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公开(公告)号：US07918415B2
公开(公告)日：2011-04-05
申请号：US10598592
申请日：2005-02-28
摘要： The invention relates to a convertible aircraft operating method. According to the invention, the aircraft comprises: a fuselage, standard fixed wings which are equipped with ailerons, a tail unit with flight-control surfaces, engines, a rotor with blades, a transmission which is placed between the engines and the rotor and which is equipped with rotor clutch and braking means, a landing gear, means for transition from helicopter mode to autogyro mode and vice versa, and means for direct or reverse transition from autogyro/helicopter mode to aeroplane mode. The lift for a range of low speeds is produced by means of the rotor, while the lift for a range of high speeds is produced by means of the wings. In addition, the lift for a range of intermediate speeds can be produced using the wings and the rotor in autogyro mode simultaneously, and take-off and landing can be performed in autogyro mode or in helicopter mode with the engines coupled to the rotor. The aircraft comprises a hybrid helicopter/autogyro/aeroplane aircraft and, as such, can perform the direct or reverse transition to aeroplane mode from both helicopter mode and autogyro mode.
摘要翻译： 本发明涉及一种可转换飞机的操作方法。 根据本发明，飞机包括：机身，配备有副翼的标准固定翼，具有飞行控制表面的尾翼单元，发动机，具有叶片的转子，位于发动机和转子之间的变速器， 配有转子离合器和制动装置，起落架，用于从直升机模式转换到自动模式的装置，反之亦然，以及用于从自动/直升机模式直接或反向过渡到飞行模式的装置。 通过转子产生一系列低速的升降机，而通过机翼产生一系列高速的升降机。 此外，可以同时使用机翼和转子以自动驾驶模式生产一系列中速的升降机，并且起飞和着陆可以在自动驾驶模式或直升机模式下执行，其中发动机联接到转子。 飞机包括混合直升机/自动飞机/飞机飞机，因此，可以直升机模式和自动驾驶模式直接或反向转换飞机模式。
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公开(公告)号：US07837141B2
公开(公告)日：2010-11-23
申请号：US11387189
申请日：2006-03-22
IPC分类号： B64C27/24 , B05B1/26 , B64C27/615
摘要： In an exemplary variable area nozzle, a fixed duct section has an inlet and an outlet oriented approximately perpendicular to the inlet. A controllable nozzle member is disposed adjacent the outlet of the fixed duct section. The controllable nozzle member has an area that is adjustable to maintain a substantially constant nozzle pressure ratio. The controllable nozzle member may include first and second flap doors hinged and pivotable in opposite directions between an open position and a closed position and that also may be hinged and pivotable in a same direction so thrust from gas exiting the nozzle is vectorable. When disposed in rotor tips of an aircraft capable of rotary wing flight and fixed wing flight, the variable area nozzle may maintain a substantially constant nozzle pressure ratio near an optimized nozzle pressure ratio as the aircraft transitions from rotary wing flight to fixed wing flight.
摘要翻译： 在示例性可变区域喷嘴中，固定管道部分具有大致垂直于入口定向的入口和出口。 可控喷嘴构件邻近固定管段的出口设置。 可控喷嘴构件具有可调节的区域，以保持基本恒定的喷嘴压力比。 可控喷嘴构件可以包括在打开位置和关闭位置之间以相反方向铰接和枢转的第一和第二折翼门，并且也可以在相同方向上铰接和枢转，从而从喷嘴排出的气体的推力是可向量的。 当设置在能够旋转翼飞行和固定翼飞行的飞行器的转子尖端时，随着飞机从旋翼飞行转变到固定翼飞行，可变区喷嘴可以在最佳喷嘴压力比附近保持基本恒定的喷嘴压力比。
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公开(公告)号：US20070095970A1
公开(公告)日：2007-05-03
申请号：US11265655
申请日：2005-11-02
申请人： Steven Richardson
发明人： Steven Richardson
摘要： Aircraft including an airframe having a fuselage extending between a forward end and an aft end and a fixed wing extending laterally from the fuselage. The aircraft includes a power plant mounted on the airframe producing exhaust during operation. The aircraft includes a rotor/wing rotatably mounted on the airframe including a plurality of blades and an adjustable nozzle mounted on the airframe downstream from the power plant exhaust for selectively directing the power plant exhaust to exit the aircraft at a pre-selected angle with respect to the airframe within a range of angles extending from about horizontally rearward to about vertically downward.
摘要翻译： 飞机包括具有在前端和后端之间延伸的机身的机身和从机身横向延伸的固定翼。 飞机包括安装在机身上的发电厂，在运行期间产生排气。 飞行器包括可旋转地安装在机身上的转子/机翼，其包括多个叶片和安装在发电厂排气下游的机身上的可调节喷嘴，用于选择性地引导发电厂排气以相对于预定角度离开飞行器 在从大约水平向后延伸到大约垂直向下的角度范围内的机身上。
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公开(公告)号：US5951608A
公开(公告)日：1999-09-14
申请号：US873504
申请日：1997-06-12
申请人： Stephen S. Osder
发明人： Stephen S. Osder
CPC分类号： G05D1/0858 , B64C27/18 , B64C27/24 , B64C39/12
摘要： The disclosed flight control system includes a rotor blade speed monitor for monitoring the rotor blade speed of the jet powered tri-mode aircraft and for outputting a rotor blade speed command. The flight control system also includes an aircraft attitude controller for controlling the aircraft attitude of the jet powered tri-mode aircraft. Weighted rotor blade attitude stabilization commands and weighted aero surface attitude stabilization commands are output from the aircraft attitude controller to distribute power, control, and lift between the rotor blade and the aero surfaces. Relative weights of the weighted rotor blade attitude stabilization commands decrease with increasing aircraft travelling velocities, and relative weights of the weighted aero surface attitude stabilization commands increase with increasing velocities. A rotor blade lift controller receives the weighted rotor blade attitude stabilization commands and the rotor blade speed commands, and positions the rotor blade swashplate to adjust lift and control according to these commands. An aero lift controller receives the weighted aero surface attitude stabilization commands and deploys the aero surfaces to generate lift and control according to the received weighted aero surface attitude stabilization commands.
摘要翻译： 所公开的飞行控制系统包括用于监测喷射式三模飞行器的转子叶片速度并用于输出转子叶片速度命令的转子叶片速度监视器。 飞行控制系统还包括用于控制喷气动力三模飞行器的飞行器姿态的飞行器姿态控制器。 从飞机姿态控制器输出加权转子叶片姿态稳定命令和加权航空表面姿态稳定命令，以分配转子叶片和航空表面之间的动力，控制和升力。 加权转子叶片姿态稳定指令的相对权重随着飞行器行进速度的增加而减小，加权航空表面姿态稳定指令的相对权重随着速度的增加而增加。 转子叶片提升控制器接收加权的转子叶片姿态稳定命令和转子叶片速度命令，并且定位转子叶片斜盘以根据这些命令调节升程和控制。 航空提升控制器接收加权的航空表面姿态稳定命令并且部署航空表面以根据所接收的加权航空表面姿态稳定命令产生升力和控制。
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公开(公告)号：US2780423A
公开(公告)日：1957-02-05
申请号：US32647452
申请日：1952-12-17
申请人： DE CENZO HERBERT A
发明人： DE CENZO HERBERT A
IPC分类号： B64C27/24
CPC分类号： B64C27/24
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公开(公告)号：US20220363374A1
公开(公告)日：2022-11-17
申请号：US17767054
申请日：2019-10-08
摘要： To provide an aerial vehicle that can improve the driving feel and riding comfort of a rider. An aerial vehicle according to the present technology includes: a vehicle body extending in the front-rear direction; a saddle section provided on an upper side of the vehicle body; a motive power section provided on an underside of the vehicle body, at a position below the saddle section; and a rotary wing section which is provided at at least one of the front and rear of the motive power section, and which rotates by using the motive power section as a motive power source.
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公开(公告)号：US20200010185A1
公开(公告)日：2020-01-09
申请号：US16460465
申请日：2019-07-02
发明人： Stefan Bender
摘要： An aircraft has an emergency rotor, and the emergency rotor can be deployed from a rest position into a use position.
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公开(公告)号：US20170283048A1
公开(公告)日：2017-10-05
申请号：US15083758
申请日：2016-03-29
发明人： Brian C. Beckman , Noam Sorek
摘要： Described is a configuration of an unmanned aerial vehicle (“UAV”) that includes one or more lifting propellers that may be converted between an operational configuration and a transit configuration. When the lifting propeller is in a operational configuration, the leading edge of each propeller blade is aligned in the direction of rotation so that the lifting propeller will generate a positive lifting force when rotated by a lifting motor. When the lifting propeller is in the transit configuration, the leading edge of each of the propeller blades are oriented toward a direction of a transit flight of the aerial vehicle. Likewise, the lifting propeller is maintained in a fixed position during the transit flight so that airflow passing over the propeller blades of the lifting propeller cause vertical lift.
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公开(公告)号：US20170217577A1
公开(公告)日：2017-08-03
申请号：US15424658
申请日：2017-02-03
申请人： Hattar Tanin LLC
发明人： Saadeh HATTAR , Volodymyr Tanin
摘要： The disclosure provides a hybrid aircraft capable of being propelled by a vertical rotor(s) or a horizontal engine(s). The aircraft includes a fuselage defining a horizontal plane, two wings attached to opposite sides of fuselage and oriented substantially parallel to the horizontal plane, an engine(s) configured to generate propulsion in a horizontal direction, and a rotor(s) extending vertically from the fuselage and oriented over a first portion of each wing. Each wing includes a wing frame and an aircraft skin covering at least a portion of the wing frame. When the aircraft is being propelled by the rotor, the aircraft skin covering the first portion of each wing frame is removed or rotated to facilitate airflow through the rotors. When the aircraft is being propelled by the one or more horizontal engines, the aircraft skin may cover the first portion of the wing frame, facilitating aerodynamic lift and stability.
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公开(公告)号：US09540103B2
公开(公告)日：2017-01-10
申请号：US14313680
申请日：2014-06-24
发明人： Geoffrey A. Long
CPC分类号： B64C39/024 , B64C27/24 , B64C27/32 , B64C2201/102 , B64C2201/108
摘要： A vertical takeoff and landing aircraft includes rotors that provide vertical and horizontal thrust. During forward motion, the vertical lift system is inactive. A lift fan mechanism positions the fan blades of the aircraft in a collapsed configuration when the vertical lift system is inactive and positions the fan blades of the aircraft in a deployed configuration when the vertical lift system is active.
摘要翻译： 垂直起降飞机包括提供垂直和水平推力的转子。 在向前运动期间，垂直升降系统不起作用。 当垂直升降系统处于非活动状态时，升降风扇机构将飞行器的风扇叶片定位在折叠构型中，并且当垂直升降系统处于活动状态时将飞行器的风扇叶片定位在展开配置中。
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