A combination of force control and position control loading system and method for strength test of aircraft structure

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

Active Publication Date: 2016-03-30
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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  • A combination of force control and position control loading system and method for strength test of aircraft structure
  • A combination of force control and position control loading system and method for strength test of aircraft structure

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Embodiment Construction

[0025] The present invention will be further described below in conjunction with the accompanying drawings:

[0026] refer to figure 1 , the force control and position control combined loading system used for the strength test of the aircraft structure of the present invention includes a force control actuator 3, a position control actuator 7, a force control sensor 8, control modules 2 and 6, and a connection loading device 1 and 6. 5. Loading device 12 and displacement sensor 9 for spanning the interference piece. Among them, the two ends of the loading device for spanning the interference piece are respectively provided with loading devices for connection, and each loading device for connection is respectively connected with the force-controlled actuator and the position-controlled actuator, and the force-controlled actuator and the position-controlled actuator are respectively connected. A control module for controlling loading and a corresponding force control sensor and...

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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 full-scale aircraft structures, in the case where the loading equipment needs to span the interfering parts during loading, a combination of active and passive loading methods was used to apply the load, that is, the load of the test piece needs to be applied by a An active loading point where the ram applies the load and a passive loading point where only a connector is used to apply the load. If the deformation of the test piece is large, in the process of applying the load, since the passive loading point cannot follow, the active loading point actuator needs to compensate for the deformation. , which may cause the stroke of the actuator to fail to meet the test requirements, and the collision b...

Claims

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Application Information

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Patent Type & Authority Patents(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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