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Loading design method for high vertical fin vertical load of full-scale fatigue test

A vertical load and fatigue test technology, which is applied in the field of aviation fatigue damage tolerance test, can solve problems such as structural damage and prolong the test loading period, and achieve the effect of novel design, clear engineering concept and correct theoretical basis

Active Publication Date: 2019-04-05
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

Due to the structural characteristics of the vertical tail, the vertical load is not easy to apply, and additional lateral force or lateral internal force will be generated by stretching the tape in the inclined direction, which will cause additional damage to the structure and prolong the test loading period.

Method used

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  • Loading design method for high vertical fin vertical load of full-scale fatigue test
  • Loading design method for high vertical fin vertical load of full-scale fatigue test
  • Loading design method for high vertical fin vertical load of full-scale fatigue test

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example

[0029] The present invention will be further described in detail with a specific example below.

[0030] A full-scale fatigue test high vertical tail vertical load loading design method, comprising the following steps:

[0031] A known:

[0032] Load case M=1.

[0033] Step 1. Establish the finite element model of the whole machine, solve the load of the whole machine, and obtain the vertical load F of the vertical tail under the 1 working condition z =-30000N (vertically downward);

[0034] Step 2, according to the size and magnitude of the vertical load of the vertical tail, determine the method of sinking the vertical load of the vertical tail to the fuselage frame to apply;

[0035] Step 3. According to the strength of the joint structure of the vertical tail of the fuselage, combined with the vertical load of the vertical tail, carry out the calculation and solution of the load of the whole machine, and obtain the load F of each vertical tail joint of the fuselage unde...

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Abstract

The invention belongs to the field of aviation fatigue damage tolerance tests, in particular to a loading design method for a high vertical fin vertical load of a full-scale fatigue test. Firstly, a full-aircraft finite element model is established, according to the size and magnitude of the vertical fin vertical load, the loading form of the load is determined, the loading form is determined, full-aircraft loads are calculated, and joint loads are converted to an adjacent fuselage frame according to the equivalence principle, finally, the durability of connection key parts of the vertical finand the fuselage is analyzed and calculated. By adopting the method, the problems that the loading system of the vertical fin vertical load is complex and difficult to design are solved.

Description

technical field [0001] The invention belongs to the field of aviation fatigue damage tolerance test, and in particular relates to a high vertical tail vertical load loading design method for full-scale fatigue test. Background technique [0002] The full-scale fatigue test of an aircraft is an important means to verify whether the structural life of the airframe can meet the service requirements, and the test load application method determines the scale of the test to a certain extent. Before formulating the test implementation plan, the designer needs to do a lot of theoretical analysis and calculation to ensure that the test loading design can not only truly simulate all load states, but also consider the test implementation scale and test cycle. [0003] For the high vertical tail structure layout, the vertical tail is located on the upper part of the rear fuselage frame, and the vertical load is mainly its own inertial load. Due to the structural characteristics of the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60G06F17/50
CPCB64F5/60G06F30/15G06F30/23
Inventor 王亚芳王新波闵强秦剑波
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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