大型无人机主结构耐久性试验加载技术

doi:10.7527/S1000-6893.2022.25887

Abstract

Abstract: In order to verify the fatigue life of the main structure for a large Unmanned Aerial Vehicle (UAV) under the designed load spectrum and expose the weak part of the structure, improve structural detail design and test reference of manufacturing technology for full-scale main structure durability test, some new technologies were proposed, such as the design of the multifunctional support fixture, the optimization of the UAV structure load, the coordinated compilation of the comprehensive load and deduction load spectrum, the application of new tension and compression pad elastomer, and the design of special deduction device for the actuator, etc. Aiming at such difficulties like aircraft constraints, load optimization, load spectrum compilation, precise loading and other test loading difficulties were brought by the advanced layout design of this model of UAV and the structure design, comparison and analysis of related test loading technologies and series verification of new technologies were performed. Based on the phased test verification of the half-life fatigue of the aircraft, these technologies are reasonable, feasible, stable, and reliable and proved to be able to ensure the normal operation of the test.

Key words: large UAV, durability test, testing aircraft constraints, load optimization, load spectrum complication, loading device

CLC Number:

V216.1

CUI Ming, FENG Jianmin, MI Zheng, GUO Junhao. Loading technology for main structure of large UAV durability test[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(6): 525887-525887.

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Loading technology for main structure of large UAV durability test

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