Active control method of airplane course constrained point errors

Abstract

The present invention relates to an active control method of airplane course constrained point errors. The method comprises the following steps that: the step 1: a position control actuating cylinder,a displacement sensor and a force measuring sensor are installed at a test machine support portion course constrained point, wherein the position control actuating cylinder and the displacement sensor form closed-loop control, and the force measuring sensor monitors size of the stress of the test machine support portion course constrained point in real time; the step 2, a course force control active load point is selected at a non-checking portion of the test machine, and the position control actuating cylinder and the displacement sensor are installed to allow load of the active load point to be transmitted to a course constrained point; and the step 3, the constrained point force measuring sensor and a selected non-checking portion course force control actuating cylinder form a closed-loop control system to apply a course constrained point target load to the force control actuating cylinder so as to convert passive load of the constrained point to active load. Through construction of a closed-loop control condition, the active control method of airplane course constrained point errors can actively control the course constrained point errors into corresponding load control precision, the control process can be automatically performed, and when the test is continuously operated, the control process can still have an active control effect; and moreover, the load control precision is adjustable, the application is flexible and convenient, and the operation is simple.

Description

technical field [0001] The invention relates to an automatic control technology, especially when it is used in an aircraft structure strength test and needs to check the loading accuracy of a passively loaded heading constraint point. Background technique [0002] At present, in the aircraft structural strength test, the support method of the test machine generally adopts six degrees of freedom statically indeterminate constraints. Constrained lateral displacement, etc. Due to the limited installation space at the test site, only large-range load cells and position control actuators are installed at the course constraint points, which can only play the role of position control and force monitoring. In the test, there are many factors affecting the loading accuracy of the heading constraint points, which are mainly divided into four aspects: the attitude of the testing machine, the deformation of the testing machine structure, the installation accuracy of all test loading po...

AI Technical Summary

Problems solved by technology

Therefore, when the strength assessment of the supporting parts of the testing machine is carried out and the supporting parts need to be used as constraints, under the existing test conditions, it is impossible to install additional heading force control loading equipment at the constraint points. The system can only passively apply the balance load of the whole machine, and at the same time, under the joint action of various factors affecting the loading accuracy, its loading accuracy cannot meet the requirement of 1% DL

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