The invention relates to the technical field of aviation energy conversion, in particular to an aircraft electro-hydraulic conversion control method and system. The control method comprises the steps that the electro-hydraulic conversion assembly is triggered based on a power generation signal of the aircraft to supply hydraulic oil to the high-pressure oil assembly, and a motor of the electro-hydraulic conversion assembly is controlled to stop rotating; based on the reduction of the rotating speed of the motor, the swash plate angle of a conversion unit of the electro-hydraulic conversion assembly is controlled to be reduced; turning on a first electromagnetic valve of a high-pressure oil assembly based on the condition that rotation of the motor stops and the swash plate angle of the conversion unit is reduced to the angle set value; on the basis that the first electromagnetic valve is opened, high-pressure hydraulic oil stored in the second hydraulic oil tank flows through the conversion unit and is supplied to the first hydraulic oil tank of the low-pressure oil assembly to drive the electro-hydraulic conversion assembly to generate electric energy. Therefore, the problem of how to realize peak shifting complementation of electric energy and hydraulic energy is solved.
本发明涉及航空能源转换技术领域,具体而言,涉及一种飞行器电液转换控制方法及系统。控制方法包括基于飞行器的发电信号触发且电液转换组件向高压油组件供给液压油,控制电液转换组件的电机停止旋转;基于电机的转速减小,控制电液转换组件的转换单元的斜盘角度减小;基于电机旋转停止且转换单元的斜盘角度减小至角度设定值,开启高压油组件的第一电磁阀;基于第一电磁阀开启,第二液压油箱存储的高压液压油流经转换单元并供给至低压油组件的第一液压油箱,驱动电液转换组件产生电能。这样就解决了如何实现电能、液压能的错峰互补的问题。
Aircraft electro-hydraulic conversion control method and system
一种飞行器电液转换控制方法及系统
29.03.2024
Patent
Elektronische Ressource
Chinesisch
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