Double-beam type long straight wing load processing method

A processing method and beam-type technology, which is applied in the field of load processing and loading of wing box sections in the static strength test of full-scale aircraft structures, can solve the problems of large load processing workload, many lever loading stages, and low load processing efficiency. , to achieve the effect of improving the effective utilization rate, reducing the number of processing and replacement, and improving the efficiency

Active Publication Date: 2016-06-29
CHINA AIRPLANT STRENGTH RES INST
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Problems solved by technology

[0003] In order to solve the problems of large load processing workload of the double-beam long straight wing box section, many lever loading stages and low load processing efficiency, this patent provides a double-beam long straight wing load processing method, which is characterized in that it includes the following steps :

Method used

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  • Double-beam type long straight wing load processing method
  • Double-beam type long straight wing load processing method
  • Double-beam type long straight wing load processing method

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Embodiment Construction

[0018] The flow chart of realizing the load processing of double-spar long straight wing with computer program is as follows: figure 2 shown.

[0019] The program is divided into two parts: data verification and data processing. All calculation programs are completed using VC++.

[0020] The present invention provides a kind of double beam type long straight wing load processing method, it is characterized in that, comprises the following steps:

[0021] 1) According to the finite element node number and position of each rib of the wing, tapes are selectively arranged near the front and rear beams of each rib, such as figure 1 As shown, the load value of each tape is the maximum load value that the tape can bear, and then calculate the lever end coordinates of the front beam and rear beam and their lever system according to the tape position and tape load value of each rib front beam and rear beam The load value that can be tolerated is called the maximum load value of its ...

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Abstract

The invention provides a double-beam type long straight wing load processing method. The double-beam type long straight wing load processing method comprises the following steps: according to a finite element node number and position of each rib of a wing, selectively distributing adhesive tapes around the front beam and the back beam of each rib, wherein the load value of each adhesive tape is the maximum load value that the adhesive tape can bear; and according to the positions of the adhesive tapes of the front beam and the back beam of each rib, respectively calculating the lever end coordinates of the front beam and the back beam, and a load value that the lever system can bear, wherein the load value is the maximum bearing value of the lever system; the lever end coordinates of the front beam and the back beam of each rib are respectively the front resultant force point and the back resultant force point; and the lever systems for the front resultant force point and the back resultant force point are uniformly named as a special lever.

Description

technical field [0001] This patent relates to a load processing method for a double-spar long straight wing, in particular to a load processing and loading method for a wing box section applied to a full-scale aircraft structure static strength test of a double-spar long straight wing. Background technique [0002] The static strength test of the full-scale aircraft structure is to study the static strength characteristics of the aircraft and its component structures under the action of static loads. The purpose is to verify whether the aircraft structure can meet the structural strength design and static strength specification requirements through tests. The wing is an important part of the aircraft. In the structural static test, it is necessary to load the wing box to simulate the bearing and deformation of the wing in different flight states. At present, various aircraft design institutes conduct numerical analysis on the finite element model of the aircraft wing. The wi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M13/00
Inventor 李涛王刚张建锋李晓冬张辉祥夏峰
Owner CHINA AIRPLANT STRENGTH RES INST
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