Airplane steering engine electro-hydraulic loading system synchronously controlled through parallel connection of double valve controlled hydraulic cylinders

Abstract

The invention relates to an airplane steering engine electro-hydraulic loading system synchronously controlled through the parallel connection of double valve controlled hydraulic cylinders. The airplane steering engine electro-hydraulic loading system synchronously controlled through the parallel connection of the double valve controlled hydraulic cylinders comprises a first controller, a secondcontroller, a third controller, a first servo valve, a second servo motor, a third servo motor, a fourth servo motor, a first hydraulic cylinder, a second hydraulic cylinder, two rubber metal buffer springs, two force sensors, two first position sensors and two second position sensors. According to the airplane steering engine electro-hydraulic loading system synchronously controlled through the parallel connection of the double valve controlled hydraulic cylinders provided by the invention, not only is the frequency response of the loading system improved, but also the forced flows in the hydraulic cylinders are reduced; and meanwhile, by adopting parallel connection control of the two hydraulic cylinders, the output force of a single hydraulic cylinder is reduced, the cost is reduced, meanwhile, the redundant force in the system is reduced, and the stability and the loading accuracy of the loading system are improved.

Description

technical field [0001] The invention belongs to the technical field of civil aviation equipment, and in particular relates to an electro-hydraulic loading system for an aircraft steering gear controlled in parallel and synchronously by double-valve-controlled hydraulic cylinders. Background technique [0002] At present, in the field of aircraft control, the aircraft steering gear is an important flight control servo component. Under laboratory conditions, the electro-hydraulic loading system is usually used to simulate the changes of various force loads on the aircraft steering gear and its servo system. It is mainly used to complete the inspection and testing of static and dynamic technical indicators. figure 1 It is a structural block diagram of the electro-hydraulic loading system for aircraft rudders commonly used at present. Such as figure 1 As shown, the system includes a control computer 1, an electro-hydraulic servo valve 2, a hydraulic cylinder 3, a rubber-metal ...

AI Technical Summary

Problems solved by technology

[0003] However, the electro-hydraulic loading system of the aircraft steering gear has the following problems: there is a problem of low frequency response in the electro-hydraulic servo valve 2, which causes the signal feedback to lag and generate redundant force; at the same time, the electro-hydraulic loading system of the aircraft steering gear drags the piston rod of the hydraulic cylinder 3 At this time, a forced flow will be generated in the two chambers of the hydraulic cylinder 3, and the electro-hydraulic servo valve 2 will change its opening according to the movement speed of the aircraft steering gear 5 and the loading command, because the electro-hydraulic servo valve 2 is in the forced flow It is suppressed after it is generated, so there will be a certain lag in time, and the redundant force generated at this time cannot be completely eliminated

Moreover, when the acceleration of the aircraft steering gear 5 changes, since the forced flow of the two chambers of the hydraulic cylinder 3 has not been eliminated in time, the redundant force of the system will become larger, thereby affecting the loading accuracy of the system

Images