Abstract

This paper introduces a method for testing the traction load on the nose landing gear of an aircraft. After analyzing and simplifying the nose landing gear of an aircraft type, a mechanical model is established. By analyzing the force balance of the nose landing gear under the traction load, the linear mapping position of the traction load is determined, and the test modification of the mapping position is used to realize the test of the nose landing gear traction load. The method achieves the ability to measure the direct load on the aircraft nose landing gear quickly, cost-effectively, and efficiently in the actual engineering environment of the aircraft, so that the strength of the aircraft nose landing gear can be analyzed.

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