radome comprises a connecting end used for being connected with a rear cabin section. At least three nut holes are formed in the inner wall of the connecting end in the circumferential direction at intervals, and bolt holes communicated with the nut holes are further formed in the connecting end. Nuts corresponding to the nut holes are arranged in the nut holes; the heat insulation screws corresponding to the nuts are used for penetrating through the connecting holes in the rear cabin section and the bolt holes in the connecting ends to be connected with the nuts so that the rear cabin section can be connected with the connecting ends. The problem that in the prior art, an adhesive type is adopted or the use temperature of the adhesive is increased by improving the adhesive, but the falling risk still exists can be solved.

Description

technical field [0001] The invention relates to the technical field of a hood and thermal protection of a hypersonic aircraft, in particular to a connecting structure of an aircraft radome. Background technique [0002] During the flight of the hypersonic aircraft, the radome is mainly used to protect the seeker, so that it has a suitable operating temperature environment to meet the effective electrical performance. Since the radome is located at the head of the aircraft, it is subjected to the largest aerodynamic and aerodynamic heating. The design requires that it can meet the requirements of static strength and thermal strength at the same time while ensuring effective electrical performance. Due to its good high temperature resistance, high high temperature strength and excellent dielectric properties, composite quartz or silicon nitride ceramics are widely used as radome materials. However, the load transfer between the ceramic material and the rear metal cabin materi...

Claims

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Application Information

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IPC IPC(8): B64C1/36B64C1/40
CPCB64C1/36B64C1/403
Inventor 洪珅范开春马治周明星涂正光王辉李志杰王博哲毛靖
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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