-
公开(公告)号：EP0861779A1
公开(公告)日：1998-09-02
申请号：EP97118352.0
申请日：1993-06-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： KRAUSS, Albert T. , HUNTER, David H., , BEATTY, Robert D.,
CPC classification number: B64C27/10 , B64C27/14 , B64C27/20 , B64C27/33 , B64C27/605 , B64C39/024 , B64C2201/027 , B64C2201/044 , B64C2201/108 , B64C2201/127 , B64C2201/146 , B64C2201/162 , F02B2075/025 , F16D3/06 , F16D3/185
Abstract: A rotor blade subassembly (250) for an unmanned aerial vehicle (10) that includes a rotor assembly (100) having ducted, coaxial counter-rotating rotors (200, 202), the rotor assembly (100) including a rotor hub (204), comprising:
flexbeam means (260) configured for reacting centrifugal and bending loads of one of the ducted, coaxial counter-rotating rotors (200 or 202), said flexbeam means (260) having an inboard end (262) and an outboard end (264), said inboard end (262) being configured for securing said flexbeam means (260) in combination with the rotor hub (204);
spar means (274) for reacting bending, torsional, shear, and centrifugal loads of the one ducted, coaxial counter-rotating rotor (200 or 202), said spar means (274) functioning as a primary structural member of said rotor blade subassembly (250);
torque tube means (272) for reacting torsional and bending loads of the one ducted, coaxial counter-rotating rotor (200 or 202); and
a rotor blade (280);
said rotor blade (280), said torque tube means (272), said spar means (274), and said flexbeam means (260) being secured in combination at said outboard end (264) of said flexbeam means (260);
characterized in that said flexbeam means (260) has a predetermined linear twist along the span thereof from said inboard end (262) to said outboard end (264).-
公开(公告)号：EP0861776A1
公开(公告)日：1998-09-02
申请号：EP97118254.8
申请日：1993-06-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Hanson, Bruce D. , Kohlhepp, Frederick W. , Millea, Vincent F. , Cycon, James P.
CPC classification number: B64C27/10 , B64C27/14 , B64C27/20 , B64C27/33 , B64C27/605 , B64C39/024 , B64C2201/027 , B64C2201/044 , B64C2201/108 , B64C2201/127 , B64C2201/146 , B64C2201/162 , F02B2075/025 , F16D3/06 , F16D3/185
Abstract: A drive train assembly (60) for an unmanned aerial vehicle (10) for coupling torque from an engine (54) to a transmission (110) of a rotor assembly (100) having ducted, coaxial counter-rotating rotors (200, 202), comprising:
an engine coupling subassembly (63);
a drive shaft (72); and
a transmission coupling subassembly (74);
said transmission coupling subassembly (74) including an external crown spline coupling (76) mechanically connected to one end of said drive shaft (72) by means of a pin-collar connector (75), and a gear spline coupling (77) in meshing engagement with said external spline coupling (76);
said engine coupling subassembly (63) including an internal spline coupling (68) mechanically connected to the other end of said drive shaft (72) by means of a pin-collar connector (69), and an external crown spline coupling (67) in meshing engagement with said internal spline coupling (68) through complementary spline teeth (67T, 68T);
characterized in that
said engine coupling subassembly (63) further includes a bundt pan (65) that transmits torque from the engine (54), a sprag clutch (62) and ball bearings (66);
said sprag clutch (62) being rigidly centered intermediate said bundt pan (65) and said external crown spline coupling (67) by means of said ball bearings (66);
wherein torque from the bundt pan (65) is coupled through the sprag clutch (62) to the external crown spline coupling (67), which in turn couples the torque to the drive shaft (72) via said internal spline coupling (67) due to the meshing between the complementary spline teeth (67T, 68T) of said internal spline coupling (67) and said external crown spline coupling (68).-
433.发明授权
公开(公告)号：EP0646084B1
公开(公告)日：1998-05-20
申请号：EP93915385.4
申请日：1993-06-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： CYCON, James, P. , HUNTER, David, H. , KOHLHEPP, Fred, W. , KRAUSS, Timothy, A. , MILLEA, Vincent, F. , FURNES, Kenneth, M. , FARRRELL, Marvin, D. , SANDY, David, F. , BEATTY, Robert, D. , HANSEN, Bruce, D.
CPC classification number: B64C27/10 , B64C27/14 , B64C27/20 , B64C27/33 , B64C27/605 , B64C39/024 , B64C2201/027 , B64C2201/044 , B64C2201/108 , B64C2201/127 , B64C2201/146 , B64C2201/162 , F02B2075/025 , F16D3/06 , F16D3/185
-
公开(公告)号：EP0148968B1
公开(公告)日：1988-01-13
申请号：EP84100428.6
申请日：1984-01-17
Applicant: DORNIER GMBH
Inventor： Frühauf, Werner, Ing. grad.
CPC classification number: B64C39/024 , B64C2201/028 , B64C2201/044 , B64C2201/165 , B64C2201/201 , B64D37/00
-
公开(公告)号：EP0167625A1
公开(公告)日：1986-01-15
申请号：EP83903825.4
申请日：1983-12-02
Applicant: IZUTSUYA, Kiyonobu
Inventor： IZUTSUYA, Kiyonobu
IPC: A63H27/12
CPC classification number: F02B75/243 , B64C27/06 , B64C27/12 , B64C39/024 , B64C2201/024 , B64C2201/044 , B64C2201/108 , B64C2201/126 , B64C2201/127 , B64C2201/146 , F02B75/34
Abstract: A small, radio-controlled helicopter with an internal- combustion engine with two opposed, simultaneous-ignition cylinders to reduce ignition vibrations applied to the helicopter body. Thus, when this small helicopter is equipped with apparatus for video recording or photography, it is possible to obtain clear picture images while preventing any unwanted movement of the camera. In addition, various other operations, such as the spreading of pharmaceuticals and the guiding of lead ropes, can be conducted stably.
Abstract translation: 小型无线电控制的直升机，带有内燃机和两个相对的同步点火气缸，以减少施加在直升机机身上的点火振动。 因此，当该小型直升机配备有用于视频记录或摄影的装置时，可以获得清晰的图像，同时防止摄像机的任何不需要的移动。 另外，可以稳定地进行各种其他操作，例如药物的传播和引导绳的引导。
-
Patent Agency Ranking
公开(公告)号：EP0148968A1
公开(公告)日：1985-07-24
申请号：EP84100428.6
申请日：1984-01-17
Applicant: DORNIER GMBH
Inventor： Frühauf, Werner, Ing. grad.
CPC classification number: B64C39/024 , B64C2201/028 , B64C2201/044 , B64C2201/165 , B64C2201/201 , B64D37/00
Abstract: Flugkörper mit stark gepfeiltem Tragwerk, ausgehend von einem Tragwerk (4) der angegebenen Art in Verbindung mit Aufnahme- bzw. Startbehältern (1') in gestapelter Anordnung, sowie ausgehend von der Forderung, die Flugkörper ohne Kraftstoff in den Behältern zu lagern bzw. zu transportieren. Die Kraftstoffbehälter für die Antriebsanlage des Flugkörpers sind von vorn in Räume des Tragwerks einsetzbar und durch Arretierung verriegelbar.
Abstract translation: 1.从装有电池的集装箱发射的飞机，包含具有燃料箱（14）的推进装置，燃料箱（14）形成结构部件，其可与翼单元（4）组装并支撑翼部以及燃料供给装置（34）和 特别是飞机，翼翼单元以三角翼的形式以明显的方式扫掠，其特征在于 - 翼单元（4）设置在前翼梁（8）和肋（9,9'）之间， 其在所述翼根部（6）的区域中彼此相邻，具有接收空间（12），所述接收空间（12）可从所述机翼鼻部（10）接近以用于容纳预充式燃料箱（14），所述相互作用的引导部件（16; 17） 设置在彼此相邻的肋（9,9'）和翼（4）的前翼梁（8）和燃料箱（14）之间，并且 - 用于将罐（14）自动锁定在 它们的最终滑入位置或通过可释放的锁定装置（29,30,32）将翼片从机翼鼻部（10）释放出来 ia操作设备（38）。
-
公开(公告)号：EP0112448A1
公开(公告)日：1984-07-04
申请号：EP83110151.4
申请日：1983-10-12
Applicant: DORNIER GMBH
Inventor： Friedel, Franz , Frühauf, Werner , Harms, Günter , Heise, Georg, Dipl.-Ing. , Lükewille, Heinrich, Dipl.-Ing.
CPC classification number: F42B10/64 , B64C39/024 , B64C2201/028 , B64C2201/044 , B64C2201/165 , B64C2201/201 , F16D7/021 , F42B15/105
Abstract: Unbemannter Flugkörper mit stark gepfeiltem Tragwerk, insbesondere Deltaflügeln, der in einem Behälter transportiert und aus dem Behälter mittels eines Hilfsantriebs nach Lösung einer Arretierung gestartet wird und der während des Marschfluges durch ein Propellertriebwerk antreibbar ist, wobei Seitenkraftflächen (25) zur Stabilisierung des Flugkörpers während des Marschfluges aus Einfahrräumen (26) im Bereich der Flügelwurzel der Deltaflügel ausfahrbar sind und ferner eine Reibschlußkupplung (64, 65) am Flugkörper vorgesehen ist, die ohne Zuführung von Energie von aussen den stillstehenden Propeller (6) mit dem im Behälter laufenden Antriebsmotor (7) nach Verlassen des Behälters kuppelt.
Abstract translation: 用强掠支撑结构，特别是三角翼，其在一个容器的锁定机构释放之后输送并从容器推出的辅助驱动装置和无人导弹是由螺旋桨发动机巡航飞行期间驱动，所述侧向力面（25），以在稳定的导弹 从Einfahrraumen MARSCH飞行（26）是在机翼根部区域伸展，三角翼，并且还包括摩擦离合器（64，65）被设置在导弹，这没有能量从静止螺旋桨（6）与所述罐箱驱动电动机的电流以外的电源（7） 离开容器后脱离。
-
公开(公告)号：WO2018148636A1
公开(公告)日：2018-08-16
申请号：PCT/US2018/017776
申请日：2018-02-12
Applicant: TOP FLIGHT TECHNOLOGIES, INC. , PHAN, Long N.
Inventor： PHAN, Long N.
CPC classification number: B64C39/024 , B64C27/12 , B64C2201/027 , B64C2201/042 , B64C2201/044 , B64C2201/108 , B64C2201/125 , B64C2201/127 , B64C2201/141 , B64C2201/162 , B64C2201/165 , B64C2201/208 , B64D2027/026 , G01W1/02 , G01W1/08 , G08G5/0069 , G08G5/0091
Abstract: An unmanned aerial vehicle includes an atmospheric sensor configured to measure an atmospheric condition. The unmanned aerial vehicle includes a rotor motor configured to drive rotation of a propeller of the unmanned aerial vehicle. The unmanned aerial vehicle includes a hybrid energy generation system including a rechargeable battery configured to provide electrical energy to the rotor motor; an engine configured to generate mechanical energy; and a generator coupled to the engine and configured to generate electrical energy from the mechanical energy generated by the engine, the electrical energy generated by the generator being provided to at least one of the rechargeable battery and the rotor motor.
-
439.发明申请AN INTERNAL COMBUSTION ENGINE POWERED MULTI-ROTOR AIRCRAFT AND METHODS OF CONTROL THEREOF 审中-公开内燃机发动机多转子飞机及其控制方法
公开(公告)号：WO2016179667A1
公开(公告)日：2016-11-17
申请号：PCT/AU2016/050367
申请日：2016-05-14
Applicant: SAARIO, Seppo
Inventor： SAARIO, Seppo
IPC: B64C27/08
CPC classification number: B64C39/024 , B64C2201/027 , B64C2201/044 , B64C2201/108
Abstract: There is provided a multirotor aircraft comprising a platform; and at least two pairs of opposing radial arms extending from the platform, the radial arms supporting at least four internal combustion engine powered rotors, rotating actuators for rotating each of the radial arms about an elongate axis; and a flight controller configured for controlling the rotating actuators, wherein the rotors rotate in the same direction; and the flight controller is configured for yaw control by controlling the rotating actuators to rotate at least one pair of the opposing radial arms in opposing rotational directions.
Abstract translation: 提供了一种包括平台的多转轮飞机; 以及至少两对相对的径向臂，其从所述平台延伸，所述径向臂支撑至少四个内燃机动力转子，所述旋转致动器用于使所述径向臂中的每一个围绕细长轴旋转; 以及飞行控制器，其构造成用于控制所述旋转致动器，其中所述转子沿相同的方向旋转; 并且飞行控制器被配置为通过控制旋转致动器以相反的旋转方向旋转至少一对相对的径向臂来进行偏航控制。
-
公开(公告)号：WO2016081041A1
公开(公告)日：2016-05-26
申请号：PCT/US2015/047620
申请日：2015-08-29
Applicant: REFERENCE TECHNOLOGIES INC.
Inventor： BISHOP, Allen
IPC: B64C27/20
CPC classification number: B64C39/024 , B64C27/20 , B64C27/82 , B64C29/04 , B64C2027/8227 , B64C2201/027 , B64C2201/042 , B64C2201/044 , B64C2201/108 , B64D2027/026
Abstract: A propulsion system for a ducted fan vertical takeoff and landing aircraft (VTOL) powered by multiple electric motors with two, counter rotating electric motors comprising the primary thrust generation within a ducted fan component and 3 or more external electric motors providing lift, stability and directional control of the aircraft. Through the use of counter rotating ducted fans, the aircraft does not require the need for internal stators - either fixed or adjustable angle. Power to the electric motors is sourced by either onboard batteries, a ground based power source via a ground to aircraft tether, or an on board fuel cell or combustion engine driving an alternator.
Abstract translation: 一种用于由具有两个反向旋转电动机的多个电动机驱动的管道风扇垂直起降飞机（VTOL）的推进系统，其包括在管道风扇部件内的主要推力产生和提供升力，稳定性和定向的3个或更多个外部电动马达 控制飞机。 通过使用反向旋转管道风扇，飞机不需要内部定子 - 固定或可调角度。 对电动机的电力来自车载电池，地面电源通过地面到飞机系绳，或车载燃料电池或驱动交流发电机的内燃机。
-
-
-
-
-
-
-
-
-
Search Results
456
records
(took 0.024 seconds)
