Ground load determination method of multi-fulcrum airplane

A determination method, multi-pivot technology, applied in the field of aviation landing gear

Inactive Publication Date: 2013-09-25
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is: to propose a multi-support aircraft ground load calculation method, this method can solve the aircraft ground load calculation problem when the main landing gear of the aircraft is a multi-strut type layout, and provide support for the multi-strut type landing gear design

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  • Ground load determination method of multi-fulcrum airplane
  • Ground load determination method of multi-fulcrum airplane
  • Ground load determination method of multi-fulcrum airplane

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Embodiment

[0088] Taking this method for a certain type of aircraft ground load calculation that adopts a multi-pillar landing gear layout as an example, the present invention is further described in detail, and the specific steps are as follows:

[0089] 1. Determine the uneven load distribution coefficient of the multi-strut landing gear;

[0090] The principle of determining the uneven load distribution coefficient of the multi-strut main landing gear is the principle of combining numerical simulation, simulation analysis and statistical analysis of measured data.

[0091] 1.1. Numerical simulation for analysis:

[0092] 1.1.1. The layout of the main landing gear of this type of aircraft adopts the layout of three pillars on each side of the aircraft, and the specified landing angle of the aircraft is 8°. Select: θ 1 =2°, θ 2 =4°, θ 3 =6°, θ 4 =8°.

[0093] 1.1.2. The average value V of the maximum vertical load of all main landing gear on one side at the corresponding angle, as...

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Abstract

The invention belongs to the field of aviation undercarriages and particularly relates to a ground load determination method of a multi-fulcrum airplane. According to the ground load determination method of the multi-fulcrum airplane, by means of equivalent conversion, a static indeterminacy calculation of the multi-fulcrum airplane is converted into a static determinacy calculation, further uneven distribution coefficients of multi-strut loads are introduced, load boundary values in every structural design of undercarriages can be effectively guaranteed, therefore, certain guiding functions are provided for optimizing the structural designs of the multi-strut undercarriages and improving the accuracy of the design of the multi-strut undercarriages. Besides, the calculation idea of the ground load determination method of the multi-fulcrum airplane is clear and rigorous, the calculation method is reliable and easy to comprehend and master, so that the ground load determination method of the multi-fulcrum airplane has a broad application prospect in engineering design of the multi-strut undercarriages. During the actual usage, the quantity of the research trials of the loads of the multi-strut undercarriages can be reduced by applying the ground load determination method of the multi-fulcrum airplane, so that obvious advantages of saving the design cost and shortening the design cycle of the multi-strut undercarriages can be achieved.

Description

technical field [0001] The invention belongs to the field of aviation landing gear, and in particular relates to a method for determining the ground load of a multi-fulcrum aircraft. Background technique [0002] The aircraft generally adopts a three-point statically determinate support method on the ground. In the early days, the rear three-point layout was mostly used, and now most of the front three-point layout is used. For the traditional three-point layout, the calculation of the ground load is stipulated in the corresponding codes. However, with the continuous development and extension of aircraft use, the take-off weight of aircraft is also increasing. Especially for large transport aircraft, more and more multi-pivot layout schemes based on the first three-point layout are adopted. However, when the main landing gear on both sides of the aircraft is a multi-pillar landing gear layout, the current calculation method for the ground load of the landing gear is no long...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 罗务揆
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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