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公开(公告)号：WO2007034240A3
公开(公告)日：2007-11-29
申请号：PCT/GB2006050295
申请日：2006-09-19
Applicant: BAE SYSTEMS PLC , WARSOP CLYDE , PRESS ANDREW JULIAN , HUCKER MARTYN JOHN
Inventor： WARSOP CLYDE , PRESS ANDREW JULIAN , HUCKER MARTYN JOHN
CPC classification number: G01F1/6845 , G01P5/12 , G01P13/025
Abstract: A sensor device for sensing air flow speed at the exterior of an aircraft, comprising a substrate having an upper side on which is mounted a diaphragm over an aperture or recess in the substrate, the diaphragm being thermally and electrically insulative, and mounting on its upper surface a heating element comprising a layer of resistive material, and wherein electrical connections to the heating element are buried in the diaphragm and/or the substrate, and provide electrical terminals at the lower side of the substrate. The heating element is exposed to the environment, but the remaining electrical parts of the device are not exposed. Portions of a conductive substrate may be cut or etched away to define a conductive pillar. Signals may be transmitted through the conductive pillar from one surface carrying the sensor element to the other surface carrying contact pads.
Abstract translation: 一种用于感测飞行器外部的空气流速的传感器装置，包括：具有上侧的基板，在基板上的孔或凹部上方安装有隔膜，所述隔膜具有热和电绝缘性，并且安装在其上部 表面包括电阻材料层的加热元件，并且其中与所述加热元件的电连接被掩埋在所述隔膜和/或所述基板中，并在所述基板的下侧提供电端子。 加热元件暴露在环境中，但是该设备的其余电气部件不暴露。 可以切割或蚀刻导电基底的一部分以限定导电柱。 信号可以通过导电柱从承载传感器元件的一个表面传输到另一个承载接触垫的表面。
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公开(公告)号：AU2008331255A1
公开(公告)日：2009-06-04
申请号：AU2008331255
申请日：2008-11-28
Applicant: BAE SYSTEMS PLC
Inventor： PRESS ANDREW JULIAN
Abstract: A temperature monitoring arrangement for an electro-thermal ice protection system is provided for a slat of an aircraft wing, incorporating heater mats of composite material, wherein, in order to avoid or at least substantially reduce some of the problems associated with use of discrete temperature sensing elements, one or more optical fiber temperature sensors are embedded within the heater mats for sensing an overheating condition of each mat. Advantageously, a control system is used to monitor the temperature of the mats, and adjusts power supplied, or switches off power, in response to detection of an overheating condition.
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公开(公告)号：GB2498185A
公开(公告)日：2013-07-10
申请号：GB201200022
申请日：2012-01-03
Applicant: BAE SYSTEMS PLC
Inventor： WARSOP CLYDE , PRESS ANDREW JULIAN , DAVIES ALAN GERAINT
Abstract: A grenade launched aerial surveillance vehicle 3 which comprisescomprises an integral propellant charge, the vehicle 3, in use, being launched from a grenade launcher weapon. The vehicle 3 also comprises a deployable wing (such as a parawing 2). A guidance system comprises altitude lock to provide a substantially circular flight path around a target, there being means of providing directional nudge to the flight path. The vehicle 3 further includes an electrical power source and at least one optical sensor mounted on the vehicle 3, a communication device relaying guidance and data output from the at least one optical sensor to a user. A propulsion device, such as a propeller 6 provides aerial movement of the vehicle 3.
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公开(公告)号：AU2008331255B2
公开(公告)日：2012-06-14
申请号：AU2008331255
申请日：2008-11-28
Applicant: BAE SYSTEMS PLC
Inventor： PRESS ANDREW JULIAN
Abstract: A temperature monitoring arrangement for an electro-thermal ice protection system is provided for a slat (2) of an aircraft wing, incorporating heater mats 12, 12, 12, 12 of composite material, wherein, in order to avoid or at least substantially reduce some of the problems associated with use of discrete temperature sensing elements, one or more optical fibre temperature sensors are embedded within the heater mats for sensing an overheating condition of each mat. Advantageously, a control system is used to monitor the temperature of the mats, and adjusts power supplied, or switches off power, in response to detection of an overheating condition.
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