An aircraft-mounted electro-thermal ice prevention system (IPS) includes a sensor, a divider strip assembly, and a controller. The sensor monitors the direction of a localized incident airflow applied on the sensor. The divider strip assembly is coupled to a critical surface and includes a plurality of heating sections. The controller is in signal communication with the sensor and the divider strip assembly. The controller determines a direction of a surface airflow incident on a critical surface of the aircraft based on the local incident airflow, and controls the aircraft based on the direction of the surface airflow. Power is selectively concentrated to at least one target heating section among the plurality of heating sections with respect to a non-target heating section among the plurality of heating sections.
一种安装在飞行器上的电热防冰系统(IPS)包括传感器、分隔条带组件和控制器。所述传感器监测施加在所述传感器上的局部入射气流的方向。所述分隔条带组件联接到关键表面并且包括多个加热部段。所述控制器与所述传感器和所述分隔条带组件进行信号通信。所述控制器基于所述局部入射气流确定入射在所述飞行器的关键表面上的表面气流的方向,并且基于所述表面气流的所述方向,相对于所述多个加热部段之中的非目标加热部段选择性地将功率集中到所述多个加热部段之中的至少一个目标加热部段。
Adjustable anti-icing system partition strip
可调节防冰系统分隔条带
02.06.2023
Patent
Elektronische Ressource
Chinesisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Europäisches Patentamt | 2021
|Europäisches Patentamt | 2017
|Europäisches Patentamt | 2022
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