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a loading device

A loading device and load technology, which is applied in the field of fatigue testing of aircraft structures, can solve problems such as cumbersome process, restricted test efficiency, and long test period

Active Publication Date: 2021-09-03
CHINA AIRPLANT STRENGTH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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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

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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 application belongs to the technical field of fatigue testing of aircraft structures, and specifically relates to a load loading device, comprising: a support beam with a groove on it; two side walls opposite to the groove have strip-shaped holes; an actuator with a piston rod It is used to connect to the aircraft structure so as to be able to apply loads to the aircraft structure; the slide rod is connected to the cylinder of the actuator, one end of which extends into a bar-shaped hole, and the other end extends into another bar-shaped hole, which can be moved along the bar. Sliding in the extending direction of the shaped hole can drive the actuator to move or move under the drive of the actuator, thereby adjusting the direction in which the actuator applies load to the aircraft structure.

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...

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Application Information

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