COOLING DEVICE AND AERIAL VEHICLE THEREWITH

According to an embodiment of the present invention, a cooling device using fuel for driving an engine of an aircraft as a coolant comprises: a feed pump connected to a fuel tank and flowing fuel; a transfer pipe through which the fuel discharged by the supply pump flows; a valve connected to the tr...

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Bibliographische Detailangaben
Hauptverfasser:	BYEON YONG WOO, HWANG YOO JUN, KIM YOUNG SHIN, LEE JU YOUNG
Format:	Patent
Sprache:	eng ; kor
Schlagworte:	ACTUATING-FLOATS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COCKS COMBUSTION ENGINES COSMONAUTICS DEVICES FOR VENTING OR AERATING ENGINEERING ELEMENTS AND UNITS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS SUPPLYING COMBUSTION ENGINES IN GENERAL, WITH COMBUSTIBLEMIXTURES OR CONSTITUENTS THEREOF TAPS THERMAL INSULATION IN GENERAL TRANSPORTING VALVES WEAPONS
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Beschreibung
Zusammenfassung:	According to an embodiment of the present invention, a cooling device using fuel for driving an engine of an aircraft as a coolant comprises: a feed pump connected to a fuel tank and flowing fuel; a transfer pipe through which the fuel discharged by the supply pump flows; a valve connected to the transfer pipe and capable of controlling an opening degree; and a cooling channel for guiding the fuel between a discharge end of the valve and the fuel tank. By changing the internal pressure in response to the change in the pressure of the external air of the aircraft, the cooling channel may cool the fuel by reducing the internal pressure when the aircraft flies at a high altitude. 일 실시 예에 따르면, 비행체의 엔진을 구동하기 위한 연료를 냉각제로 하는 냉각 장치는, 연료 탱크에 연결되고, 연료를 유동시키는 공급 펌프; 상기 공급 펌프에 의하여 토출된 상기 연료가 흐르는 이송관; 상기 이송관에 연결되고, 개도량을 조절 가능한 밸브; 및 상기 밸브의 토출단 및 상기 연료 탱크 사이에서 연료를 안내하는 냉각 채널을 포함하고, 상기 냉각 채널은, 상기 비행체의 외기의 압력의 변화에 대응하여 내부의 압력이 변화됨으로써, 상기 비행체가 높은 고도로 비행할 경우, 내부의 압력이 감소되어 연료를 냉각시킬 수 있다.