The invention relates to a temperature control system in an aircraft cabin. The temperature control system comprises an engine air entraining opening (15), an electric control pressure regulating valve (6), a vortex tube (7), an electromagnetic valve (16), a flow divider (17), a temperature sensor (19) and a temperature control unit. According to the temperature control system in the aircraft cabin, heating and refrigerating components do not need to be additionally arranged, the vortex temperature separation effect of the vortex tube is utilized, separated cold airflow and hot airflow can be generated at the same time only by leading high-pressure air entraining after one engine air compressor is led, extra energy is not consumed independently in the working process, and the system is high in working efficiency and low in cost. The temperature of each specific area in flight can be automatically controlled through temperature feedback, and the whole system is simple in structure, low in cost, efficient in performance, free of maintenance and good in safety.
本发明涉及一种飞行器舱内温控系统,包括发动机引气口(15)、电控调压阀(6)、涡流管(7)、电磁阀(16)、分流器(17)、温度传感器(19)和温控单元。本发明的飞行器舱内温控系统,无需额外增加发热以及制冷部件,利用涡流管的涡旋温度分离效应,仅需引一处发动机压气机后高压引气即可同时产生分离的冷、热两股气流,工作过程中不单独消耗额外的能量,系统工作效率高,通过温度反馈可实现飞行内各个特定区域温度的自动控制,整套系统结构简单,成本低廉,性能高效,无需维护且安全性较好。
Temperature control system in aircraft cabin
一种飞行器舱内温控系统
2024-03-12
Patent
Electronic Resource
Chinese
JET AIRCRAFT CABIN TEMPERATURE CONTROL
SAE Technical Papers | 1948
|Jet aircraft cabin temperature control
Engineering Index Backfile | 1948
|Aircraft cabin temperature control systems
Engineering Index Backfile | 1953
|Cabin Temperature Control Model for Commercial Aircraft
British Library Conference Proceedings | 2012
|Cabin Temperature Control Model for Commercial Aircraft
AIAA | 2012
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