Load system and method combining force control and position control and used for airplane structural strength tests

A technology of strength test and aircraft structure, applied in the direction of aircraft component testing, aircraft parts, transportation and packaging, etc., can solve the problems of large active load of test piece deformation, and achieve the effect of simple installation and strong practicability

Active Publication Date: 2013-04-17
CHINA AIRPLANT STRENGTH RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to propose a combined loading system using force control and position control to solve the problem that the test piece is deformed greatly and the active load needs to be applied across the interference piece

Method used

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  • Load system and method combining force control and position control and used for airplane structural strength tests
  • Load system and method combining force control and position control and used for airplane structural strength tests

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Embodiment Construction

[0025] Below in conjunction with accompanying drawing, the present invention will be further described:

[0026] refer to figure 1 , the force control and position control combined loading system used in the aircraft structural strength test of the present invention includes a force control actuator 3, a position control actuator 8, a force control sensor 9, control modules 2 and 7, and a connecting loading device 1 and 5. A loading device 13 and a displacement sensor 10 for straddling the interference piece. Among them, the two ends of the loading device for interfering parts are respectively provided with loading devices for connection, and each loading device for connection is connected with the force control actuator and the position control actuator respectively, and the force control actuator and the position control actuator are respectively connected to each other. A control module for controlling loading and corresponding force control sensors and position control se...

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Abstract

The invention relates to a load test technology and in particular to a load system and method combining force control and position control and used for airplane structural strength tests. The load system combining force control and position control comprises a force control actuator cylinder, a position control actuator cylinder, a force control sensor, a displacement sensor, a control module, load devices used for connection and a load device used for crossing interference pieces. Two ends of the load device used for crossing interference pieces are respectively provided with the load devices used for connection, each load device used for connection is respectively connected with the force control actuator cylinder and the position control actuator cylinder, the force control actuator cylinder is provided with a load module controlling load and the force control sensor, and the position control actuator cylinder is provided with the control module used for control load. The load system and method combining force control and position control controls the force control actuator cylinder and the position control actuator cylinder to respectively perform load on two ends of loading devices according to control commands of load spectrums, the load devices can move along deformation of test pieces, and interference of the load devices and the test pieces during testing process can be avoided.

Description

technical field [0001] The invention relates to a test loading technology, in particular to a force control and position control combined loading system and method for the strength test of an aircraft structure. Background technique [0002] In the static / fatigue strength test of the full-scale aircraft structure, for the case where the loading equipment needs to span the interfering parts during loading, in the past, the combination of active and passive loading is used to apply the load, that is, the load of the test piece needs to be controlled by a An active loading point where the moving cylinder applies the load, and a passive loading point where the load is applied using only a connector connection. If the deformation of the test piece is large, in the process of applying the load, since the passive loading point cannot follow the movement, the active loading point needs to be used as the cylinder to perform deformation compensation. The greater the deformation of the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/00B64F5/60
Inventor 任红云宋鹏飞杜峰邓文亮何月洲夏龙
Owner CHINA AIRPLANT STRENGTH RES INST
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