公开(公告)号：US08560203B2

公开(公告)日：2013-10-15

申请号：US13190549

申请日：2011-07-26

申请人： Salvatore Calandra ,  Frederic Giroux ,  Mark Iacobacci ,  Martin Chabot ,  Simon Hartropp ,  Yusuf Syed ,  Dariusz Chmiel ,  Adrienne Bajaj

发明人： Salvatore Calandra ,  Frederic Giroux ,  Mark Iacobacci ,  Martin Chabot ,  Simon Hartropp ,  Yusuf Syed ,  Dariusz Chmiel ,  Adrienne Bajaj

IPC分类号： G06F19/00 ,  G06G7/70 ,  F02C9/28 ,  F02D9/00 ,  G07C3/00

CPC分类号： B64D31/06 ,  F01D25/02 ,  F02C7/047 ,  F02C9/28 ,  F02D9/00 ,  F05B2260/80 ,  F05B2270/303 ,  F05D2270/094 ,  F05D2270/303 ,  F05D2270/80 ,  G01K1/20 ,  G01K13/02 ,  G01K13/022 ,  G01K2013/024 ,  G01K2205/02 ,  G07C3/00

摘要： Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.

公开(公告)号：US20120029786A1

公开(公告)日：2012-02-02

申请号：US13190549

申请日：2011-07-26

申请人： Salvatore Calandra ,  Frederic Giroux ,  Mark Iacobacci ,  Martin Chabot ,  Simon Hartropp ,  Yusuf Syed ,  Dariusz Chmiel ,  Adrienne Bajaj

发明人： Salvatore Calandra ,  Frederic Giroux ,  Mark Iacobacci ,  Martin Chabot ,  Simon Hartropp ,  Yusuf Syed ,  Dariusz Chmiel ,  Adrienne Bajaj

IPC分类号： F02C9/00 ,  F02C7/047

CPC分类号： B64D31/06 ,  F01D25/02 ,  F02C7/047 ,  F02C9/28 ,  F02D9/00 ,  F05B2260/80 ,  F05B2270/303 ,  F05D2270/094 ,  F05D2270/303 ,  F05D2270/80 ,  G01K1/20 ,  G01K13/02 ,  G01K13/022 ,  G01K2013/024 ,  G01K2205/02 ,  G07C3/00

摘要： Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.

摘要翻译： 描述了在温度探针结冰期间控制飞行器涡扇发动机的方法和用于执行这种方法的装置。 所述方法可以包括：使用代表从加热温度探测器接收的温度的一个或多个信号来产生用于控制发动机的一个或多个控制信号; 确定与探针相关联的结冰条件存在; 并且使用表示一个或多个替代信号的数据代替代表从加热温度探测器接收的温度的信号，以产生用于控制发动机的一个或多个控制信号。