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    • 52. 发明专利
    • ANTI-ICING DEVICE
    • JPH042595A
    • 1992-01-07
    • JP9923890
    • 1990-04-17
    • MITSUBISHI HEAVY IND LTD
    • IWAZAWA YOSHIAKI
    • B64D15/04
    • PURPOSE:To uniform the temperature distribution of an anti-icing face so as to enable the positive anti-icing of the whole anti-icing face by disposing a face-shaped heat pipe across the whole inner face of the anti-icing face, and providing a means for heating the inner face of this heat pipe. CONSTITUTION:A face-shaped heat pipe 20 is placed across the whole inner face of an outside plate 1 with its outer face formed into an anti-icing face 1a. Inside this heat pipe 20, porous metal and a wire mesh wick are built in, and an operating fluid is sealed. A temperature sensor 23 is fitted at the anti- icing face 1a, and the opening of a flow control valve 25 interposed at a duct 7 is controlled by a controller 24 receiving the output of the temperature sensor 23. When the temperature of the anti-icing face 1a is lowered below the specified value, 2 deg.C, for instance, the flow control valve 25 is opened so that heated air in a heated air source 8 is led into a manifold 4 through the duct 7 and injected to the inner face of the face-shaped heat pipe 20 from a nozzle 11. The heat is thereby transmitted to the outer face of heat pipe 20 through an operating medium to heat the anti-icing face 1a.
    • 58. 发明专利
    • Anti-icing device and aircraft main wing
    • 防盗装置和飞机主机
    • JP2013163478A
    • 2013-08-22
    • JP2012028268
    • 2012-02-13
    • Mitsubishi Heavy Ind Ltd三菱重工業株式会社
    • ICHIKAWA KURODOKAMIFUJI YOICHIAOKI YASUTAKAKOBAYASHI NAOKIITO AKIRAMIWA JUNICHI
    • B64D15/04
    • PROBLEM TO BE SOLVED: To provide an anti-icing device for a front edge part in an aircraft, configured to reliably and efficiently prevent icing at the front edge of the aircraft with a simple structure.SOLUTION: An anti-icing device 40 includes: an extraction air nozzle 41 where extraction air to be supplied to a main-wing front edge part 22 flows; and a collision bar 45 that is provided on a flow passage of the extraction air and with which the extraction air collides. The extraction air nozzle 41 has a plurality of blow holes 41a blowing the extraction air toward a tip part 22a of the main wing front edge part 22. The collision bar 45 is provided to face the blow holes 41a. The extraction air blown from the blow holes 41a toward an inner wall surface 31 near the tip part 22a collides with the collision bar 45, and flows backward along the inner wall surface 31. The main-wing front edge part 22 is entirely heated uniformly, thereby efficiently preventing icing on the outside of the main-wing front edge part 22.
    • 要解决的问题:提供一种用于航空器中的前缘部分的防冰装置,其构造成以简单的结构可靠且有效地防止飞机前缘处的结冰。解决方案:防冰装置40包括: 提供给主翼前缘部22的抽吸空气的抽气用喷嘴41; 以及设置在抽取空气的流路上并与提取空气碰撞的碰撞条45。 抽吸用空气喷嘴41具有朝向主翼前缘部22的前端部22a吹出抽取空气的多个吹出孔41a。碰撞杆45设置成与吹气孔41a相对。 从吹出孔41a向前端部22a附近的内壁面31吹出的抽出气体与碰撞杆45碰撞,沿着内壁面31向后方流动。主翼前缘部22被均匀地加热, 从而有效地防止在主翼前缘部22的外侧结冰。