A helicopter landing gear loading device

A loading device and landing gear technology, which is applied in the direction of measuring devices, aircraft component testing, mechanical component testing, etc., can solve the problems of difficult upward loading, unsatisfactory design effect, and complicated bench structure, etc., so as to achieve easy installation, Strong practicability, simple and convenient operation

Active Publication Date: 2022-07-01
CHINA HELICOPTER RES & DEV INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

When the landing gear is in the middle of the fuselage, it is not easy to load upwards
[0003] In the past, when this type of test was carried out, it was possible to design a special bench and install the steering pulley by turning the load, but it was often limited by the space, and the design effect was not ideal; it was also possible to directly design a fixed bench and install the actuator to apply the compressive load. This brings about the complex structure of the bench and the pressure load applied by the actuator is prone to instability.

Method used

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  • A helicopter landing gear loading device
  • A helicopter landing gear loading device
  • A helicopter landing gear loading device

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Embodiment Construction

[0027] In order to describe the present invention more clearly and in detail so as to facilitate the understanding of those skilled in the art, the specific embodiments of the present invention are described with reference to the accompanying drawings.

[0028] like Figure 1-4 As shown, a helicopter landing gear loading device is used to load test a helicopter landing gear test piece. The helicopter landing gear test piece includes a fuselage frame 100 and a landing gear 200. The landing gear 200 is located in the The lower part of the body frame 100 is characterized in that the loading device includes a long lever assembly 1, a connecting wire 2, a short lever assembly 4, a first adapter 5, a second adapter 6, and a wheel support assembly 7;

[0029] The long lever assembly 1 includes an upper long lever 11, a lower front long lever 12, and a lower rear long lever 13 that are arranged in parallel up and down along the direction parallel to the plane of symmetry of the helico...

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Abstract

The invention belongs to the technical field of static test of helicopter body parts, in particular to a helicopter landing gear loading device. It comprises a long lever assembly (1), a connecting wire rope (2), a short lever assembly (4), a first adapter (5), a second adapter (6), and a wheel support assembly (7). The device of the invention adopts the wheel dummy and the three-level combined lever to realize upward loading according to the force requirement during the test, and the size and tolerance of the wheel dummy and the real one are consistent, so as to ensure that the force state is truly reflected when the loading force is applied. The wheel dummy and lever system are designed to avoid interference with the fuselage when the landing gear in the middle of the fuselage is pulled toward the load by the actuator, and the installation is convenient and the loading is stable. The device has stable structure and reliable performance, and can well meet the test requirements.

Description

technical field [0001] The invention belongs to the technical field of static test of helicopter body parts, and in particular relates to a helicopter landing gear loading device. Background technique [0002] Helicopter landing gear is one of the most important parts of the airframe structure, and its on-board connection test is an indispensable part of the helicopter design process. When the landing gear is in the middle of the body, it becomes less easy to load upwards. [0003] In the past, when this type of test was carried out, a special bench could be designed to install steering pulleys through steering loading, but it was often limited by space and the design effect was not ideal. This brings about the complex structure of the bench and the easy instability of the actuator when the compressive load is applied. [0004] The key step of the test is to design a fixture that can easily bypass the fuselage for installation and upward loading, and the load application m...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M13/00B64F5/60
CPCG01M13/00B64F5/60
Inventor 马子广王卫卫王宇
Owner CHINA HELICOPTER RES & DEV INST
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