公开(公告)号：WO9400347A2

公开(公告)日：1994-01-06

申请号：PCT/US9305797

申请日：1993-06-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYPON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FURNES KENNETH M ,  FARRELL MARVIN D ,  SANDY DAVID F ,  BEATTY ROBERT D ,  HANSEN BRUCE D

IPC: B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/20 ,  B64C27/33 ,  B64C27/46 ,  B64C27/473 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  F02B75/02 ,  F16C11/06 ,  F16D1/02 ,  F16D1/05 ,  F16D1/06 ,  F16D3/06 ,  F16D3/18 ,  F16D41/07 ,  F16F15/10 ,  F16H1/14 ,  F16H1/22

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: An unmanned aerial vehicle (UAV) (10) has a composite toroidal fuselage structure (20) that surrounds a rotor assembly (100) that includes pair of coaxial, multi-bladed, counter-rotating rotors (200, 202). The toroidal fuselage structure (20) includes an annular C-shaped structure (430) that defines an internal cavity (436) and removable panel structures (464) mounted in combination with the annular C-shaped structure (430). The UAV has a drive train assembly (60) that includes a sprag clutch (62), an engine coupling subassembly (63), a transmission coupling subassembly (74), and a drive shaft (72) operative to couple torque between the UAV engine (54) and the rotor assembly (100) and configured to maximize allowable axial, angular, and/or parallel misalignments therebetween. The UAV further includes a coaxial transmission/center hub assembly (110), an integrated spline/cone seat subassembly (190), rotor blade subassemblies including pretwisted inner flexbeams (260), and snubber assemblies (230).

Abstract translation: 无人飞行器（UAV）（10）具有围绕转子组件（100）的复合环形机身结构（20），转子组件（100）包括一对同轴，多叶片的反向旋转转子（200,202）。 环形机身结构（20）包括环形C形结构（430），其限定与环形C形结构（430）组合安装的内部空腔（436）和可移除的面板结构（464）。 该无人机具有一个传动系组件（60），它包括一个起落架离合器（62），一个发动机联接子组件（63），一个变速器联接子组件（74）和一个驱动轴（72） （54）和转子组件（100），并且构造成使其间允许的轴向，角度和/或平行不对准最大化。 无人机还包括同轴传动/中心轮毂组件（110），集成的花键/锥座组件（190），包括预扭曲的内柔性梁（260）和缓冲组件（230）的转子叶片子组件。

公开(公告)号：AU1018195A

公开(公告)日：1995-03-09

申请号：AU1018195

申请日：1995-01-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYPON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FURNES KENNETH M ,  FARRELL MARVIN D ,  SANDY DAVID F ,  BEATTY ROBERT D ,  HANSEN BRUCE D

IPC: B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/20 ,  B64C27/33 ,  B64C27/46 ,  B64C27/473 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  F02B75/02 ,  F16C11/06 ,  F16D1/02 ,  F16D1/05 ,  F16D1/06 ,  F16D3/06 ,  F16D3/18 ,  F16D41/07 ,  F16F15/10 ,  F16H1/14 ,  F16H1/22 ,  B64C27/52 ,  B64C11/04

Abstract: An integrated spline/cone seat subassembly (190) for an unmanned aerial vehicle (10) having a rotor assembly (100) that includes ducted, counter-rotating rotors (200, 202), comprising:a rotor shaft (128R or 130R) having an axis, said rotor shaft (128R or 130R) includinga primary shaft portion (192) having a first diameter (D 1 ),an end shaft portion (194) having a second diameter (D 2 ) and having a plurality of shaft splines (198) extending radially outwardly therefrom, anda conic transition portion (196) intermediate said primary and end shaft portions (192, 194), said conic transition portion (196) making a predetermined angle (β) with respect to said axis of said rotor shaft (128R or 130R); anda rotor hub (204) having a centerline (212), said rotor hub (204) having a shaft aperture (206) having a plurality of hub splines (208) extending radially inwardly therefrom;said plurality of hub splines (208) and said plurality of shaft splines (198) being interleaved in combination to provide a rotational interlock between said rotor hub (204) and said rotor shaft (128R or 130R) in the rotor assembly (100);   characterized in thateach of said hub splines (208) having an outwardly tapered lower portion (210) that makes a predetermined angle (θ) with respect to said centerline (212); andsaid predetermined angle (θ) of said outwardly tapered lower portions (210) of said hub splines (208) being equal to said predetermined angle (β) of said conic transition portion (196) of said rotor shaft (128R or 130R) wherein said tapered lower portions (210) of said hub splines (208) abuttingly engage and are mechanically supported by said conic transition portion (196) of said rotor shaft (128R or 130R) in the rotor assembly (100).

公开(公告)号：RU2113378C1

公开(公告)日：1998-06-20

申请号：RU95106358

申请日：1993-06-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYPON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FURNES KENNETH M ,  FARRELL MARVIN D ,  SANDY DAVID F ,  BEATTY ROBERT D ,  HANSEN BRUCE D

IPC: B64C11/02 ,  B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C39/02 ,  F02B75/02

Abstract: FIELD: aircraft manufacture; designing of combined bearing subunits for unmanned flying vehicles. SUBSTANCE: combined subunit includes upper or lower main rotors and bush embracing the respective shaft and coaxial with it; end portion of shaft and surface of bush embracing it are provided with many radial splines which are external splines for shaft and inner splines for bush; splines of shaft and bush are mutually alternating providing for engagement between shaft and bush for setting it in rotation. Main rotor shaft is provided with main and end cylindrical parts of different diameter: D1 and D2 with taper adapter portion formed between them at angle of inclination beta of surface relative to shaft axis. According to invention, each spline of bush has lower portion bevelled outside forming angle theta relative to axis of bush which is equal to angle beta of taper adapter portion of shaft of main rotor. Bush rests on taper adapter portion of respective shaft by its bevelled lower portions of splines. Distance D3 of such combined subunit between edges of splines of main rotor shaft may be equal to diameter Dl of its main portion in diametral plane. EFFECT: optimization of construction of subunit. 2 cl, 32 dwg.

公开(公告)号：AU664144B2

公开(公告)日：1995-11-02

申请号：AU1017995

申请日：1995-01-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYPON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FURNES KENNETH M ,  FARRELL MARVIN D ,  SANDY DAVID F ,  BEATTY ROBERT D ,  HANSEN BRUCE D

IPC: B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/20 ,  B64C27/33 ,  B64C27/46 ,  B64C27/473 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  F02B75/02 ,  F16C11/06 ,  F16D1/02 ,  F16D1/05 ,  F16D1/06 ,  F16D3/06 ,  F16D3/18 ,  F16D41/07 ,  F16F15/10 ,  F16H1/14 ,  F16H1/22 ,  B64C11/02 ,  B64C27/32 ,  B64D35/06

公开(公告)号：AU4538593A

公开(公告)日：1994-01-24

申请号：AU4538593

申请日：1993-06-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYPON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FURNES KENNETH M ,  FARRELL MARVIN D ,  SANDY DAVID F ,  BEATTY ROBERT D ,  HANSEN BRUCE D

IPC: B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/20 ,  B64C27/33 ,  B64C27/46 ,  B64C27/473 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  F02B75/02 ,  F16C11/06 ,  F16D1/02 ,  F16D1/05 ,  F16D1/06 ,  F16D3/06 ,  F16D3/18 ,  F16D41/07 ,  F16F15/10 ,  F16H1/14 ,  F16H1/22

Abstract: An integrated spline/cone seat subassembly (190) for an unmanned aerial vehicle (10) having a rotor assembly (100) that includes ducted, counter-rotating rotors (200, 202), comprising:a rotor shaft (128R or 130R) having an axis, said rotor shaft (128R or 130R) includinga primary shaft portion (192) having a first diameter (D 1 ),an end shaft portion (194) having a second diameter (D 2 ) and having a plurality of shaft splines (198) extending radially outwardly therefrom, anda conic transition portion (196) intermediate said primary and end shaft portions (192, 194), said conic transition portion (196) making a predetermined angle (β) with respect to said axis of said rotor shaft (128R or 130R); anda rotor hub (204) having a centerline (212), said rotor hub (204) having a shaft aperture (206) having a plurality of hub splines (208) extending radially inwardly therefrom;said plurality of hub splines (208) and said plurality of shaft splines (198) being interleaved in combination to provide a rotational interlock between said rotor hub (204) and said rotor shaft (128R or 130R) in the rotor assembly (100);   characterized in thateach of said hub splines (208) having an outwardly tapered lower portion (210) that makes a predetermined angle (θ) with respect to said centerline (212); andsaid predetermined angle (θ) of said outwardly tapered lower portions (210) of said hub splines (208) being equal to said predetermined angle (β) of said conic transition portion (196) of said rotor shaft (128R or 130R) wherein said tapered lower portions (210) of said hub splines (208) abuttingly engage and are mechanically supported by said conic transition portion (196) of said rotor shaft (128R or 130R) in the rotor assembly (100).

公开(公告)号：DE69318713D1

公开(公告)日：1998-06-25

申请号：DE69318713

申请日：1993-06-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYPON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FURNES KENNETH M ,  FARRELL MARVIN D ,  SANDY DAVID F ,  BEATTY ROBERT D ,  HANSEN BRUCE D

IPC: B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/20 ,  B64C27/33 ,  B64C27/46 ,  B64C27/473 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  F02B75/02 ,  F16C11/06 ,  F16D1/02 ,  F16D1/05 ,  F16D1/06 ,  F16D3/06 ,  F16D3/18 ,  F16D41/07 ,  F16F15/10 ,  F16H1/14 ,  F16H1/22

公开(公告)号：AU667650B2

公开(公告)日：1996-03-28

申请号：AU1017895

申请日：1995-01-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYPON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FURNES KENNETH M ,  FARRELL MARVIN D ,  SANDY DAVID F ,  BEATTY ROBERT D ,  HANSEN BRUCE D

IPC: B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/20 ,  B64C27/33 ,  B64C27/46 ,  B64C27/473 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  F02B75/02 ,  F16C11/06 ,  F16D1/02 ,  F16D1/05 ,  F16D1/06 ,  F16D3/06 ,  F16D3/18 ,  F16D41/07 ,  F16F15/10 ,  F16H1/14 ,  F16H1/22 ,  B64D35/06

公开(公告)号：AU1018095A

公开(公告)日：1995-03-09

申请号：AU1018095

申请日：1995-01-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYPON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FURNES KENNETH M ,  FARRELL MARVIN D ,  SANDY DAVID F ,  BEATTY ROBERT D ,  HANSEN BRUCE D

IPC: B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/20 ,  B64C27/33 ,  B64C27/46 ,  B64C27/473 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  F02B75/02 ,  F16C11/06 ,  F16D1/02 ,  F16D1/05 ,  F16D1/06 ,  F16D3/06 ,  F16D3/18 ,  F16D41/07 ,  F16F15/10 ,  F16H1/14 ,  F16H1/22 ,  B64D35/06 ,  B64C27/32

Abstract: An integrated spline/cone seat subassembly (190) for an unmanned aerial vehicle (10) having a rotor assembly (100) that includes ducted, counter-rotating rotors (200, 202), comprising:a rotor shaft (128R or 130R) having an axis, said rotor shaft (128R or 130R) includinga primary shaft portion (192) having a first diameter (D 1 ),an end shaft portion (194) having a second diameter (D 2 ) and having a plurality of shaft splines (198) extending radially outwardly therefrom, anda conic transition portion (196) intermediate said primary and end shaft portions (192, 194), said conic transition portion (196) making a predetermined angle (β) with respect to said axis of said rotor shaft (128R or 130R); anda rotor hub (204) having a centerline (212), said rotor hub (204) having a shaft aperture (206) having a plurality of hub splines (208) extending radially inwardly therefrom;said plurality of hub splines (208) and said plurality of shaft splines (198) being interleaved in combination to provide a rotational interlock between said rotor hub (204) and said rotor shaft (128R or 130R) in the rotor assembly (100);   characterized in thateach of said hub splines (208) having an outwardly tapered lower portion (210) that makes a predetermined angle (θ) with respect to said centerline (212); andsaid predetermined angle (θ) of said outwardly tapered lower portions (210) of said hub splines (208) being equal to said predetermined angle (β) of said conic transition portion (196) of said rotor shaft (128R or 130R) wherein said tapered lower portions (210) of said hub splines (208) abuttingly engage and are mechanically supported by said conic transition portion (196) of said rotor shaft (128R or 130R) in the rotor assembly (100).

公开(公告)号：AU1017995A

公开(公告)日：1995-03-09

申请号：AU1017995

申请日：1995-01-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYPON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FURNES KENNETH M ,  FARRELL MARVIN D ,  SANDY DAVID F ,  BEATTY ROBERT D ,  HANSEN BRUCE D

IPC: B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/20 ,  B64C27/33 ,  B64C27/46 ,  B64C27/473 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  F02B75/02 ,  F16C11/06 ,  F16D1/02 ,  F16D1/05 ,  F16D1/06 ,  F16D3/06 ,  F16D3/18 ,  F16D41/07 ,  F16F15/10 ,  F16H1/14 ,  F16H1/22 ,  B64C11/02 ,  B64C27/32 ,  B64D35/06

Abstract: An integrated spline/cone seat subassembly (190) for an unmanned aerial vehicle (10) having a rotor assembly (100) that includes ducted, counter-rotating rotors (200, 202), comprising:a rotor shaft (128R or 130R) having an axis, said rotor shaft (128R or 130R) includinga primary shaft portion (192) having a first diameter (D 1 ),an end shaft portion (194) having a second diameter (D 2 ) and having a plurality of shaft splines (198) extending radially outwardly therefrom, anda conic transition portion (196) intermediate said primary and end shaft portions (192, 194), said conic transition portion (196) making a predetermined angle (β) with respect to said axis of said rotor shaft (128R or 130R); anda rotor hub (204) having a centerline (212), said rotor hub (204) having a shaft aperture (206) having a plurality of hub splines (208) extending radially inwardly therefrom;said plurality of hub splines (208) and said plurality of shaft splines (198) being interleaved in combination to provide a rotational interlock between said rotor hub (204) and said rotor shaft (128R or 130R) in the rotor assembly (100);   characterized in thateach of said hub splines (208) having an outwardly tapered lower portion (210) that makes a predetermined angle (θ) with respect to said centerline (212); andsaid predetermined angle (θ) of said outwardly tapered lower portions (210) of said hub splines (208) being equal to said predetermined angle (β) of said conic transition portion (196) of said rotor shaft (128R or 130R) wherein said tapered lower portions (210) of said hub splines (208) abuttingly engage and are mechanically supported by said conic transition portion (196) of said rotor shaft (128R or 130R) in the rotor assembly (100).

公开(公告)号：AU1017895A

公开(公告)日：1995-03-09

申请号：AU1017895

申请日：1995-01-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYPON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FURNES KENNETH M ,  FARRELL MARVIN D ,  SANDY DAVID F ,  BEATTY ROBERT D ,  HANSEN BRUCE D

IPC: B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/20 ,  B64C27/33 ,  B64C27/46 ,  B64C27/473 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  F02B75/02 ,  F16C11/06 ,  F16D1/02 ,  F16D1/05 ,  F16D1/06 ,  F16D3/06 ,  F16D3/18 ,  F16D41/07 ,  F16F15/10 ,  F16H1/14 ,  F16H1/22 ,  B64D35/06

Abstract: An integrated spline/cone seat subassembly (190) for an unmanned aerial vehicle (10) having a rotor assembly (100) that includes ducted, counter-rotating rotors (200, 202), comprising:a rotor shaft (128R or 130R) having an axis, said rotor shaft (128R or 130R) includinga primary shaft portion (192) having a first diameter (D 1 ),an end shaft portion (194) having a second diameter (D 2 ) and having a plurality of shaft splines (198) extending radially outwardly therefrom, anda conic transition portion (196) intermediate said primary and end shaft portions (192, 194), said conic transition portion (196) making a predetermined angle (β) with respect to said axis of said rotor shaft (128R or 130R); anda rotor hub (204) having a centerline (212), said rotor hub (204) having a shaft aperture (206) having a plurality of hub splines (208) extending radially inwardly therefrom;said plurality of hub splines (208) and said plurality of shaft splines (198) being interleaved in combination to provide a rotational interlock between said rotor hub (204) and said rotor shaft (128R or 130R) in the rotor assembly (100);   characterized in thateach of said hub splines (208) having an outwardly tapered lower portion (210) that makes a predetermined angle (θ) with respect to said centerline (212); andsaid predetermined angle (θ) of said outwardly tapered lower portions (210) of said hub splines (208) being equal to said predetermined angle (β) of said conic transition portion (196) of said rotor shaft (128R or 130R) wherein said tapered lower portions (210) of said hub splines (208) abuttingly engage and are mechanically supported by said conic transition portion (196) of said rotor shaft (128R or 130R) in the rotor assembly (100).