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1. 发明申请

US20180093760A1 FLIGHT CONTROL PUMP SYSTEMS 审中-公开
公开(公告)号：US20180093760A1
公开(公告)日：2018-04-05
申请号：US15723521
申请日：2017-10-03
申请人： Sikorsky Aircraft Corporation
发明人： Scott J. Young , Frederick L. Bourne , William F. Lange
IPC分类号： B64C27/02 , B64C27/16 , G05D1/02 , F16H61/00
CPC分类号： B64C27/027 , B64C13/36 , B64C13/42 , B64C27/16 , F16D43/22 , F16H61/0006 , F16H61/0031 , G05D1/0202 , Y02T50/44
摘要： A flight control pump system includes an electrical machine configured to operate in a motor mode and in a generator mode. A pump is operatively connected to be driven by the electrical machine in the motor mode. An overriding clutch is operatively connected to the electrical machine and to the pump to transfer torque from a main transmission to drive the pump and the electrical machine in the generator mode, and to decouple the main transmission from the electrical machine and the pump in the motor mode.

2. 发明授权

US09886039B2 System and method for avoiding inadvertant entry into an unsafe vertical descent speed region for rotorcraft 有权
公开(公告)号：US09886039B2
公开(公告)日：2018-02-06
申请号：US14623382
申请日：2015-02-16
申请人： Bell Helicopter Textron Inc.
发明人： Luke D. Gillett , Joseph M. Schaeffer , Christopher M. Bothwell , Robert Worsham , Jillian Alfred , Sung Kim
IPC分类号： G05D1/08 , G05D1/06 , B64C27/10 , B64C27/16 , B64C27/605
CPC分类号： G05D1/0607 , B64C27/10 , B64C27/16 , B64C27/605
摘要： A flight control system having a control law, the control law operable to generate a modified pitch command, the modified pitch command representing a greater amount of collective pitch compared to an amount of collective pitch generated by a first pitch command, the modified pitch command being generated because a vertical descent speed of the rotorcraft at a given forward airspeed is greater than a threshold. A method of avoiding entry into an undesired vertical descent speed region during operation of a rotorcraft, including measuring a forward airspeed; evaluating a vertical descent of the rotorcraft; and generating a modified collective pitch command in respond to a first collective pitch command having a collective pitch value that would cause the rotorcraft to experience a vertical descent rate greater than a threshold value at the forward airspeed of the rotorcraft.

3. 发明授权

US09878788B2 Aircraft 有权
公开(公告)号：US09878788B2
公开(公告)日：2018-01-30
申请号：US14795406
申请日：2015-07-09
申请人： ADVISR AERO LLC
发明人： Linden S. Blue , Austin J. N. Blue
IPC分类号： B64C27/16 , B64C27/18 , B64C27/24 , B64C3/38 , B64C37/00 , B64C39/10 , B64C29/00
CPC分类号： B64C39/10 , B64C3/38 , B64C27/16 , B64C27/18 , B64C27/24 , B64C29/0075 , B64C37/00 , B64C2039/105
摘要： An aircraft is provided that is convertible in flight between a rotary wing configuration and a fixed wing configuration. In its fixed wing configuration the aircraft resembles a Blended Wing Body (BWB) having a swept wing angle β. Conversions from the fixed wing configuration to the rotary wing configuration, and vice versa, are accomplished by flipping an outboard portion of one wing through 180° to reorient the leading edge of the outboard portion by an angle of 2β to establish a reverse sweep. In its rotary configuration, the entire aircraft is rotated.

4. 发明申请

US20170008622A1 AIRCRAFT 有权
标题翻译：飞机
公开(公告)号：US20170008622A1
公开(公告)日：2017-01-12
申请号：US14795406
申请日：2015-07-09
申请人： ADVISR AERO LLC
发明人： Linden S. Blue , Austin J. N. Blue
IPC分类号： B64C27/22 , B64C39/10 , B64C3/38
CPC分类号： B64C39/10 , B64C3/38 , B64C27/16 , B64C27/18 , B64C27/24 , B64C29/0075 , B64C37/00 , B64C2039/105
摘要： An aircraft is provided that is convertible in flight between a rotary wing configuration and a fixed wing configuration. In its fixed wing configuration the aircraft resembles a Blended Wing Body (BWB) having a swept wing angle β. Conversions from the fixed wing configuration to the rotary wing configuration, and vice versa, are accomplished by flipping an outboard portion of one wing through 180° to reorient the leading edge of the outboard portion by an angle of 2β to establish a reverse sweep. In its rotary configuration, the entire aircraft is rotated.
摘要翻译：提供一种飞行器，其可在旋翼结构和固定翼构型之间在飞行中可转换。在其固定翼构型中，飞机类似于具有扫掠翼角β的混合翼体（BWB）。通过将一个机翼的外侧部分翻转180°，将外侧部分的前缘重新定位2°的角度来建立反向扫描来实现从固定翼构型到旋转翼构型的转换，反之亦然。在其旋转结构中，整个飞机旋转。

5. 发明授权

US09464624B2 Gyroglider power-generation, control apparatus and method 有权
标题翻译：陀螺仪发电，控制装置和方法
公开(公告)号：US09464624B2
公开(公告)日：2016-10-11
申请号：US14548842
申请日：2014-11-20
申请人： Grant Howard Calverley
发明人： Grant Howard Calverley
IPC分类号： F03D7/00 , F03D5/00 , F03D11/04 , B64C27/02 , B64C39/02 , B64C27/16
CPC分类号： F03D5/00 , B64C27/02 , B64C27/16 , B64C39/022 , B65H75/4402 , B65H75/4481 , B65H2701/35 , F03D7/00 , F03D9/25 , F03D13/20 , F03D80/70 , F05B2240/40 , F05B2240/921 , F05B2270/32 , G05D1/0866 , Y02E10/70 , Y02E10/723 , Y02E10/725 , Y02T10/90
摘要： A power generation apparatus and method comprises at least one gyroglider rotary wing flying at an altitude above the nap of the earth. A strong and flexible tether, connected to the gyroglider frame is pulled with a force generated by the rotary wing. The force is transmitted to a ground station that converts the comparatively linear motion of the tether being pulled upward with a lifting force. The linear motion is transferred to a rotary motion at the ground station to rotate an electrical generator. The tether is retrieved and re-coiled about a drum by controlling the gyroglider to fly down at a speed and lift force that permit recovery of the gyroglider at a substantially reduced amount of retrieval force compared to the lifting force during payout of the tether. Thus, the net difference in force results in a net gain of energy.
摘要翻译：发电装置和方法包括至少一个在地球上方的高度上飞行的陀螺仪旋转翼。连接到陀螺仪框架的强大而灵活的系绳用旋转翼产生的力拉动。该力传递到地面站，该地面站转换由提升力向上拉的系绳的比较线性的运动。线性运动在地面站转移到旋转运动，以旋转发电机。通过控制陀螺滑翔机以与系绳支撑期间的提升力相比基本上减少的撤回力量的速度和提升力而使陀螺仪回缩，从而将系绳重新卷绕在滚筒周围。因此，力的净差异导致能量的净增益。

6. 发明申请

US20150232178A1 AIRCRAFT FOR VERTICAL TAKE-OFF AND LANDING WITH TWO WING ARRANGEMENTS 审中-公开
标题翻译：用于双向安装的垂直起落架的飞机
公开(公告)号：US20150232178A1
公开(公告)日：2015-08-20
申请号：US14378604
申请日：2013-02-13
申请人： Johannes REITER
发明人： Johannes Reiter
IPC分类号： B64C29/00 , B64C37/00 , B64C3/38
CPC分类号： B64C29/0033 , B64C3/38 , B64C3/385 , B64C27/00 , B64C27/001 , B64C27/16 , B64C27/18 , B64C29/00 , B64C29/0075 , B64C29/02 , B64C37/00 , B64C39/008 , B64C39/024 , B64C2201/088 , B64C2201/102 , B64C2201/104 , B64C2201/108 , B64C2201/165
摘要： The present invention relates to an aircraft comprising a fuselage (100) comprising a fuselage axis (101), a first wing arrangement (110) and a second wing arrangement (120). The first wing arrangement (110) is mounted to the fuselage (100) such that the first wing arrangement (110) is tiltable around a first longitudinal wing axis (111) of the first wing arrangement (110) and such that the first wing arrangement (110) is rotatable around the fuselage axis (101). The second wing arrangement (120) comprises at least one propulsion unit (122), wherein the second wing arrangement (120) is mounted to the fuselage (100) such that the second wing arrangement (120) is tiltable around a second longitudinal wing axis (121) of the second wing arrangement (120) and such that the second wing arrangement (120) is rotatable around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are adapted in such a way that, in a fixed-wing flight mode, the first wing arrangement (110) and the second wing arrangement (120) do not rotate around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are further adapted in such a way that, in a hover flight mode, the first wing arrangement (110) and the second wing arrangement (120) are tilted around the respective first longitudinal wing axis (111) and the respective second longitudinal wing axis (121) with respect to its orientations in the fixed-wing flight mode and that the first wing arrangement (110) and the second wing arrangement (120) rotate around the fuselage axis (101).
摘要翻译：本发明涉及一种飞行器，其包括机身（100），其包括机身轴线（101），第一机翼装置（110）和第二机翼装置（120）。第一机翼装置（110）安装到机身（100），使得第一机翼装置（110）能围绕第一机翼装置（110）的第一纵向机翼轴线（111）倾斜，并且使得第一机翼装置（110）能够围绕机身轴线（101）旋转。第二机翼装置（120）包括至少一个推进单元（122），其中第二机翼装置（120）安装到机身（100）上，使得第二机翼装置（120）可围绕第二纵向机翼轴线（121），并且使得所述第二机翼装置（120）能够围绕所述机身轴线（101）旋转。第一机翼装置（110）和第二机翼装置（120）以这样的方式适配，使得在固定翼飞行模式中，第一机翼装置（110）和第二机翼装置（120）不围绕机身轴（101）。第一机翼装置（110）和第二机翼装置（120）进一步适于以悬停飞行模式，第一机翼装置（110）和第二机翼装置（120）围绕相应的第一纵向翼片轴线（111）和相应的第二纵向翼片轴线（121）相对于其在固定翼飞行模式中的定向，并且第一翼形装置（110）和第二翼形装置（120）围绕机身旋转轴（101）。

7. 发明授权

US3930625A Steam-powered aircraft 失效
标题翻译：蒸汽动力的飞机
公开(公告)号：US3930625A
公开(公告)日：1976-01-06
申请号：US502271
申请日：1974-09-03
申请人： Alexander Krivka
发明人： Alexander Krivka
IPC分类号： B64C27/08 , B64C27/16
CPC分类号： B64C27/08 , B64C27/16
摘要： A steam generator on the aircraft selectively delivers high-pressure steam to atmospheric discharge jets on a lift rotor and/or to peripheral jets on a forwardly-directed propulsion propeller. The propeller is enclosed by a hollow shroud into which the steam jets discharge so that the shroud acts both as a propeller efficiency-enhancing device and a steam condenser to permit recycling of the condensate.
摘要翻译：飞机上的蒸汽发生器选择性地将高压蒸汽输送到升降机转子上的大气排放喷嘴和/或向前定向的推进螺旋桨上的周边射流。螺旋桨由中空的外壳包围，蒸汽喷头喷射到其中，使得护罩同时作为螺旋桨效率提高装置和蒸汽冷凝器，以允许冷凝物的再循环。

8. 发明授权

US2268552A Rotor operating mechanism 失效
标题翻译：转子操作机构
公开(公告)号：US2268552A
公开(公告)日：1942-01-06
申请号：US28447139
申请日：1939-07-14
申请人： UNITED AIRCRAFT CORP
发明人： RHINES THOMAS B
IPC分类号： B64C27/16
CPC分类号： B64C27/16 , Y10T74/19665

9. 发明授权

US1669758A Helicopter 失效
公开(公告)号：US1669758A
公开(公告)日：1928-05-15
申请号：US9936826
申请日：1926-04-02
申请人： ISACCO
发明人： VITTORIO ISACCO , VICENTE ANDRES
IPC分类号： B64C27/16
CPC分类号： B64C27/16

10. 发明授权

US1398750A Aeroplane 失效
公开(公告)号：US1398750A
公开(公告)日：1921-11-29
申请号：US28166519
申请日：1919-03-10
申请人： STEWART JOHN H
发明人： STEWART JOHN H
IPC分类号： B64C27/04
CPC分类号： B64C27/16

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