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51. 发明授权

US06367738B1 Aerobatic aircraft 有权
标题翻译：特技飞机
公开(公告)号：US06367738B1
公开(公告)日：2002-04-09
申请号：US09494710
申请日：2000-01-31
申请人： John Wadleigh
发明人： John Wadleigh
IPC分类号： B64C3902
CPC分类号： B64D33/00 , B64C39/04 , B64D27/08 , B64D27/10 , F01M11/067
摘要： An improved aerobatic aircraft design having a first engine located in the nose portion of the fuselage and a second engine located in the tail portion of the fuselage. The thrust components of both the first and second engines are coaxial along the long axis of the fuselage. Both engines can individually provide sufficient power for the aircraft to takeoff, maintain altitude, and/or land.
摘要翻译：一种改进的特技飞行器设计，其具有位于机身的鼻部中的第一引擎和位于机身尾部的第二引擎。第一和第二发动机的推力部件沿着机身的长轴是同轴的。这两种发动机可以单独提供足够的动力使飞机起飞，保持高度和/或降落。

52. 发明授权

US4437627A Integrated power plant installation system 失效
标题翻译：综合电站安装系统
公开(公告)号：US4437627A
公开(公告)日：1984-03-20
申请号：US357746
申请日：1982-03-12
申请人： James R. Moorehead
发明人： James R. Moorehead
IPC分类号： B64D27/18 , B64D33/00
CPC分类号： B64D27/18 , B64D33/00 , B64D2027/264
摘要： An integrated power plant installation system for underwing high-bypass mid-length fan air duct core-mounted engines readily permits disconnection of the entire powerplant at the wing thereby virtually eliminating the necessity of disconnecting the engine and complex systems per se from the support strut when engine replacement or removal proves necessary. Excessive congestion within the vicinity of the strut box structure is eliminated by disposing the engine accessories, and auxiliary equipment and system lines, within the lower quadrant of the powerplant assembly in both a laterally and longitudinally distributed array. Potential catastrophic fire hazards within the nacelle are substantially eliminated by routing the fluid lines and electrical conduits axially aft and upwardly around the circumference of the engine within the nozzle section of the powerplant aft of all rotating discs. These latter features permit the utilization of a simplified strut box structure in that the same need not be provided with equipment clearance structure, conduit throughbores, and complex fire seals and drains. The strut structure is easily tunable with simple plate structure for flutter stiffness control, involving strut and wing bending in gusts. The wing attach/detach engine mounting system, particularly for a core-mounted engine by means of the simplified strut box structure, also facilitates the elimination of the conventional fan D, or split, duct system and enables the employment of a continuous hoop structure thrust reverser system.
摘要翻译：用于底部高旁路中长风扇风道核心安装发动机的集成发电厂安装系统易于允许机翼上的整个动力装置断开，从而实际上消除了将发动机和复杂系统本身与支撑支柱断开的必要性，发动机更换或拆卸证明是必要的。通过将发动机附件和辅助设备和系统线路布置在动力装置组件的下部象限的横向和纵向分布的阵列中，可以消除支柱结构附近的过度拥塞。通过在所有旋转盘的动力装置后部的喷嘴部分内沿着发动机的圆周方向将流体管线和电气导管轴向向后轴向布置，从而基本上消除了机舱内潜在的灾难性火灾危险。这些后面的特征允许利用简化的支柱结构，因为不需要设备间隙结构，导管通孔和复杂的防火密封和排水沟。支柱结构易于调整，具有简单的板结构，用于颤振刚度控制，涉及阵风和翼阵弯曲。机翼安装/拆卸发动机安装系统，特别是通过简化支柱结构的内置发动机，也有助于消除传统的风扇D或分流管道系统，并且能够使用连续的环形结构推力反向系统。

53. 发明授权

US4377933A Reservoir with an antivibration suspension 失效
标题翻译：水库与防震悬挂
公开(公告)号：US4377933A
公开(公告)日：1983-03-29
申请号：US275699
申请日：1981-06-22
申请人： Yves J. Lojou
发明人： Yves J. Lojou
IPC分类号： B64D33/00 , F01D25/18 , F02C7/00 , F16N19/00 , F02C7/06
CPC分类号： B64D33/00 , F01D25/18 , F02C7/00 , F16N19/00 , Y02T50/671
摘要： The reservoir has three fastening elements, on the upper part of the reservoir and the two others on the lower part of opposed end faces.The fastening elements are provided at the ends of an axle mounted in elastic support means and in a tubular passage parallel to the adjacent face of the housing and parallel to the axis of the turbojet engine, secured to the reservoir and passing through it from end to end.
摘要翻译：储存器具有三个紧固元件，位于储存器的上部，另外两个位于相对端面的下部。紧固元件设置在安装在弹性支撑装置中的轴的端部处，并且在平行于壳体的相邻面并且平行于涡轮喷气发动机的轴线的管状通道中，固定到储存器并且从端部通过它结束。

54. 发明授权

US4206776A Gravity-controlled flow valve 失效
标题翻译：重力控制流量阀
公开(公告)号：US4206776A
公开(公告)日：1980-06-10
申请号：US954635
申请日：1978-10-25
申请人： Eberhard Bader
发明人： Eberhard Bader
IPC分类号： B64D33/00 , F01M11/06 , F16K17/36
CPC分类号： B64D33/00 , F01M11/065 , F16K17/36 , Y10T137/0923
摘要： A gravity-controlled flow valve of the pendulum-type, having a valve body with two chambers which communicate through gaps formed in a separating wall between the chambers and an adjoining outer circumferential surface of a rotary slide valve. A pendulum is connected to the rotary slide valve for movement within the valve body whereby flow apertures in a sleeve-like member are either opened or closed by the rotary slide valve in cooperation with flow apertures in that valve.
摘要翻译：摆锤式重力控制流量阀，具有带有两个腔室的阀体，该阀体通过形成在腔室之间的分隔壁中的间隙与旋转滑阀的相邻的外圆周表面相连通。摆动件连接到旋转滑阀以在阀体内移动，由此套筒状构件中的流动孔口由旋转滑阀与该阀中的流动孔口协作地打开或关闭。

55. 发明公开

US20240263584A1 AIRCRAFT PROPULSION SYSTEM WITH START-UP CONTROL DEVICE 审中-公开
公开(公告)号：US20240263584A1
公开(公告)日：2024-08-08
申请号：US18569336
申请日：2022-06-09
申请人： SAFRAN , SAFRAN HELICOPTER ENGINES
发明人： Antoine Pierre Emmanuel FERRAND , Fabien MERCIER-CALVAIRAC
IPC分类号： F02C7/268 , B64D33/00 , F02C7/264
CPC分类号： F02C7/268 , B64D33/00 , F02C7/264 , F05D2260/85
摘要： A propulsion system includes a gas turbine designed so that a combustion chamber can be ignited in a first ignition range of rotational speeds of a compressor shaft. The system further includes a control device designed to control an electric starter to accelerate the compressor shaft and, when the compressor shaft is accelerated, to control an attempt to ignite the combustion chamber. The gas turbine is designed so that the combustion chamber can be ignited in a second ignition range which is higher than the first ignition range, but not between these two ignition ranges, and the ignition attempt is carried out in the second ignition range.

56. 发明授权

US12054254B2 Method and system for cooling electronics in an unmanned aerial vehicle 有权
公开(公告)号：US12054254B2
公开(公告)日：2024-08-06
申请号：US17730414
申请日：2022-04-27
申请人： Daniel McCann
发明人： Daniel McCann
IPC分类号： B64C39/02 , B64D33/00 , B64U20/92 , B64U20/96 , H05K7/20
CPC分类号： B64C39/024 , B64D33/00 , B64U20/92 , B64U20/96 , H05K7/20145 , H05K7/20154 , H05K7/20336 , H05K7/2039
摘要： The present disclosure provides an unmanned aerial vehicle (UAV) having a housing containing electronic components required of the UAV and a heat transfer device for cooling heat generated by said electronic components; at least one boom for connecting said housing to at least one propeller. The boom includes one or more inlet located on a first surface of the boom and within an airflow of said at least one propeller; at least one outlet on a second surface of the boom; a hallow channel extending in interior of the boom from said at least one inlet to said at least one outlet, wherein said airflow generated by said at least one propeller passes into said at least one inlet through the hollow channel to said at least one outlet providing cooling for said heat transfer device.

57. 发明公开

US20230382539A1 AIRCRAFT ENGINE WITH STATOR HAVING VARYING GEOMETRY 审中-公开
公开(公告)号：US20230382539A1
公开(公告)日：2023-11-30
申请号：US17804570
申请日：2022-05-30
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Alexandre CAPRON , Karan ANAND , Tammy YAM , Ali AZMI , Sylvain CLAUDE , Krishna Prasad BALIKE , Prakul MITTAL
IPC分类号： B64D27/10 , B64D33/00
CPC分类号： B64D27/10 , B64D33/00
摘要： An aircraft engine, has: an upstream stator having upstream stator vanes distributed about a central axis; and a downstream stator having downstream stator vanes distributed about the central axis, the downstream stator located downstream of the upstream stator, a number of the upstream stator vanes different than a number of the downstream stator vanes, the downstream stator vanes including: a first vane, a major portion of a leading edge of the first vane circumferentially overlapped by one of the upstream stator vanes; and a second vane differing from the first vane by a geometric parameter, the geometric parameter causing the second vane to have one or more of: a stiffness greater than that of the first vane, and a major portion of a leading edge of the second vane circumferentially overlapped by another one of the upstream stator vanes.

58. 发明授权

US11731777B2 Control circuit for a power distribution node 有权
公开(公告)号：US11731777B2
公开(公告)日：2023-08-22
申请号：US17400866
申请日：2021-08-12
申请人： GE Aviation Systems Limited
发明人： John Oliver Collins , David Alan Elliott
IPC分类号： B64D33/00 , H02J9/06 , B64D41/00 , G06F1/3206 , H02H1/00 , H02H9/02
CPC分类号： B64D33/00 , B64D41/00 , G06F1/3206 , H02H1/0007 , H02H9/02 , H02J9/061 , B64D2221/00 , H02J2310/44
摘要： A power distribution node, includes a power switch controllably operable to supply energy from an input to an output when the power switch is closed and to not supply energy from the input to the output when the power switch is open, a controller module, a supply power source connected with and energizing the controller module, and a control circuit configured to sense a power characteristic of the power distribution node.

59. 发明授权

US10487744B2 Fence for duct tone mitigation 有权
公开(公告)号：US10487744B2
公开(公告)日：2019-11-26
申请号：US15161953
申请日：2016-05-23
申请人： United Technologies Corporation
发明人： Keith A. Post , Daniel W. Shannon , Steven H. Zysman , Mark Zsurka , Diego H. de la Riva , Sudarshan N. Koushik
IPC分类号： F02C7/24 , B64D29/00 , F01D25/24 , F02C3/04 , B64D33/00 , B64C23/06
CPC分类号： F02C7/24 , B64D29/00 , B64D33/00 , F01D25/24 , F02C3/04 , B64C23/06 , F05D2220/32 , F05D2260/96
摘要： Aspects of the disclosure are directed to a system associated with an engine of an aircraft comprising: a duct, an inlet coupled to the duct, and a fence coupled to the inlet or located upstream of the inlet. In some embodiments, the system further comprises a valve body coupled to the duct. In some embodiments, the valve body includes at least one valve that is configured to rotate between a closed state and an open state.

60. 发明授权

US10060284B2 Engine inlet total air temperature sensor 有权
公开(公告)号：US10060284B2
公开(公告)日：2018-08-28
申请号：US14774519
申请日：2013-12-16
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Xuejun Liu , Matthew R. Feulner
IPC分类号： G01K13/02 , F01D17/08 , F01D21/00 , B64D33/00
CPC分类号： F01D17/085 , B64D33/00 , F01D21/003 , F05D2260/80 , G01K13/02 , G01K13/028 , G01K2013/024 , G01K2205/02
摘要： A total air temperature (TAT) sensor assembly is disclosed. The assembly includes a housing that accommodates a temperature sensor. The assembly also includes a first airfoil that includes a leading end and a trailing end and a second airfoil that includes a leading end and a trailing end. The first and second airfoils are disposed in a spaced-apart fashion that defines a curved passageway so incoming air can flow between the first and second airfoils before engaging the housing and the temperature sensor. The trailing ends of the airfoils are disposed on opposite sides of the housing and spaced apart from the housing to permit air flowing through the curved passageway to pass the housing.

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