The embodiment of the invention discloses an aircraft power system based on a dual-redundancy bus and a control method and device.The aircraft power system comprises a rack and a power assembly, the power assembly is connected to the rack, and the power assembly comprises a flight control computer, a first CAN bus and a plurality of power devices; each power device is communicated with the flight control computer through a first CAN bus, the number of the first CAN buses is equal to that of the power devices, and the power devices are in one-to-one correspondence with the first CAN buses. Each power device communicates with the flight control computer through the independent corresponding first CAN bus, so that the number of the power devices is equal to the number of the first CAN buses which are consistent with the number of the power devices and correspond to the power devices in a one-to-one mode. The mode that the first CAN bus is used for controlling communication is adopted to replace a traditional mode that two lines are needed to achieve communication and control respectively, so that the anti-interference performance is high, the transmission distance is long, and transmission is more stable.
本发明实施例公开了一种基于双余度总线的飞行器动力系统、控制方法及装置,飞行器动力系统包括机架、动力组件,所述动力组件连接在机架上,所述动力组件包括飞控计算机、第一CAN总线和若干个动力设备,每一个所述动力设备与所述飞控计算机之间通过第一CAN总线通信,第一CAN总线的数量与动力设备的数量相等,所述动力设备与所述第一CAN总线一一对应。由于每一个动力设备是通过单独的对应的第一CAN总线与飞控计算机进行通信,当有多少个动力设备,就有多少个与动力设备数量一致的第一CAN总线与动力设备一一对应,采用第一CAN总线进行控制通信的方式取代传统的需要两路线路来分别实现通信和控制,使得抗干扰性强,传输距离远,传输更加稳定。
Aircraft power system based on dual-redundancy bus, control method and device
一种基于双余度总线的飞行器动力系统、控制方法及装置
2022-12-02
Patent
Electronic Resource
Chinese
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