Acoustic coating for an aircraft incorporating a frost treatment system by joule effect
    61.
    发明授权
    Acoustic coating for an aircraft incorporating a frost treatment system by joule effect 有权
    用于通过焦耳效应结合霜冻处理系统的飞机的声学涂层

    公开(公告)号:US08181900B2

    公开(公告)日:2012-05-22

    申请号:US12515035

    申请日:2007-11-13

    IPC分类号: B64C1/40 B64C23/40 B64D15/00

    摘要: The invention relates to acoustic lining for an aircraft, which can cover a leading edge, such as an air inlet in the nacelle of a propulsion unit, said lining comprising: (i) from the inside outwards, a reflective layer (28), at least one cellular structure (30) and an acoustically resistive structure (32) having a pre-determined proportion of open surface; and (ii) at least one frost treatment system in the form of at least one heating layer (46) comprising open zones through which acoustic waves can pass, which co-operate at least partially with the open zones in the acoustically resistive structure. The invention is characterized in that the acoustically resistive structure (32) includes at least one structural layer (36) with openings (38) and in that said at least one heating layer (46) is disposed under the structural layer (36).

    摘要翻译: 本发明涉及一种用于飞机的声衬,其可以覆盖前缘,例如推进单元的机舱中的空气入口,所述衬里包括:(i)从内向外的反射层(28),在 至少一个蜂窝结构(30)和具有预定比例的开放表面的声阻结构(32); 以及(ii)至少一个形式为至少一个加热层(46)形式的霜冻处理系统,所述加热层包括声波可穿过的开放区域,所述开口区域至少部分地与声阻结构中的开放区域协作。 本发明的特征在于,声阻结构(32)包括具有开口(38)的至少一个结构层(36),并且所述至少一个加热层(46)设置在结构层(36)下方。

    ROTOR BASED AIR GAP HEATING FOR AIR DRIVEN TURBINE
    63.
    发明申请
    ROTOR BASED AIR GAP HEATING FOR AIR DRIVEN TURBINE 有权
    基于转子的空气加热风力发电机

    公开(公告)号:US20120056601A1

    公开(公告)日:2012-03-08

    申请号:US12875475

    申请日:2010-09-03

    申请人: Todd A. Spierling

    发明人: Todd A. Spierling

    IPC分类号: H02P9/08

    摘要: A generator apparatus comprises a deicing circuit. The deicing circuit is operable during a time when a main generator rotor is not being rotated by a generator shaft. The deicing circuit includes a first power source for energizing a plurality of exciter field windings with alternating input current to induce an exciter output current in a plurality of exciter armature windings. The exciter output current is provided to main generator rotor windings for producing resistance heating around an air gap separating the main generator rotor from a main generator stator.

    摘要翻译: 发电机装置包括除冰电路。 除冰电路在主发电机转子不被发电机轴旋转的时间内是可操作的。 除冰电路包括用于通过交流输入电流激励多个励磁场励磁绕组以在多个励磁机电枢绕组中感应励磁机输出电流的第一电源。 励磁机输出电流提供给主发电机转子绕组,用于在主发电机转子与主发电机定子分开的气隙周围产生电阻加热。

    Aircraft Heating System
    64.
    发明申请
    Aircraft Heating System 审中-公开
    飞机加热系统

    公开(公告)号:US20110290786A1

    公开(公告)日:2011-12-01

    申请号:US13115081

    申请日:2011-05-24

    申请人: Jin Hu James M. Roman

    发明人: Jin Hu James M. Roman

    IPC分类号: H05B3/48

    摘要: An aircraft heating system wherein the heater includes a haven (34) constructed from dielectric layers (40-50), conductive lanes (60), bus bars (70), and strips (80-150). Façade sections (41, 51, 61) of the dielectric layers (40-50) and the lanes (60) form the primary heating surface (31). The strips (80-150), along with sections (42, 52, 62) of the layers/lanes, form havens (34) for harbor sections (72) of the bus bars (70).

    摘要翻译: 一种飞机加热系统,其中加热器包括由电介质层(40-50),导电通道(60),汇流条(70)和条带(80-150)构成的避风港(34)。 电介质层(40-50)和通道(60)的外墙部分(41,41,61)形成主加热表面(31)。 条带(80-150)以及层/车道的部分(42,52,62)形成用于汇流条(70)的港口部分(72)的避风港(34)。

    ELECTRIC DE-ICING DEVICE AND RELATED MONITORING SYSTEM
    65.
    发明申请
    ELECTRIC DE-ICING DEVICE AND RELATED MONITORING SYSTEM 有权
    电动保护装置及相关监控系统

    公开(公告)号:US20110277443A1

    公开(公告)日:2011-11-17

    申请号:US13145601

    申请日:2010-01-20

    IPC分类号: F02G3/00 G06F19/00

    摘要: The invention relates to a de-icing device for an element of a nacelle of a turbojet engine, including at least one heating resistant mat connected to at least one electrical power source (3) and thus defining an assembly (1) of resistant mats, characterised in that the assembly of resistant mats includes one or more subassemblies of resistant mats, each subassembly in turn including one or more resistant mats of the assembly, and each subassembly of resistive mats having a different ohmic value.

    摘要翻译: 本发明涉及一种用于涡轮喷气发动机的机舱的元件的除冰装置,包括至少一个与至少一个电源(3)连接的耐热垫,从而限定了抵抗垫的组件(1) 其特征在于,抵抗垫的组件包括一个或多个抵抗垫的子组件,每个子组件依次包括组件的一个或多个阻力垫,以及具有不同欧姆值的电阻垫的每个子组件。

    Electrical power supply circuit in an aircraft for electrical equipment including a de-icing circuit
    67.
    发明授权
    Electrical power supply circuit in an aircraft for electrical equipment including a de-icing circuit 有权
    用于包括除冰电路的电气设备的飞机中的电源电路

    公开(公告)号:US07936082B2

    公开(公告)日:2011-05-03

    申请号:US12022492

    申请日:2008-01-30

    IPC分类号: B60L1/00

    摘要: An electrical power supply circuit in an aircraft is disclosed. The circuit includes an electricity distribution network on board the aircraft for powering electrical equipment situated in an engine of the aircraft or in the surroundings of the engine, and a power supply generator integrated in the engine of the aircraft for powering a de-icing circuit. The electrical equipment includes nacelle loads connected to a DC voltage distribution bus which is connected to a voltage converter circuit powered by the distribution network. The de-icing circuit includes at least one electrical resistance for dissipating electricity returned to the DC voltage distribution bus by at least some of the nacelle loads.

    摘要翻译: 公开了一种飞机中的电源电路。 该电路包括飞机上的配电网络,用于对位于发动机的发动机或发动机周围的电气设备供电,以及集成在飞行器的发动机中用于为除冰电路供电的电力供应发电机。 电气设备包括连接到直流电压分配总线的机舱负载,其连接到由分配网络供电的电压转换器电路。 除冰电路包括至少一个电阻,用于通过至少一些机舱负载来耗散返回到DC电压分配总线的电力。

    Power distribution architecture for an ice protection system
    68.
    发明授权
    Power distribution architecture for an ice protection system 有权
    防冰系统的配电架构

    公开(公告)号:US07922121B2

    公开(公告)日:2011-04-12

    申请号:US11974697

    申请日:2007-10-15

    IPC分类号: B64D15/00 B64D15/12

    摘要: An ice protection system for a vehicle is disclosed which includes a plurality of de-ice power distribution units positioned proximate to a leading edge surface of the vehicle that is susceptible to ice accretion, at least two anti-ice power distribution units located within the vehicle, spaced from the de-ice power distribution units, and a point of power regulation located within the vehicle, spaced from the power distribution units, from which power is fed to the power distribution units through independent feeder wire bundles so as to distribute line current across the system in a manner that optimizes wire weight.

    摘要翻译: 公开了一种用于车辆的防冰系统,其包括位于车辆前缘表面附近易于积冰的多个除冰配电单元,位于车辆内的至少两个防冰配电单元 与除冰配电单元间隔开的功率调节点和位于车辆内的功率调节点与配电单元间隔开,电力通过独立的馈电线束供电到配电单元,以便分配线路电流 跨系统以优化线重量的方式。

    ELECTRICAL POWER TRANSFER ASSMEBLY
    69.
    发明申请
    ELECTRICAL POWER TRANSFER ASSMEBLY 有权
    电力传输组件

    公开(公告)号:US20110024566A1

    公开(公告)日:2011-02-03

    申请号:US12827120

    申请日:2010-06-30

    IPC分类号: B64C13/00 H02G11/02

    摘要: An assembly for an aircraft including a first structure mounted to a second structure, and a power transfer assembly electrically connecting the first and second structures. The first structure is movable relative to the second structure between a retracted and an extended position. The power transfer assembly includes a housing, a spool mounted for rotation relative to the housing and biased to rotate in a first direction, and an electrical cable adapted to be wound around the spool when the spool rotates, such that movement of the first structure from its retracted to its extended position causes the cable to be unwound from the spool by rotation of the spool in a second direction opposite the first. Also, a method of electrically connecting the first and second structures. The invention may be applied to an aircraft wing to electrically connect a leading edge slat to a fixed aerofoil portion.

    摘要翻译: 一种用于飞机的组件,包括安装到第二结构的第一结构,以及电连接第一和第二结构的动力传递组件。 第一结构可相对于第二结构在缩回位置和伸出位置之间移动。 动力传递组件包括壳体,安装成相对于壳体旋转并被偏压以沿第一方向旋转的线轴,以及当线轴旋转时适于围绕线轴缠绕的电缆,使得第一结构从 其缩回到其延伸位置通过在与第一方向相反的第二方向上旋转卷轴来使线缆从卷轴展开。 另外,电连接第一和第二结构的方法。 本发明可以应用于飞行器机翼,以将前缘板条电连接到固定机翼部分。

    Aircraft wing slat
    70.
    发明授权
    Aircraft wing slat 有权
    飞机翼板

    公开(公告)号:US07878460B2

    公开(公告)日:2011-02-01

    申请号:US11507373

    申请日:2006-08-21

    IPC分类号: B64C3/50 B64D15/12

    摘要: An aircraft wing slat for mounting to a leading portion of an aircraft wing includes a main body section and a forward section, wherein the forward section is demountable from or releasably secured to the main body section. The forward section may have a nose skin with an electrically powered heater. The electrically powered heater may be integral with the nose skin and may be microporous such that it is integrated into surrounding dielectric to contribute to the mechanical strength of the nose skin. A demountable forward section of an aircraft wing slat, a main body section of an aircraft wing slat arranged to receive a demountable forward section, an aircraft wing and an aircraft wing slat with a nose skin with an electrically powered heater are also disclosed.

    摘要翻译: 用于安装到飞行器机翼的前部的飞机翼板包括主体部分和前部,其中前部可拆卸地或可拆卸地固定到主体部分。 前部可以具有电动加热器的鼻部皮肤。 电动加热器可以与鼻子皮肤成一体,并且可以是微孔的,使得其被集成到周围的电介质中以有助于鼻部皮肤的机械强度。 还公开了飞机机翼板的可拆卸的前部,布置成接收可拆卸前部的飞机机翼板的主体部分,具有电动加热器的飞机机翼和具有鼻部皮肤的飞机翼板条。