Fatigue test device and method thereof

A technology of fatigue test and loading device, applied in the direction of aircraft component testing, etc., can solve the problems of lack of and difficult to obtain effective test results, and achieve the effect of effective test results

Active Publication Date: 2020-11-17
CHINA AIRPLANT STRENGTH RES INST
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Problems solved by technology

[0004] When performing fatigue tests on the rear fuselage structure of an aircraft, how to accurately simulate its loaded state during flight is of great significance for obtaining accurate test results. At present, when performing fatigue tests on the rear fuselage structure of an aircraft, there is a lack of accurate simulation It is an effective method for the rear fuselage structure of the aircraft to be loaded under the flight state, and it is difficult to obtain effective test results

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  • Fatigue test device and method thereof
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[0051] In order to make the technical solution of the present application and its advantages clearer, the technical solution of the present application will be further clearly and completely described in detail below in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only part of the application Examples are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the drawings, and other relevant parts can refer to the general design. In the case of no conflict, the embodiments in the application and the technologies in the embodiments Features can be combined with each other to obtain new embodiments.

[0052] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the application shall have the usual meanings und...

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Abstract

The invention belongs to the technical field of aircraft rear fuselage structure fatigue tests, and particularly relates to a fatigue test device, which comprises two vertical fin vibration load loading devices, wherein each vertical fin vibration load loading device is used for correspondingly connected with a vertical fin of the aircraft rear fuselage structure for applying a vibration load to the corresponding vertical fin two vertical tail gas dynamic load loading devices, each vertical tail gas dynamic load loading device being used for being correspondingly connected to one vertical finof the aircraft rear fuselage structure to apply aerodynamic load to the corresponding vertical fin; and an engine frame vibration load loading device which is used for being connected to an engine frame of an aircraft rear fuselage structure and applying a vibration load to the engine frame. Furthermore, the invention relates to a fatigue test method which is implemented on the basis of the fatigue test device, and a relatively more effective test result can be obtained when the fatigue test method is applied to the aircraft rear fuselage structure fatigue test.

Description

technical field [0001] The application belongs to the technical field of fatigue test of aircraft rear fuselage structure, and in particular relates to a fatigue test device and a method thereof. Background technique [0002] At present, when conducting aircraft fatigue tests, the dynamic characteristics of the aircraft structure during flight are mostly ignored, and the load environment of the aircraft structure during flight cannot be truly simulated, resulting in deviations between the test structure and the actual situation. [0003] The rear fuselage structure of the aircraft includes the engine frame and two opposite vertical fins, which are subjected to complex loads during the flight of the aircraft. Among them, the engine frame bears the vibration load caused by the engine when the aircraft is flying, and the vertical fin bears the vibration load caused by the air flow passing through its surface. Vibration loads of eddy currents, as well as withstand aerodynamic lo...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 王彬文张治君潘凯何石王龙
Owner CHINA AIRPLANT STRENGTH RES INST
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