The invention belongs to the technical field of aviation electromechanical control, and relates to a temperature control and alarm method of a civil airplane inerting system control device. The method comprises the following steps: acquiring an external input signal, and inputting the external input signal into a control channel and a monitoring channel; a temperature control valve control signal is output through a control channel according to the control logic of the inerting system, the air-entraining temperature in the inerting system is adjusted to a normal range, meanwhile, whether the air-entraining temperature is too high or not is continuously judged according to the control logic, and once the air-entraining temperature exceeds a preset value and lasts for a preset duration, a negative end control signal of an isolating valve is output; the monitoring channel serves as a function reliability backup, and when the monitoring channel monitors that the control channel breaks down, the air entraining temperature is too high and exceeds the temperature preset value of the monitoring channel, a positive control signal of the isolation valve is output, namely the isolation valve is closed.
本发明属于航空机电控制技术领域,涉及一种民用客机惰化系统控制装置的温度控制、告警方法。该方法包括:采集外部输入信号,输入控制通道和监控通道中;通过控制通道按照惰化系统的控制逻辑输出温度控制阀控制信号,将惰化系统中引气温度调节至正常范围,同时根据控制逻辑,持续判断引气温度是否过高,一旦引气温度超过预设值且持续预设时长,输出隔离阀的负端控制信号;将监控通道作为功能可靠性备份,通过监控通道监测到在控制通道发生故障,导致引气温度过高时,超过监控通道的温度预设值时,输出隔离阀的正控信号,即关闭隔离阀。
Temperature control and alarm method for civil airplane inerting system control device
一种民用客机惰化系统控制装置的温度控制、告警方法
2024-05-10
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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