Catapulting impact ground verification test method

A verification test and ground technology, applied in the field of aircraft, can solve the problems such as the inability to accurately simulate the dynamic response of the landing gear and the body structure under the impact of ejection, the complex time history of aircraft loading, and the inability to reflect the impact, etc., to reduce the scale and reduce the test. Difficulty and the effect of reducing design and manufacturing costs

Inactive Publication Date: 2018-09-07
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] 1) The results of the whole body are used as the test piece, the scale of the test piece is large, and the test cost is very high;
[0005] 2) The actual loading time history of the aircraft during the ejection take-off process is very complicated, and the static test cannot reflect the influence of various factors such as the rated shear load of the tension pin, the ejection rod load, and the impact time on the ejection impact process;
[0006] 3) Impact loading and static loading have completely different effects on the structure, and the static test process cannot accurately simulate the dynamic response of the landing gear and the body structure under the ejection impact
[0007] At present, there is no ground test verification method for simulating the ejection impact process in China that can be used for reference.

Method used

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Examples

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Effect test

Embodiment 1

[0035] A kind of ejection impact ground verification test method, it is characterized in that: comprise the following steps:

[0036] 1) According to the main force transmission path of the shipboard aircraft ejection load, select a section from the airframe structure as the ground verification test piece and the airframe test section;

[0037] 2) Install overload sensors and paste strain sensors on the main force transmission path and key parts of the landing gear and the body structure, and set up laser displacement sensors;

[0038] 3) Fix and constrain the rear end of the test piece on the load-bearing wall, and place a rubber pad at the wheel center of the landing gear to restrain the vertical downward displacement of the test piece during the load application process;

[0039] 4) Screen the ejection and take-off conditions of the carrier-based aircraft, determine the ejection impact ground verification test load, perform static calculations on the ejection operating cond...

Embodiment 2

[0049] A kind of ejection impact ground verification test method, it is characterized in that: comprise the following steps:

[0050] 1) According to the main force transmission path of the shipboard aircraft ejection load, select a section from the airframe structure as the ground verification test piece and the airframe test section;

[0051] 2) Install overload sensors and paste strain sensors on the main force transmission path and key parts of the landing gear and the body structure, and set up laser displacement sensors;

[0052] 3) Fix and constrain the rear end of the test piece on the load-bearing wall, and place a rubber pad at the wheel center of the landing gear to restrain the vertical downward displacement of the test piece during the load application process;

[0053] 4) Screen the ejection and take-off conditions of the carrier-based aircraft, determine the ejection impact ground verification test load, perform static calculations on the ejection operating cond...

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PUM

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Abstract

The invention relates to the related field of airplanes, in particular to a ground verification test method for simulating catapult-assisted take-off impact response during catapult-assisted take-offof an airplane. The ground verification test method for simulating the catapult-assisted take-off impact response during the catapult-assisted take-off of the airplane comprises the steps of selectingone section from an airframe structure as a ground verification test piece and an airframe test section according to a main force transmission path of catapult load of a carrier plane; placing overload sensors and bonding strain sensors on the main force transmission paths and key parts of a landing gear and the airframe structure; arranging laser displacement sensors; fixedly restricting the rear end of the test piece on a force bearing wall; and placing a rubber pad at the wheel center of the landing gear to restrict the vertical downward displacement of the test piece in the load applyingprocess. According to the ground verification test method for simulating the catapult-assisted take-off impact response during the catapult-assisted take-off of the airplane, as the main airframe structures on the front landing gear and the main force transmission paths are used as test pieces, the scale of the test pieces is greatly reduced, and the design and manufacturing cost is reduced. Through coordinated loading of multi-passage oil cylinders, the correctness of the load in the whole catapulting process is guaranteed.

Description

technical field [0001] The invention relates to related fields of aircraft, in particular to a ground verification test method for simulating the impact response of ejection when the aircraft is ejected. technical background [0002] Nowadays, catapult takeoff is the most ideal way for carrier-based aircraft to take off. During the catapult takeoff process, the aircraft ejection lever is connected and tensioned with the reciprocating vehicle, and the restraint lever is disconnected. The aircraft slides with the reciprocating vehicle, and then takes off. It is a typical dynamic impact process. Because the impact has a huge impact on the aircraft structure, especially the nose landing gear and its connection structure, in order to ensure the safety of take-off, it is necessary to conduct ground test verification on the nose landing gear and the body structure of the carrier-based aircraft. [0003] At present, the simulation of the ejection process of carrier-based aircraft a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 朱小龙李永刚张浩成
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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