Fuselage cabin section structural strength test constraint system

A technology of structural strength and restraint system, applied in the direction of aircraft component testing, etc., can solve the problems of increasing the processing cost of the test piece and the demand of the test site, and achieve the effect of reducing the demand for test space, speeding up the design process, and improving the test efficiency.

Active Publication Date: 2020-07-14
CHINA AIRPLANT STRENGTH RES INST
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AI Technical Summary

Problems solved by technology

The design of the test frame plus transition frame increases the processing cost of the test piece and the demand for the test site

Method used

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  • Fuselage cabin section structural strength test constraint system
  • Fuselage cabin section structural strength test constraint system
  • Fuselage cabin section structural strength test constraint system

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Embodiment Construction

[0030] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention are described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the described embodiments are only descriptive, not restrictive, and cannot limit the protection scope of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention. The embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0031] In the static / fatigue test of the aircraft fuselage section, the structural strength test of the fuselage section usually adopts the fixed support / hinged support constraint. When the above two kinds of con...

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Abstract

The invention belongs to the field of structural strength tests and particularly relates to a fuselage cabin section structural strength test constraint system. The system comprises a bearing terrace,M stand columns, M fastening structures, M load conversion mechanisms, a fixed base, an adhesive tape and a vertical constraint mechanism, wherein the fixed base is arranged on the bearing terrace, the vertical restraining mechanisms are arranged at two ends of the fixed base and connected with the fuselage cabin section through bolts, the M stand columns are distributed at the front-back headingposition and the left-right lateral position of the fuselage cabin section correspondingly, lower ends of the stand columns are fixed to the force bearing terrace, the adhesive tape is adhered to a skin end frame and two sides of the fuselage cabin section, upper ends of the stand columns are connected with one ends of the load conversion mechanisms through a fastening structure, and the other ends of the load conversion mechanisms are connected with the adhesive tape. The system is advantaged in tht constraints meeting requirements can be provided, the constraint load of a fuselage cabin section end frame and a side wall boundary is effectively reduced, and the boundary is prevented from being damaged earlier than an assessment area.

Description

technical field [0001] The invention belongs to the technical field of structural strength testing, in particular to a restraint system for structural strength testing of a fuselage cabin section. Background technique [0002] In the static / fatigue test of the aircraft fuselage section, the structural strength test of the fuselage section usually adopts the fixed support / hinged support constraint. When the above two kinds of constraints are used, the test piece of the fuselage section is generally designed as a test frame and a transition frame. The test frame is the same as the real structure of the aircraft, and is assessed in the test. The transition frame is used as the test constraint boundary, which acts as a constraint and transfer load in the test. The design of the test frame plus the transition frame increases the processing cost of the test piece and the demand for the test site. SUMMARY OF THE INVENTION [0003] The purpose of the invention is to provide a res...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60
CPCB64F5/60Y02T50/40
Inventor 卓轶魏玉龙陈莉孙汉斌廖江海
Owner CHINA AIRPLANT STRENGTH RES INST
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