Electric backup onboard pressurization energy storage flow compensation hydraulic system and method

Abstract

The invention relates to the field of aircraft hydraulic systems, and provides an electric backup airborne pressurization energy storage flow compensation hydraulic system and method.The system comprises an energy accumulator, an electromagnetic reversing valve, a one-way pump-two-way motor, a speed change device and a direct current motor; the oil supply end of the onboard hydraulic system is communicated with an energy accumulator through an oil supply one-way valve, and a one-way pump-two-way motor is connected with an onboard actuator and a direct current motor through a speed change device; when the one-way pump-two-way motor is used as a pump, an oil outlet is communicated with the energy accumulator through the pressurizing one-way valve; when the one-way pump-two-way motor serves as a motor, the two sides of the one-way pump-two-way motor are connected with a port A and a port B of the electromagnetic reversing valve respectively, a port P of the electromagnetic reversing valve is connected with the energy accumulator, and a port T of the electromagnetic reversing valve is connected with the oil return end of the onboard hydraulic system. According to the invention, the pressure grade of an airborne hydraulic system can be locally improved, high-power instantaneous flow is provided, and the actuation time of airborne users with extremely high requirements on actuation speed, such as cabin doors, is greatly shortened.

Description

technical field [0001] The present application relates to the field of aircraft hydraulic systems, in particular to an electric backup on-board pressurized energy storage flow compensation hydraulic system and method. Background technique [0002] The retraction and retraction of the landing gear is required during the take-off and landing of the aircraft, and the reliable retraction of the landing gear is directly related to the flight safety of the aircraft. When the aircraft encounters emergency conditions such as fuel shortage or fuel leakage during flight, it is necessary to open the cargo door and discard the cargo in order to reduce the weight and ensure the flight safety of the aircraft. When the transport plane is performing the airdrop mission, it needs to open the hatch to perform the airdrop mission after arriving at the designated airdrop point. Retraction and retraction of the landing gear and actuation of the hatch need to be performed safely and reliably, an...

AI Technical Summary

Problems solved by technology

[0004] The patent [Application No.: 201510959136.X] and the patent [Application No.: 201710554447.7] proposed a motor-based pressurized energy storage hatch door actuation system, which uses a hydraulic motor to drive a hydraulic pump for pressurized energy storage. The efficiency of this method is low, and the pressurized energy storage process may still face flow disputes with other hydraulic users. In addition, the above systems cannot be used when the main hydraulic system fails

The patent [Application No.: 201710554477.8] proposes an electric pressurized energy storage hatch door actuation system, all the power of the energy storage is provided by the motor, and a motor failure will cause the hatch actuation system to be unusable

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