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Load loading device

A loading device and load technology, which is applied in measurement devices, aircraft component testing, instruments, etc., can solve the problems of cumbersome process, long test period and restricting test efficiency.

Active Publication Date: 2020-06-05
CHINA AIRPLANT STRENGTH RES INST
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  • Abstract
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Problems solved by technology

[0003] At present, in the fatigue test of aircraft structure, the position of the actuator is mostly adjusted by manual disassembly and assembly to realize the adjustment of the loading direction of the aircraft structure to adapt to different fatigue assessment states. The process of this technical solution is cumbersome and requires shutdown. , which severely restricts the test efficiency and makes the test cycle too long

Method used

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Embodiment Construction

[0026] 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.

[0027] 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 structure fatigue tests, and particularly relates to a load loading device, which comprises a support beam provided with a groove, strip-shapedholes are formed in two opposite side walls of the groove; an actuator cylinder, a piston rod of the actuator cylinder is used for being connected to an aircraft structure so as to apply a load to the aircraft structure; a sliding rod which is connected with a cylinder body of the actuating cylinder, one end of the sliding rod extends into one strip-shaped hole, the other end of the sliding rod extends into the other strip-shaped hole, and the sliding rod can slide in the extending direction of the strip-shaped holes, so that the actuating cylinder can be driven to move or driven by the actuating cylinder to move, and the direction of load applied to the aircraft structure by the actuating cylinder can be adjusted.

Description

technical field [0001] The application belongs to the technical field of aircraft structure fatigue testing, and in particular relates to a load loading device. Background technique [0002] In the aircraft structure fatigue test, corresponding to the various changing states of the aircraft in an aircraft cycle, there are various fatigue assessment states for the aircraft structure design. Under different fatigue assessment states, the direction of the load on the aircraft structure There are differences. When changing the fatigue assessment state, adjust the load direction of the actuator to the aircraft structure accordingly. [0003] At present, in the fatigue test of aircraft structure, the position of the actuator is mostly adjusted by manual disassembly and assembly to realize the adjustment of the loading direction of the aircraft structure to adapt to different fatigue assessment states. The process of this technical solution is cumbersome and requires shutdown. , w...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60G01M13/00
CPCB64F5/60G01M13/00
Inventor 王鑫涛尹伟高建
Owner CHINA AIRPLANT STRENGTH RES INST
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