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Undercarriage rising and landing control hydraulic device for helicopter

A hydraulic device and landing gear technology, which is applied in fluid pressure actuation devices, mechanical equipment, fluid pressure actuation system components, etc., can solve the problems of high transmission medium requirements, affecting the life of hydraulic pumps, system temperature rise, etc., to achieve convenient Integrated design, easy failure and simple maintenance

Inactive Publication Date: 2016-07-20
HARBIN
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] In the existing hydraulic device for retracting and retracting the landing gear of a helicopter, a valve-controlled throttling and speed-adjusting servo hydraulic system is generally used, and the flow and pressure of the system are controlled by the throttle valve or by controlling the opening of the electro-hydraulic servo valve to realize the retraction and retraction of the landing gear. Put, this type of system has high requirements on the transmission medium, heavy structure, complex structure, and unavoidable throttling loss and overflow loss caused by system temperature rise, difficult heat dissipation, and low efficiency
In addition, in some systems, when the landing gear is not retracted, the hydraulic pump is idling, and the electro-hydraulic servo valve is unloaded in the neutral position, and the hydraulic pump works for a long time, which affects the life of the hydraulic pump.

Method used

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  • Undercarriage rising and landing control hydraulic device for helicopter

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Embodiment Construction

[0032] A hydraulic device for retracting and retracting the landing gear of a helicopter is provided. The device includes a frequency conversion motor 1, a bidirectional quantitative hydraulic pump 2, a first hydraulic control check valve 3, a first overflow valve 4, a second hydraulic control check valve 5, and a second hydraulic control check valve. Three hydraulic control check valves 6, second overflow valve 7, fourth hydraulic control check valve 8, fuel tank 9, landing gear retractable cylinder 10;

[0033] Among them, the two-way quantitative hydraulic pump 2 has oil port A and oil port B, and the drive shaft of the two-way quantitative hydraulic pump 2 is connected to the output shaft of the frequency conversion motor. Oil enters oil from port A and oil exits oil port A. When the frequency conversion motor reverses, the working state of the two-way quantitative hydraulic pump 2 is that oil enters oil port A and oil exits oil port B;

[0034] The four hydraulic control ...

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Abstract

The invention relates to an undercarriage rising and landing control hydraulic device for a helicopter. According to the hydraulic device, a variable-frequency motor is adopted to control a quantitative hydraulic pump, and the rotating speed of the motor is changed to control the flow of a system, and therefore rising and landing of an undercarriage are achieved. By means of the undercarriage rising and landing system of the structural form, the structure is simple, the installation position is not limited, the requirement for the precision of oil liquid is low, a valve-control throttling speed-adjusting servo hydraulic system is abandoned, the problems that the temperature of the system is increased and the efficiency is low due to throttling losses and overflow losses are avoided, and meanwhile electro-hydraulic servo valves very high in manufacturing cost and electromagnetic reversing valves large in pressure impact are abandoned.

Description

technical field [0001] The invention belongs to the field of helicopter hydraulic control. Background technique [0002] In the existing hydraulic device for retracting and retracting the landing gear of a helicopter, a valve-controlled throttling and speed-adjusting servo hydraulic system is generally used, and the flow and pressure of the system are controlled by the throttle valve or by controlling the opening of the electro-hydraulic servo valve to realize the retraction and retraction of the landing gear. Put, this type of system has high requirements on the transmission medium, the structure is heavy, the structure is complex, and the system temperature rise, difficult heat dissipation and low efficiency caused by throttling loss and overflow loss cannot be avoided. In addition, in some systems, when the landing gear is not retracted, the hydraulic pump is idling, and the hydraulic pump is unloaded through the neutral position of the electro-hydraulic servo valve, and ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F15B11/16F15B13/06F15B21/08B64C25/22
CPCF15B11/167B64C25/22F15B13/06F15B21/08F15B2211/20515F15B2211/2053F15B2211/365F15B2211/71F15B2211/78
Inventor 谷峰
Owner HARBIN
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