A design method for full-scale fatigue test fuselage heading load loading

Abstract

The invention discloses a full scale fatigue test fuselage course load loading design method, and belongs to the field of aviation fatigue damage tolerance test. The full scale fatigue test fuselage course load loading design method comprises the following steps that firstly, a fuselage course total load in all working conditions is obtained; secondly, an airplane course loading scheme is determined, and a plurality of course loading connectors are mounted by adopting a mode of conjoint riveting with long crosspieces and skins or a mode of conjoint riveting with the long crosspieces, a fuselage frame and the skins; then connector load upper limits of the course loading connectors are calculated, a loading scheme of all the course loading connectors and a distribution load of all the course loading connectors are determined according to the course total load; durability of structure connecting in all the loading connectors is analyzed, and the strength of a weak part is improved; and finally, course load loading is conducted. According to the full scale fatigue test fuselage course load loading design method, the problems that a fuselage course load loading system is complete and difficult to design are solved.

Description

technical field [0001] The invention belongs to the field of aviation fatigue damage tolerance test, in particular to a full-scale fatigue test fuselage heading load loading design method. Background technique [0002] Aircraft full-scale fatigue test is the embodiment of the highest technical level in the field of aviation fatigue damage tolerance test, and the test loading design is related to the implementation scale of full-scale fatigue test. When the designers formulate the test implementation plan, they have to do a lot of theoretical analysis and calculation to ensure that the test loading design can not only truly simulate the force state of the aircraft, but also consider the scale of the test implementation and coordinate the application of loads in all directions on the whole aircraft. [0003] For the application of the fuselage heading load, refer to the research on the existing types of heading load application. Most of them are applied in the form of adhesive...

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Problems solved by technology

[0003] For the application of the fuselage heading load, refer to the research on the existing types of heading load application. Most of them are applied in the form of adhesive tape. This design is a conventional design technology that can ensure the application of the load. However, due to the The layout and load size are limited by the strength of the fuselage structure, so the layout of the fuselage tapes will be more and scattered, the lever system is too heavy, and it is easy to cause interference with the vertical and lateral load layout of the fuselage

[0004] Regarding the research on the full-scale fatigue test of aircraft, there are few researches on domestic public data, which are limited by the current domestic technical level and contain other factors. There are more researches on foreign public data, but most of them are on the airframe configuration and test hardware matching , A brief introduction to the load situation, failed to give a practical fatigue test design method for the fuselage structure itself in terms of its stress and load characteristics

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