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A composite material tail section fatigue and defect tolerance test device

A test device and composite material technology, applied in the field of helicopter body structure fatigue test, can solve the problems of not being able to give defect tolerance life, unable to give full play to the performance of the structure, etc., and achieve small load fluctuation, stable test bench, and test environment. Good results

Active Publication Date: 2019-03-01
CHINA HELICOPTER RES & DEV INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The technical problem to be solved by the present invention is to provide a composite material tail section fatigue and defect tolerance test device, which is used for the composite material tail section fatigue and defect tolerance test, and the device of the present invention can be used for the composite material tail section defect tolerance test. Fully verify its performance and obtain the defect tolerance life, which can overcome the disadvantages of using calculation methods to determine the safety life of the airframe in the background technology, which can only give a conservative safety life, but cannot give the defect tolerance life, and cannot give full play to the performance of the structure.

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  • A composite material tail section fatigue and defect tolerance test device
  • A composite material tail section fatigue and defect tolerance test device
  • A composite material tail section fatigue and defect tolerance test device

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Embodiment Construction

[0015] The present invention will be described in further detail below.

[0016] like figure 1 , figure 2 , image 3 , Figure 4 As shown, the present invention is a composite material tail section fatigue and defect tolerance test device, which is characterized in that it includes a rigid bearing frame 1, a connecting plate 2, a transition section dummy 3, a tail boom load loading fixture 4, and a tail rotor Dummy 5-1, tail rotor load loading fixture 5, and horizontal tail load loading fixture 6. The transition section dummy 3 adopts the real structure of the aircraft, one end is connected with the connecting plate 2 by bolts, and the other end is connected with the tail section (test piece) according to the installed state, and the transition section dummy 3 connection can more realistically simulate the boundary conditions and transmission of the test load. The tail rotor load loading fixture 5 includes a tail rotor dummy 5-1, a tail rotor horizontal load loading rod ...

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Abstract

The invention provides a composite material tail fatigue and defect tolerance test apparatus to be used in a composite material tail fatigue and defect tolerance test. According to the invention, the apparatus can sufficiently examine the properties of the composite material tail in a composite material tail defect tolerance test, and acquires the service lifetime of the defect tolerance, can overcome delivery of over-conservative safe lifetime, the failure to provide the service lifetime of the defect tolerance, and insufficiency of the usage of a structure in the prior art technologies when determining safe lifetime of an aircraft body.

Description

technical field [0001] The invention belongs to the fatigue test technology of a helicopter body structure, and relates to a composite material tail section fatigue and defect tolerance test device. Background technique [0002] The tail section is a complex and key part of the helicopter body structure. The main loads include mass force, tail rotor thrust, and aerodynamic force of the horizontal tail and vertical tail. The fatigue stress level of the tail section is obviously higher than that of the middle fuselage and nose. The fatigue life is generally replaced by the life of the tail section. Due to the complex shape of the structure, the severe load it bears, and the lightest possible weight, it is very important to provide an accurate fatigue test assessment environment, and to conduct the test assessment to obtain the fatigue life and weak parts. [0003] Background Art The calculation method is used to determine the safe life of the airframe. During the calculation,...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M99/00
CPCG01M99/00
Inventor 方丽颖包名邓文朱浩煜
Owner CHINA HELICOPTER RES & DEV INST