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公开(公告)号：US20180222597A1
公开(公告)日：2018-08-09
申请号：US15424801
申请日：2017-02-04
CPC分类号： B64D35/00 , B64C13/503 , B64C27/04 , B64D31/06 , F02C9/28 , F05D2220/323 , F05D2270/313 , G05B13/00
摘要： A power demand anticipation system for a rotorcraft includes an engine subsystem having an engine with a power output. The power demand anticipation system also includes one or more sensors including a cyclic control sensor. The one or more sensors are operable to detect one or more flight parameters of the rotorcraft to form sensor data including a cyclic control position. A power demand anticipation module is in data communication with the engine subsystem and the one or more sensors. The power demand anticipation module is operable to anticipate a power demand of the engine using the sensor data to form a power demand anticipation signal. The engine subsystem is operable to adjust the power output of the engine based on the power demand anticipation signal received from the power demand anticipation module.
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公开(公告)号：US10012305B2
公开(公告)日：2018-07-03
申请号：US15173879
申请日：2016-06-06
申请人： AIRBUS HELICOPTERS
发明人： Charles Louis
CPC分类号： F16H57/046 , B64D35/00 , B64D35/02 , F16H57/0435 , F16H57/0442 , F16N7/40 , F16N2260/24 , F16N2260/50
摘要： A power transmission gearbox provided with at least one lubrication system including a lubrication pump. The lubrication pump is in fluid flow communication with a fluid flow circuit leading to at least one spray means. The gearbox includes an emergency tank suitable for containing a lubrication fluid, the emergency tank being in fluid flow communication with the fluid flow circuit, the emergency tank being connected by at least one pipe to the fluid flow circuit upstream from each spray means, the lubrication fluid being moved in the fluid flow circuit to each spray means by a gas that is set into motion by the lubrication pump in the event of a leak of the lubrication liquid.
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公开(公告)号：US20180087561A1
公开(公告)日：2018-03-29
申请号：US15702958
申请日：2017-09-13
CPC分类号： F16C3/16 , B64C27/12 , B64C27/14 , B64C27/82 , B64D35/00 , B64D45/00 , B64D2045/009 , F16C3/02 , F16C3/026 , F16C2326/06 , F16C2326/43 , F16H57/0416
摘要： The present invention includes a thermal management system and method including: a drive shaft; one or more fans or impellers in fluid communication with at least a portion of the drive shaft; and one or more air management baffles configured to direct air flow between the impeller and the portion of the drive shaft. In one embodiment, the system and method further includes insulation positioned about the at least a portion of the drive shaft.
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公开(公告)号：US20170356525A1
公开(公告)日：2017-12-14
申请号：US15177783
申请日：2016-06-09
发明人： LAZAR MITROVIC , KEITH MORGAN
CPC分类号： F16H1/20 , B64D35/00 , F02C7/36 , F05D2260/4031
摘要： A reduction gearbox for an aircraft engine, including an input pinion configured to be driven by the aircraft engine, a input gear meshed with the input pinion, a drive gear meshed with the input gear, an output pinion, and an output gear meshed with the output pinion and configured to drive an output shaft of the aircraft engine. The reduction gearbox is selectively configurable between an engaged configuration where the input gear and output pinion are drivingly engaged and a disengaged configuration where the input gear is rotatable independently of the output pinion. The output shaft may drive a propeller and the gearbox may include a propeller brake. A method of driving a generator of a turboprop engine is also discussed.
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公开(公告)号：US20170305568A1
公开(公告)日：2017-10-26
申请号：US15407486
申请日：2017-01-17
发明人： James Elbert King , Jeffrey Matthew Williams , Christopher R. Jackson , Andrew G. Baines , James Everett Kooiman
IPC分类号： B64D27/26 , B64C29/00 , B64D35/00 , B64C27/26 , B64C3/32 , F16C17/02 , F16H57/021 , F16H57/02
CPC分类号： B64D27/26 , B64C3/32 , B64C27/14 , B64C27/26 , B64C27/28 , B64C29/0033 , B64D27/12 , B64D35/00 , B64D35/08 , B64D2027/264 , B64D2027/266 , F16C17/02 , F16H57/021 , F16H2057/02043 , Y10T29/49318 , Y10T74/1966
摘要： A propulsion system for a tiltrotor aircraft includes an engine supported by the airframe and a fixed gearbox operably coupled to the engine. Inboard and outboard tip ribs extend above the wing and define slots. Inboard and outboard bearing cartridges are received in respective slots. The inboard and outboard bearing cartridges respectively include inboard and outboard bearing assemblies. A pylon assembly is rotatably coupled between the inboard and outboard bearing assemblies. The pylon assembly includes a spindle gearbox having an input gear, a mast operably coupled to the input gear and a proprotor assembly operable to rotate with the mast. The spindle gearbox is rotatable about a conversion axis to selectively operate the tiltrotor aircraft between helicopter and airplane modes. A common shaft, rotatable about the conversion axis, is configured to transfer torque from an output gear of the fixed gearbox to the input gear of the spindle gearbox.
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公开(公告)号：US20170305565A1
公开(公告)日：2017-10-26
申请号：US15407449
申请日：2017-01-17
发明人： James Everett Kooiman , George Ryan Decker , Matthew Carl VanBuskirk , Andrew G. Baines , Keith Alan Stanney
IPC分类号： B64D27/26 , F16C17/26 , F16C17/02 , B64D35/00 , B64C29/00 , B64C27/26 , B64C3/32 , F16H57/02
CPC分类号： B64D27/26 , B64C3/32 , B64C27/22 , B64C27/26 , B64C29/0033 , B64D35/00 , B64D2027/266 , B64F5/40 , F16C17/02 , F16C17/26 , F16H2057/02043 , Y10T29/49318 , Y10T74/1966
摘要： A propulsion system for a tiltrotor aircraft includes an engine supported by the airframe and a fixed gearbox operably coupled to the engine. Inboard and outboard pedestals are supported by the airframe and positioned above the wing. A pylon assembly is rotatably coupled between the inboard and outboard pedestals. The pylon assembly includes a spindle gearbox having an input gear, a mast operably coupled to the input gear and a proprotor assembly operable to rotate with the mast. The spindle gearbox is rotatable about a conversion axis to selectively operate the tiltrotor aircraft between helicopter and airplane modes. A common shaft, rotatable about the conversion axis, is configured to transfer torque from an output gear of the fixed gearbox to the input gear of the spindle gearbox. Each of the inboard and outboard pedestals includes a journal bearing that provides a stiff coupling with the pylon assembly.
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公开(公告)号：US20170241539A1
公开(公告)日：2017-08-24
申请号：US15285232
申请日：2016-10-04
发明人： Scott D. Poster , David A. Elliott , Gary A. Cope
CPC分类号： F16H57/0447 , B64C27/06 , B64C27/12 , B64C27/82 , B64D35/00 , F16H57/027 , F16H57/0424 , F16H57/0438 , F16H57/0442 , F16H57/045 , F16H57/0471
摘要： A lubrication system includes a reserve housing configured to retain a lubrication fluid. A supply line in fluid communication with the reserve housing is configured to provide pressurized lubrication fluid to the reserve housing. An overflow tube has an overflow port, the overflow tube being configured to prevent the volume of the lubrication fluid from exceeding a certain amount. A metering jet is configured to allow the lubrication fluid to flow from the reserve housing onto a component, such as a bearing, in the gearbox at a predetermined rate. The metering jet provides flow of the lubrication fluid onto the bearing even when the supply line no longer provides pressurized lubrication fluid to the reserve housing.
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公开(公告)号：US20170240267A1
公开(公告)日：2017-08-24
申请号：US15589017
申请日：2017-05-08
CPC分类号： B64C11/04 , B63H1/20 , B64C11/02 , B64C39/024 , B64C2201/042 , B64C2201/108 , B64C2201/165 , B64D35/00 , F16D1/112
摘要： A propulsion system comprises a propeller and a driving device coupled with the propeller. The propeller comprises a hub having a receiving hole, a plurality of blades connected to the hub, and a connecting surface. The driving device comprises a body portion, an elastic abutting member disposed on the body portion and configured to abut against the connecting surface, and a lock portion disposed on the body portion and including a first snap-fitting portion. A second snap-fitting portion is arranged on an inner wall of the receiving hole and is configured to snap with the first snap-fitting portion.
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公开(公告)号：US20170021935A1
公开(公告)日：2017-01-26
申请号：US15186662
申请日：2016-06-20
发明人： Jacques Hervé Marche
CPC分类号： B64D27/26 , B64D35/00 , B64D2027/264 , B64D2027/266 , F02C3/107 , F02C6/206 , F02C7/20 , F02C7/36 , F05D2220/324 , F05D2240/62 , F05D2250/611
摘要： An engine assembly for an aircraft, comprising a mast. The engine assembly comprises an engine with a horizontal engine axis, an engine shaft having a first end rigidly connected to the engine and a second end, and a reducer having an input shaft meshing with the second end, and an output shaft to which a propeller is fixed. The engine assembly is configured such that the engine is fixed to the mast by a rigid connection, the reducer is fixed to the mast by means of flexible fasteners, the rotation between the engine shaft and the input shaft being driven via a slide link, the engine shaft has a first part and a second part and, therebetween, a flexible part assuring a tolerance to an angular misalignment between the axis of the second part and the axis of the first part.
摘要翻译： 一种用于飞行器的发动机组件，包括桅杆。 发动机组件包括具有水平发动机轴线的发动机，具有刚性地连接到发动机的第一端的发动机轴和第二端，以及具有与第二端啮合的输入轴的减速器，以及输出轴，螺旋桨 是固定的 发动机组件构造成使得发动机通过刚性连接固定到桅杆上，减速器通过柔性紧固件固定到桅杆上，发动机轴和输入轴之间的旋转通过滑动连杆驱动， 发动机轴具有第一部分和第二部分，并且在其间具有柔性部分，确保对第二部分的轴线和第一部分的轴线之间的角度偏移的公差。
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10.发明申请公开(公告)号：US20160258497A1
公开(公告)日：2016-09-08
申请号：US15057248
申请日：2016-03-01
CPC分类号： F16D48/06 , B64C29/0058 , B64C29/0066 , B64D35/00 , F01D15/12 , F05D2220/328 , F05D2220/90 , F05D2260/96 , F16D2500/10412 , F16D2500/50293
摘要： Systems and methods to control an amount of axial clearance within a clutch transmission system are disclosed. A propulsion system includes a clutch transmission system having clutch vibratory response clearance control logic configured to iteratively control the amount of axial clearance within the clutch transmission system so as to achieve a desired, e.g., consistent and/or limited, clutch vibratory response.
摘要翻译： 公开了一种用于控制离合器传动系统内的轴向间隙量的系统和方法。 推进系统包括具有离合器振动响应间隙控制逻辑的离合器传动系统，该离合器振动响应间隙控制逻辑被配置为迭代地控制离合器传动系统内的轴向间隙的量，以便实现期望的，例如一致的和/或有限的离合器振动响应。
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