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公开(公告)号：US20180327086A1
公开(公告)日：2018-11-15
申请号：US15594588
申请日：2017-05-13
IPC分类号： B64C27/32 , B64C27/605 , B64C29/00 , B64C27/06 , F16C19/06
CPC分类号： B64C27/32 , B64C27/06 , B64C27/605 , B64C29/0033 , F16C19/06 , F16C2326/43
摘要： An aircraft rotor assembly has a yoke with at least two arms extending therefrom. The yoke is attached to a mast through a constant-velocity joint, thereby permitting axial tilt of the yoke relative to the mast. Each arm of the yoke includes an axisymmetric elastomeric bearing with a spherical central member and two opposite partially-spherical members attached to the central member. Each axisymmetric bearing cooperates with a cup and a bracket. Each cup is attached to one of the yoke arms and each bracket is attached to a blade cuff.
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公开(公告)号：US20180327078A1
公开(公告)日：2018-11-15
申请号：US15593241
申请日：2017-05-11
CPC分类号： B64C5/02 , B64C27/06 , B64C27/82 , B64C2003/142 , B64C2027/8272 , B64C2027/8281
摘要： In one embodiment, a horizontal stabilizer comprises an airfoil structure configured to be mounted to an aircraft at a horizontal orientation. The airfoil structure comprises a leading edge, a trailing edge, a top surface, and a bottom surface. Moreover, the airfoil structure is cambered, wherein a camber of the airfoil structure forms a concave slope on the top surface and a convex slope on the bottom surface.
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公开(公告)号：US20180259977A1
公开(公告)日：2018-09-13
申请号：US15863238
申请日：2018-01-05
CPC分类号： G05D1/101 , B64C13/503 , B64C27/06 , B64C27/82 , B64C39/02 , B64C2027/8236 , G06F3/0482 , G06F17/243 , G06F17/248
摘要： An example computer-implemented method for natural language mission planning includes: responsive to receiving a request to initiate mission planning for a selected mission type from a plurality of mission types, constructing, by a processing system, a mission narrative that describes a mission intent based on the selected mission type, the mission narrative comprising a plurality of fields; populating, by the processing system, the plurality of fields in the mission narrative from an autonomous mission manager based on the selected mission type with options to be selected by a mission planner; responsive to presenting the populated plurality of fields to the mission planner, filling, by the processing system, the mission narrative with the received selected options; creating, by the processing system, an optimized mission plan based on the mission narrative; and controlling, by the processing system, a vehicle based on the optimized mission plan.
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公开(公告)号：US20170334554A1
公开(公告)日：2017-11-23
申请号：US15533502
申请日：2015-10-15
发明人： Krzysztof Kopanski , Justin Thomas
IPC分类号： B64C27/473 , B64C27/06 , B64C27/00
CPC分类号： B64C27/473 , B64C27/008 , B64C27/06 , B64C2027/4736
摘要： An aircraft rotor blade includes a surface of the rotor blade, at least one main hole that extends through the surface and has a width and a length, and at least one leader hole that extends through the surface and has a length that is less than the length of the main hole and arranged spaced from and adjacent the main hole. The leader hole gradually increases in width from a first end of the leader hole opposite the main hole to an opposed second end of the leader hole proximate the main hole to operatively gradually distribute stress in the leader and main holes and rotor blade and reduce an amount of the stress exerted therein.
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公开(公告)号：US20170216638A1
公开(公告)日：2017-08-03
申请号：US15122057
申请日：2015-02-25
发明人： Noriko ASAYAMA , Yuhei MATSUBARA
CPC分类号： A62C3/025 , A62C3/0228 , A62C3/0235 , A62C5/002 , A62C5/033 , A62C8/005 , B64C27/06 , B64D1/16
摘要： Provided is a dropping-type fire extinguishing body that, in fire extinguishing using a gel-like fire extinguishing agent, can allow the fire extinguishing agent to be smoothly conveyed and dropped.A dropping-type fire extinguishing body 1 to be dropped onto the fire site to extinguish the fire, wherein a gelling agent 3 is contained in a bag body 2 formed of a water-permeable material and water is permeated into the body and is mixed with the gelling agent to prepare a gel-like fire extinguishing agent, thereby filling the gel-like fire extinguishing agent into the inside of the bag body.
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公开(公告)号：US20170211483A1
公开(公告)日：2017-07-27
申请号：US15327631
申请日：2015-07-21
发明人： Romain THIRIET , Camel SERGHINE , Frederic MOULON
CPC分类号： F02C7/277 , A62C3/08 , B60Y2200/52 , B64C27/06 , B64D27/10 , B64D31/06 , B64D35/08 , F01D19/00 , F05D2220/329 , F05D2260/85 , F05D2270/093 , Y02T50/671
摘要： The invention relates to a device for the rapid reactivation of a helicopter turbine engine (6), characterised in that it comprises a pneumatic turbine (7) mechanically connected to said turbine engine (6) so as to be able to rotate it and ensure reactivation thereof; a pneumatic storage (9) connected to said pneumatic turbine (7) by means of a pneumatic circuit (10) for supplying pressurised gas to said pneumatic turbine (7); a controlled fast-opening pneumatic valve (11) arranged on the pneumatic circuit (10) between said storage (9) and said pneumatic turbine (7) and suitable for being on demand placed at least in an open position in which the gas can supply said pneumatic turbine (7), or in a closed position in which said pneumatic turbine (7) is no longer supplied with pressurised gas.
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公开(公告)号：US09650135B2
公开(公告)日：2017-05-16
申请号：US14885972
申请日：2015-10-16
申请人： AeroVironment Inc.
IPC分类号： B64C27/08 , B64C39/02 , B64C27/12 , B64C27/59 , B64C11/20 , B64C11/32 , B64C27/04 , B64C29/00 , B64C27/473 , B64D31/00 , B64C27/06 , G05D1/00
CPC分类号： B64D31/06 , B64C11/20 , B64C11/32 , B64C27/04 , B64C27/06 , B64C27/08 , B64C27/12 , B64C27/473 , B64C27/59 , B64C29/0033 , B64C39/02 , B64C39/024 , B64C39/028 , B64C2027/4733 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/126 , B64C2201/127 , B64D31/00 , G05D1/0038 , G05D1/005
摘要： A rotorcraft including a fuselage, one or more motor-driven rotors for vertical flight, and a control system. The motors drive the one or more rotors in either of two directions of rotation to provide for flight in either an upright or an inverted orientation. An orientation sensor is used to control the primary direction of thrust, and operational instructions and gathered information are automatically adapted based on the orientation of the fuselage with respect to gravity. The rotors are configured with blades that invert to conform to the direction of rotation.
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公开(公告)号：US20170073066A1
公开(公告)日：2017-03-16
申请号：US15265018
申请日：2016-09-14
申请人： AIRBUS HELICOPTERS
CPC分类号： B64C27/12 , B64C27/06 , B64C27/82 , F16H1/28 , F16H2057/0087
摘要： A power transmission system having at least one inlet speed-reducing gear and a main speed-reducing gear, each inlet speed-reducing gear comprising an inlet pinion meshing with an inlet gearwheel. The inlet gearwheel is constrained to rotate with a main pinion of the main speed-reducing gear, the main pinion meshing with a main gearwheel. At least one inlet gearwheel is secured to reversible connection means in order to be capable of driving a first additional drivetrain connected to an additional rotor.
摘要翻译： 一种具有至少一个入口减速齿轮和主减速齿轮的动力传动系统，每个入口减速齿轮包括与入口齿轮啮合的入口小齿轮。 入口齿轮被限制为与主减速齿轮的主小齿轮一起旋转，主小齿轮与主齿轮啮合。 至少一个入口齿轮固定到可逆连接装置，以便能够驱动连接到附加转子的第一附加传动系。
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公开(公告)号：US09566839B2
公开(公告)日：2017-02-14
申请号：US15132288
申请日：2016-04-19
申请人： PAL-V Europe, N.V.
发明人： Michael Alwin William Stekelenburg , Christiaan Cornelis Klok , Louis Petrus Valentijn Marie Van Rijn , Wouter Adriaan Soethoudt , Robert Christiaan Wegerif
摘要： A vehicle capable of being converted between a flying condition and an automotive riding condition. The vehicle has a telescopically extendable tail having a first tubular tail segment and a second tail segment disposed axially slideable within the first tubular tail segment. The tail is provided with at least two form-closing coupling members located at an axial distance from each other for providing a force-transferring coupling between the second tail segment and the first tubular tail segment in the extended state of the second tail segment, each of the form-closing coupling members capable of transferring torque and transverse forces, and each of the form-closing coupling members coming into engagement by axial displacement of the second tail segment in the outward direction.
摘要翻译： 能够在飞行状态和汽车行驶状态之间转换的车辆。 车辆具有可伸缩地延伸的尾部，其具有第一管状尾部段和在第一管状尾部段内轴向可滑动设置的第二尾部段。 尾部设置有至少两个形成 - 闭合联接构件，其位于彼此轴向距离处，以在第二尾段的延伸状态下在第二尾段和第一管段尾段之间提供力传递耦合，每个 能够传递扭矩和横向力的形状关闭联接构件，并且每个形成 - 闭合联接构件通过沿着向外方向的第二尾段的轴向位移而进入接合。
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公开(公告)号：US20160046371A1
公开(公告)日：2016-02-18
申请号：US14923608
申请日：2015-10-27
发明人： John Corrigan , Frank B. Stamps
CPC分类号： B64C27/82 , B64C27/06 , B64C27/10 , B64C27/14 , B64C27/32 , B64C27/52 , B64C27/57 , B64C27/64 , B64C2027/8227
摘要： A system and method to tilt coaxial counter-rotating rotor hub assemblies relative to a fuselage. The system includes a first rotor hub assembly and a second rotor hub assembly spaced apart from the first hub assembly and carried by the fuselage. The method includes pivotally attaching the first rotor hub assembly and the second rotor hub assembly to a pivot joint and thereafter tilting the first rotor hub assembly and the second rotor hub assembly about the pivot joint with a driver.
摘要翻译： 相对于机身倾斜同轴反转转子毂组件的系统和方法。 该系统包括第一转子轮毂组件和与第一轮毂组件间隔开并由机身承载的第二转子轮毂组件。 该方法包括将第一转子轮毂组件和第二转子轮毂组件枢转地连接到枢转接头，然后使用驱动器使第一转子轮毂组件和第二转子轮毂组件围绕枢转接头倾斜。
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