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公开(公告)号：US11853054B2
公开(公告)日：2023-12-26
申请号：US17603193
申请日：2021-10-12
IPC分类号： B64C27/02 , G05D1/08 , B64C11/50 , B64C27/10 , B64C27/12 , B64C27/22 , B64C27/26 , B64D31/00 , B64C27/00 , B64C27/14 , B64D27/24 , H02K1/27 , B64C11/48 , B64C27/82
CPC分类号： G05D1/0858 , B64C11/50 , B64C27/006 , B64C27/02 , B64C27/021 , B64C27/025 , B64C27/027 , B64C27/028 , B64C27/10 , B64C27/12 , B64C27/14 , B64C27/22 , B64C27/26 , B64D31/00 , B64C11/48 , B64C2027/8236 , B64D27/24 , H02K1/27
摘要： A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thrust to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.
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公开(公告)号：US11829161B2
公开(公告)日：2023-11-28
申请号：US17603180
申请日：2020-04-10
IPC分类号： B64C27/10 , G05D1/08 , B64C11/50 , B64C27/02 , B64C27/12 , B64C27/22 , B64C27/26 , B64D31/00 , B64C27/00 , B64C27/14 , B64D27/24 , H02K1/27 , B64C11/48 , B64C27/82
CPC分类号： G05D1/0858 , B64C11/50 , B64C27/006 , B64C27/02 , B64C27/021 , B64C27/025 , B64C27/027 , B64C27/028 , B64C27/10 , B64C27/12 , B64C27/14 , B64C27/22 , B64C27/26 , B64D31/00 , B64C11/48 , B64C2027/8236 , B64D27/24 , H02K1/27
摘要： A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thrust to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.
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公开(公告)号：US11757523B2
公开(公告)日：2023-09-12
申请号：US17764085
申请日：2020-09-28
CPC分类号： H04B7/18504 , B64C11/04 , B64C11/30 , B64C27/02 , B64D1/02 , B64C39/024 , B64U2101/20
摘要： The present invention relates to an aerially distributable communications device (ACCD) including one or more gyrochutes and communications module configured for wireless communication with external communication nodes. The communications module can be configured for mesh network type communication with similar aerially distributable communications device, or as a gateway type communications device to a wide area network such as a satellite network. The ACCD is for deployment in remote areas and/or areas where normal communications networks are down, such as disaster areas. The ACCD can be deployed from an aircraft or a spacecraft. The ACCD can further be configured with emergency equipment such as water purification equipment, power charging equipment, or the like.
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公开(公告)号：US09914525B2
公开(公告)日：2018-03-13
申请号：US14925472
申请日：2015-10-28
申请人： AIRBUS HELICOPTERS
发明人： David Alfano
摘要： A rotorcraft provided on top with a waterdrop-shaped fairing arranged below the rotary wing of a main rotor of the rotorcraft and overlying a cover covering a power plant of the rotorcraft. The trailing edge(s) of the fairing is/are provided with a respective movable member guiding a first stream of air flowing along the fairing and escaping from the trailing edge towards the rear of the rotorcraft in flight. By way of example, the movable member is arranged as a flap or as a bladed roller that may potentially be motor-driven as a function of the effects of the first stream of air on the behavior of the rotorcraft in flight.
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公开(公告)号：US20160208780A1
公开(公告)日：2016-07-21
申请号：US14548842
申请日：2014-11-20
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.
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公开(公告)号：US20150353189A1
公开(公告)日：2015-12-10
申请号：US14760572
申请日：2013-09-02
摘要： The power plant of the hybrid (transformed) vehicle belongs to area of light aircrafts and motorcycles. The essence of the invention is a possibility of transfer the rotary moment from the motorcycle chain not only to the rear wheel, but also to two propellers. Thus propellers together with balancing device, called by the elements of the air drive (EAD) can be fixed in two positions. Firstly when the plane of their rotation is perpendicular to the planes of rotation of a back wheel (the flight mode). Secondly, when propellers (and EAD) are pressed to side parts of the hybrid aircraft (the land mode).
摘要翻译： 混合（变换）车辆的发电厂属于轻型飞机和摩托车区域。 本发明的本质是将来自摩托车链的旋转力矩不仅传递到后轮的可能性，而且可以转移到两个螺旋桨。 因此，螺旋桨与平衡装置一起被称为空气驱动装置（EAD）的元件可以固定在两个位置。 首先，当它们的旋转平面垂直于后轮的旋转平面（飞行模式）时。 其次，当螺旋桨（和EAD）被压到混合飞机的侧面部分（陆地模式）时。
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公开(公告)号：US20140291440A1
公开(公告)日：2014-10-02
申请号：US14357075
申请日：2012-11-09
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： The present invention discloses a vehicle (1) capable of being converted between a flying condition and an automotive riding condition. The vehicle has a telescopically extendable tail (10) comprising a first tubular tail segment (11) and a second tail segment (12) disposed axially slideable within the first tubular tail segment. The tail is provided with at least two form-closing coupling members (21, 35; 31, 36) located at an axial distance (LI) from each other for providing a force-transferring coupling between the second tail segment (12) and the first tubular tail segment (11) in the extended state of the second tail segment (12), each of said form-closing coupling members (21, 35; 31, 36) capable of transferring torque and transverse forces, and each of said form-closing coupling members (21, 35; 31, 36) coming into engagement by axial displacement of the second tail segment (12) in the outward direction.
摘要翻译： 本发明公开了一种能够在飞行状态和汽车行驶状态之间进行转换的车辆（1）。 车辆具有可伸缩地延伸的尾部（10），其包括第一管状尾部段（11）和第二尾部段（12），所述第二尾部段（12）可在第一管状尾部段内轴向滑动设置。 尾部设有至少两个位于彼此轴向距离（LI）处的形成 - 闭合联接构件（21,35; 31,36），用于在第二尾段（12）和 在第二尾段（12）的延伸状态下的第一管状尾部段（11），能够传递扭矩和横向力的每个所述成形 - 闭合联接构件（21,35; 31,36），以及每个所述形式 闭合联接构件（21,35; 31,36）通过第二尾段（12）沿向外的方向的轴向位移而接合。
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公开(公告)号：US08727271B2
公开(公告)日：2014-05-20
申请号：US11972879
申请日：2008-01-11
申请人： Ival O. Salyer
发明人： Ival O. Salyer
CPC分类号： B64D35/08 , B64C27/02 , B64C27/04 , B64C27/14 , B64C27/32 , B64D27/02 , B64D27/10 , B64D27/24 , B64D31/00 , B64D2027/026 , Y02T50/44 , Y02T50/64
摘要： An air vehicle incorporating a hybrid propulsion system. The system includes a gas turbine engine as a first motive power source, and one or more battery packs as a second motive power source. Through selective coupling to a DC electric motor that can in turn be connected to a bladed rotor or other lift-producing device, the motive sources provide differing ways in which an aircraft can operate. In one example, the gas turbine engine can provide operation for a majority of the flight envelope of the aircraft, while the battery packs can provide operation during such times when gas turbine-based motive power is unavailable or particularly disadvantageous. In another example, both sources of motive power may be decoupled from the bladed rotor such that the vehicle can operate as an autogyro.
摘要翻译： 搭载混合动力推进系统的机动车辆。 该系统包括作为第一动力源的燃气涡轮发动机和作为第二动力源的一个或多个电池组。 通过选择性地连接到直流电动机，其可以连接到叶片转子或其他提升产生装置，动力源提供飞机可以操作的不同方式。 在一个示例中，燃气涡轮发动机可以为飞行器的大部分飞行包线提供操作，而电池组可以在基于燃气轮机的动力不可用或特别不利的时间期间提供操作。 在另一示例中，动力的两个来源可以与叶片转子分离，使得车辆可以作为自动驾驶台操作。
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公开(公告)号：US20130168491A1
公开(公告)日：2013-07-04
申请号：US13544874
申请日：2012-07-09
IPC分类号： B64C27/72
摘要： A rotorcraft may include an airframe and a rotor connected to the airframe. The rotor may include a plurality of blades defining ducts along the length thereof and vents in fluid communication with the ducts. Flow from through the vents may be controlled by valves with piezoelectric actuators. The valves may be adjusted to achieve a lift profile suited for an operational mode such as vertical, autorotative, or unloaded flight. The lift profile may vary along the length of the blade and may vary cyclically with rotation of the blade. The lift profile may be chosen to approximate a figure of merit for the rotor suitable for a given operational mode.
摘要翻译： 旋翼航空器可以包括机身和连接到机身的转子。 转子可以包括沿着其长度限定管道的多个叶片和与管道流体连通的通风口。 通过通风口的流量可以由具有压电致动器的阀门控制。 可以调整阀门以实现适合于诸如垂直，自转或无负载飞行的操作模式的升力曲线。 提升轮廓可以沿着叶片的长度而变化，并且可随着叶片的旋转而周期性变化。 可以选择升力曲线以近似适于给定操作模式的转子的品质因数。
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公开(公告)号：US08366037B2
公开(公告)日：2013-02-05
申请号：US12785420
申请日：2010-05-21
CPC分类号： B64C27/02 , B64C39/024 , B64C2201/024 , B64C2201/128 , B64D3/00
摘要： An unmanned, towable aerovehicle is described and includes a container to hold cargo, an autogyro assembly connected to the container and to provide flight characteristics, and a controller to control operation the autogyro assembly for unmanned flight. The container includes a connection to connect to a powered aircraft to provide forward motive force to power the autogyro assembly. In an example, the autogyro assembly includes a mast extending from the container, a rotatable hub on an end of the mast, and a plurality of blades connected to the hub for rotation to provide lift to the vehicle. In an example, an electrical motor rotates the blades prior to lift off to assist in take off. The electrical motor does not have enough power to sustain flight of the vehicle.
摘要翻译： 描述了一种无人驾驶的可拖动的飞行器，并且包括容纳货物的容器，连接到容器并提供飞行特性的自动装配组件以及用于控制无人驾驶的自动装配组件的操作的控制器。 容器包括连接到动力飞机的连接，以提供向自动装配组件供电的向前动力。 在一个示例中，自动组件组件包括从容器延伸的桅杆，在桅杆的端部上的可旋转轮毂，以及连接到轮毂以便旋转以提供车辆升力的多个叶片。 在一个示例中，电动马达在升降之前旋转叶片以帮助起飞。 电动机没有足够的电力来维持车辆的飞行。
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