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    • 6. 发明申请
    • LOAD INTRODUCTION STRUCTURE, IN PARTICULAR A LINING FRAME, FOR AN AIRCRAFT
    • 负载引言结构,特别是一个内置的框架,用于飞机
    • US20100038486A1
    • 2010-02-18
    • US12512477
    • 2009-07-30
    • Hermann BenthienMichael Kruse
    • Hermann BenthienMichael Kruse
    • B64C1/00B64C1/06
    • B64C1/061B64C1/066
    • The invention relates to a load introduction structure for an aircraft, comprising two lateral frames which are arranged opposite one another in the two lateral regions of a fuselage airframe structure of the aircraft and adjoin a continuous floor surface which rests on a floor frame. The two lateral frames are connected via the top thereof by a ceiling frame, the ceiling frame being suspended from a ceiling region of the fuselage airframe structure. Each lateral frame is divided into at least two lateral frame segments. At least three track portions which extend parallel to a longitudinal axis of the aircraft are arranged on each lateral frame segment. The lateral frames are connected to the fuselage airframe structure, the ring frames in particular, by a plurality of x-rods, y-rods and y-cardan rods. The load introduction structure is largely uncoupled according to the invention from the fuselage airframe structure of the aircraft inter alia by a plurality of coupling members arranged between the track portions to form gaps in order to compensate for load-induced and/or thermally-induced deformations, in particular changes in length, of the fuselage airframe structure.
    • 本发明涉及一种用于飞行器的载荷引入结构,包括两个横向框架,它们在机身的机身机身结构的两个横向区域中彼此相对布置并且邻接在搁置在地板框架上的连续地板表面上。 两个横向框架通过其顶部通过天花板框架连接,天花板框架从机身机身结构的天花板区域悬挂。 每个横向框架被分成至少两个横向框架段。 至少三个平行于飞行器的纵向轴线延伸的轨道部分布置在每个横向框架段上。 横向框架通过多个x杆,Y杆和y-万向棒连接到机身机身结构,特别是环形框架。 根据本发明,负载引入结构根据本发明从飞机的机身机身结构中大体上脱离,尤其是通过布置在轨道部分之间的多个联接构件形成间隙,以便补偿负载引起的和/或热诱导的变形 ,特别是长度的变化,机身机身结构。
    • 10. 发明授权
    • Load introduction structure, in particular a lining frame, for an aircraft
    • 负载引导结构,特别是用于飞行器的衬里框架
    • US08376276B2
    • 2013-02-19
    • US12512477
    • 2009-07-30
    • Hermann BenthienMichael Kruse
    • Hermann BenthienMichael Kruse
    • B64C1/00
    • B64C1/061B64C1/066
    • The invention relates to a load introduction structure for an aircraft, comprising two lateral frames which are arranged opposite one another in the two lateral regions of a fuselage airframe structure of the aircraft and adjoin a continuous floor surface which rests on a floor frame. The two lateral frames are connected via the top thereof by a ceiling frame, the ceiling frame being suspended from a ceiling region of the fuselage airframe structure. Each lateral frame is divided into at least two lateral frame segments. At least three track portions which extend parallel to a longitudinal axis of the aircraft are arranged on each lateral frame segment. The lateral frames are connected to the fuselage airframe structure, the ring frames in particular, by a plurality of x-rods, y-rods and y-cardan rods. The load introduction structure is largely uncoupled according to the invention from the fuselage airframe structure of the aircraft inter alia by a plurality of coupling members arranged between the track portions to form gaps in order to compensate for load-induced and/or thermally-induced deformations, in particular changes in length, of the fuselage airframe structure.
    • 本发明涉及一种用于飞行器的载荷引入结构,包括两个横向框架,它们在机身的机身机身结构的两个横向区域中彼此相对布置并且邻接在搁置在地板框架上的连续地板表面上。 两个横向框架通过其顶部通过天花板框架连接,天花板框架从机身机身结构的天花板区域悬挂。 每个横向框架被分成至少两个横向框架段。 至少三个平行于飞行器的纵向轴线延伸的轨道部分布置在每个横向框架段上。 横向框架通过多个x杆,y杆和y-万向棒连接到机身机身结构,特别是环形框架。 根据本发明,负载引入结构根据本发明从飞机的机身机身结构中大体上脱离,尤其是通过布置在轨道部分之间的多个联接构件形成间隙,以便补偿负载引起的和/或热诱导的变形 ,特别是长度的变化,机身机身结构。