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Active thermal control distributed electro-hydraulic servo steering engine

An electro-hydraulic servo, distributed technology, applied in the field of aircraft design, can solve problems such as reliability reduction

Active Publication Date: 2021-04-27
沈阳飞机设计研究所扬州协同创新研究院有限公司
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AI Technical Summary

Problems solved by technology

[0004] Aiming at the problems of abnormal wear and reliability reduction caused by the internal heating of the aircraft distributed electro-hydraulic servo steering gear, the present invention proposes an active thermal control distributed electro-hydraulic servo steering gear that can realize the internal core zero of the distributed electro-hydraulic servo steering gear. The active control of component temperature can ensure that the internal temperature is relatively constant according to different working conditions and ambient temperature, so that the steering gear is always in a high-performance working state

Method used

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Embodiment Construction

[0017] An active thermal control distributed electro-hydraulic servo steering gear, including a servo motor 1, a bidirectional hydraulic pump 2, an overflow valve, a rudder surface 4, an actuator 5, an evaporator, a compressor 7, an expansion valve 8 and a condenser device 9;

[0018] The double-rotation hydraulic pump 2 is driven by the servo motor 1, the output flow of the double-rotation hydraulic pump 2 is controlled by the rotating speed of the servo motor 1, the double-rotation hydraulic pump 2 controls the speed of the piston rod of the actuator cylinder 5, and the piston rod Connect the steering surface 4 to control the deflection rate of the steering surface 4; the compressor 7 is driven by the servo motor 1 to improve the integration of the whole system.

[0019] The output ports of the dual-rotational hydraulic pump 2 are respectively arranged with evaporator A6-1 and evaporator B6-2, and the low-pressure, gaseous refrigerant evaporates and absorbs heat when it circ...

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Abstract

The invention belongs to the field of aircraft design, and relates to an active thermal control distributed electro-hydraulic servo steering engine. The active thermal control distributed electro-hydraulic servo steering engine comprises a servo motor, a double-rotation-direction hydraulic pump, an overflow valve, a control surface, an actuator cylinder, an evaporator, a compressor, an expansion valve and a condenser. A distributed electro-hydraulic servo steering engine is combined with an evaporation circulation active cooling system, and it is guaranteed that the temperature of key elements such as a hydraulic pump and an actuator cylinder is within a reasonable working range by conducting active cooling on the key elements. Heat is brought out of the equipment through refrigerant evaporation circulation and taken away through cold source fluid, it is guaranteed that the internal temperature of the steering engine is controllable, and the external heat exchange efficiency is improved. A hydraulic pump and actuator cylinder integrated heat exchange device is provided, a refrigerant flow channel is arranged in a hydraulic element shell, and normal work of a hydraulic system is not affected while efficient heat exchange is achieved. A heat insulation layer is arranged between a hydraulic system and a cooling system condenser, heat is brought away from the hydraulic system in an active cooling mode, and heat is prevented from returning in a heat conduction mode again through the heat insulation layer.

Description

technical field [0001] The invention belongs to the field of aircraft design and relates to an active thermal control distributed electro-hydraulic servo steering gear. Background technique [0002] Traditional aircraft electro-hydraulic servo steering gear mostly uses a centralized oil source, and the engine drives the pump to provide hydraulic energy for each steering gear of the aircraft. With the development of aircraft design technology, the disadvantages of centralized hydraulic systems cannot be ignored. Long pipelines are difficult to arrange, the reliability of pipeline vibration is reduced, and at the same time, it accounts for an increasing proportion of the total weight of the aircraft hydraulic system. The distributed hydraulic system arranges motors and hydraulic pumps near each steering gear, and uses cables to transmit electric energy instead of pipelines to transmit hydraulic energy, which avoids some problems of long pipeline transmission and has better mai...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C13/50F25B41/40F25B39/00F25B41/31
CPCB64C13/504F25B39/00
Inventor 王克龙张国辉刘江陈召斌何川
Owner 沈阳飞机设计研究所扬州协同创新研究院有限公司
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