A non-collinear connection device for loading levers in aircraft testing and its design method

By designing a U-shaped force transmission rod and a detachable nut fixing method, the problem of the lever connection point and the loading point not being on the same straight line in a confined space was solved. This enabled reliable connection and application of test loads in a confined space, meeting the requirements of aircraft structural fatigue testing, and improving test efficiency and device maintenance convenience.

CN121404543BActive Publication Date: 2026-07-17CHINA AIRPLANT STRENGTH RES INST
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Patent Information

Application Number
CN202511560676.0
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2025-10-29
Publication Date
2026-07-17
Estimated Expiration
2045-10-29

AI Technical Summary

Technical Problem

In aircraft structural fatigue tests, it is difficult to ensure that the lever connection point and the aircraft loading point are on the same straight line in a confined space. Existing connection methods are limited and cannot meet the test requirements.

Method used

A non-collinear connection device for loading levers in aircraft testing is designed. By changing the force transmission rod of the connection joint to a U-shaped cross-section, the force transmission rod is vertically inserted into the force transmission hole and fixed with a detachable nut. Combined with a spherical bearing and a polyurethane block, the reliability and flexibility of the connection are ensured.

Benefits of technology

It enables the application of test force loads in confined spaces, has a reliable connection method, is easy to install, meets the requirements of aircraft structural fatigue testing, and improves test efficiency and device maintenance convenience.

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Abstract

This invention relates to the field of aircraft structural fatigue testing technology, and discloses a non-collinear connection device for aircraft test loading levers and its design method. The connection joint is designed with a U-shaped cross-section, allowing the force transmission rod to be inserted vertically into the force transmission hole of the force transmission lug. This changes the force transmission path from the lever connection point to the aircraft test loading point, enabling the application of test loads in confined spaces. It features a simple structure, reliable connection, and convenient installation. In the design process of the loading lever for the non-collinear connection device, the lower limit of the force transmission rod diameter, the lower limit of the bolt hole diameter, and the minimum distance from the center of the bolt hole to the edge of the U-shaped support plate are analyzed in advance. Then, based on these key parameters, the structural design of the loading lever, the force transmission lug, and the connection joint is carried out to ensure that a structurally reasonable and high-performance non-collinear connection device for aircraft test loading levers can be designed to meet the requirements of aircraft structural fatigue testing.
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