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    • 1. 发明公开
    • Aircraft flap system with aileron functionality
    • Flugzeugklappensystem mitQuerruderfunktionalität
    • EP2808250A1
    • 2014-12-03
    • EP13169534.8
    • 2013-05-28
    • Airbus Operations GmbH
    • Burchard, Alexander
    • B64C9/16
    • B64C9/18B64C9/04B64C9/16B64C13/38B64C2009/005Y02T50/32Y10T74/18216
    • The present invention pertains to an actuation mechanism for a flap with aileron functionality, including a crank (4) having a crank axle (4a), a crank arm (6) and a crank pivot (7); a displacement shaft (3) articulated to the crank pivot (7) at an actuating end portion; and a rotatable linear-motion bearing (2) in which the displacement shaft is slidably supported, wherein the displacement shaft is fixedly connectable to a flap body (1) of the aircraft flap at a flap end portion of the displacement shaft (3) opposite to the actuating end portion, and wherein the linear-motion bearing (2) is rotatably attachable at a pivot point to an aircraft wing (10) comprising the aircraft flap, so that the displacement shaft is able to rotate around an axis running spanwise of the aircraft wing around the pivot point. The present invention further pertains to an aircraft flap with such an actuation mechanism and an aircraft having an aircraft flap.
    • 本发明涉及具有副翼功能的翼片的致动机构,包括具有曲柄轴(4a),曲柄臂(6)和曲柄轴(7)的曲柄(4)。 在致动端部处铰接到曲柄枢轴(7)的位移轴(3); 和可旋转的直线运动轴承(2),其中位移轴可滑动地支撑在其中,其中位移轴可固定地连接到飞行器翼片的翼片主体(1),位于相对的位移轴(3)的翼片端部 并且其中所述直线运动轴承(2)在枢转点处可转动地附接到包括所述飞行器翼片的飞行器机翼(10),使得所述位移轴能够围绕运行的轴线 飞机机翼围绕枢轴点。 本发明还涉及具有这种致动机构的飞机翼片和具有飞行器翼片的飞行器。
    • 5. 发明公开
    • STIRLING ENGINE
    • STIRLINGMOTOR
    • EP2518298A1
    • 2012-10-31
    • EP10838496.7
    • 2010-05-21
    • Yang, Yongshun
    • Yang, Yongshun
    • F02G1/04F02G1/00
    • F02D41/005F01B1/10F01B7/16F01B9/02F02B75/32F02B2075/1816F02B2275/38F02G1/043F02G1/044F02G2243/38F02G2244/50F02G2244/52Y02T10/47Y10T74/18216
    • A heat engine includes four groups of cylinder assemblies and a transmission output mechanism. The transmission output mechanism includes a rocker-arm shaft support (100), a crankshaft support (200), a first rocker-arm assembly (4), a second rocker-arm assembly (5), and a crankshaft (300) rotatablely installed on the crankshaft support (200). A crankshaft long-arm connecting rod (301) and a crankshaft short-arm connecting rod (302) are hinged on the crankshaft (300). The first rocker-arm assembly (4) includes a first straight shaft (41), a first long arm (42) and a second long arm (43), and a first hinged part (431) is arranged on the second long arm (43) to hinge with the crankshaft long-arm connecting rod (301). The second rocket-arm assembly (5) includes a second straight shaft (41), a third long arm (52) and a fourth long arm (53) and a short arm (54). A second hinged part (53) is arranged on the short arm (54) to hinge with the crankshaft short-arm connecting rod (302). The crankshaft long-arm connecting rod (301) is parallel with the short arm (54) and the crankshaft short-arm connecting rod (302) is parallel with the second long arm (43). The heat engine is simple in structure, has low manufacturing cost and makes less noise.
    • 热机包括四组气缸组件和变速器输出机构。 变速器输出机构包括摇臂轴支撑件(100),曲轴支架(200),第一摇臂组件(4),第二摇臂组件(5)和曲轴(300),可旋转地安装 在曲轴支撑件(200)上。 曲轴长臂连杆(301)和曲轴短臂连杆(302)铰接在曲轴(300)上。 第一摇臂组件(4)包括第一直轴(41),第一长臂(42)和第二长臂(43),第一铰接部分(431)布置在第二长臂 43)与曲轴长臂连杆(301)铰接。 第二火箭臂组件(5)包括第二直轴(41),第三长臂(52)和第四长臂(53)以及短臂(54)。 第二铰链部分(53)布置在短臂(54)上以与曲轴短臂连杆(302)铰接。 曲轴长臂连杆(301)与短臂(54)平行,曲轴短臂连杆(302)与第二长臂(43)平行。 热机结构简单,制造成本低,噪音小。