Hangkong gongcheng jinzhan (Jun 2023)
Balancing load design for full-size static strength test of civil aircraft in front fuselage serious condition
Abstract
In the full-size static strength test of aircraft, the traditional balancing load scheme is used to ensure the loading accuracy to simplify the complex loading scheme, and the load in non-assessment area is simplified to several loading points. For the thin-wall structure, the balancing in non-assessment area has great influence on assess-ment area. Taking a front fuselage serious condition of a certain civil aircraft as an example, the balancing load scheme of full-size static strength test is studied based on the finite element model. By comparing the internal force solution of analysis mode load and traditional test mode balancing schemes, the traditional load balancing scheme of full-size static strength test is optimized. The results show that the internal force under optimized test load is basically identical with that under theoretical design load. The Saint-Venant principle is inapplicable to the thin-wall structure of civil aircraft. The load balancing of full-size static strength test should accordance with the stress of ac-tual condition, which can achieve the purpose of test verification.
Keywords