公开(公告)号：JP2001026297A

公开(公告)日：2001-01-30

申请号：JP2000182393

申请日：2000-06-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYCON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FAANZU 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: PROBLEM TO BE SOLVED: To provide the optimum design for maximizing the allowable mistake alignment by connecting the torque to a driving shaft through an internal spline connection by the complementary engagement of spline teeth between the internal spline connection and an external crown spline connection. SOLUTION: An engine connection sub-assembly 63 includes a fastening fitting 64, a taper adapter, that is, a band pan 65, a ball bearing 66, an external crown spline connection 61, an internal spline connection 68 and a pin collar connector 69. The fastening fitting 64 is used for firmly fixing the engine connection sub-assembly 63 and a taper output shaft 54S of an engine. The fastening fitting 64 is mechanically mutually connected to the band pan 65. A center of a sprag clutch 62 is placed on an intermediate between the external crown spline connection 67 and the band pan 65 by means of the ball bearing 66. The external crown spline connection 67 is mechanically mutually connected to the internal spline connection 68.

公开(公告)号：JP2001026296A

公开(公告)日：2001-01-30

申请号：JP2000182395

申请日：2000-06-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYCON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FAANZU 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: PROBLEM TO BE SOLVED: To provide a rotor type unmanned aircraft which can be utilized for wide-range reconnaissance aviation, or communication mission and especially for tactical reconnaissance aviation. SOLUTION: An unmanned aircraft UAV has a composite annular fuselage structure 20 surrounding a rotary assembly 100 including a pair of co-axial multi-blade double reversing rotors. The annular fuselage structure 20 includes an annular C-type structure, and the annular C-type structure regulates a cavity and a freely removable panel structure fitted in combination with the annular C-type structure. The UAV has a drive train assembly including a sprag clutch, an engine connection sub-assembly, a transmission connection sub-assembly and a drive shaft.

公开(公告)号：JP2001026298A

公开(公告)日：2001-01-30

申请号：JP2000182394

申请日：2000-06-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYCON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FAANZU 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: PROBLEM TO BE SOLVED: To rotate upper and lower rotary shafts in the directions opposite to each other by providing upper and lower bevel gears and a UAV power device sub-system for connecting the torque to a counter-rotating rotor with a mechanically engageable input gear. SOLUTION: A single-stage transmission sub-system 120 has an input pinion gear 122. The input pinion gear 122 comprises a spline end 124, a bearing 126 for mounting the input pinion gear 122 rotatably connected to a transmission housing 140, and upper and lower spiral bevel gears 128, 130. The upper and lower spiral bevel gears 128, 130 are respectively provided with integrally formed upper and lower rotor shafts 128R, 130R, which dispenses with an independent rotor shaft connecting means. Upper and lower multiblade rotors are respectively combined with the rotor shafts 128R, 130R to be fixed.

公开(公告)号：JP2001026299A

公开(公告)日：2001-01-30

申请号：JP2000182396

申请日：2000-06-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYCON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FAANZU 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: PROBLEM TO BE SOLVED: To provide the optimum design for exercising the optimum performance by providing a bearing bolt connected with a cabin internal bulkhead to be inserted, and a rotatable mounting means by combining an external inner bulkhead, a spherical bearing, a spherical bearing in a bearing cavity, and a bracket. SOLUTION: This snubber assembly comprises a spherical bearing 232, a bearing bolt 234, a fastening nut, a snubber bracket 238 connected and fixed to the spherical bearing 232, and a fixing bolt 240. The combination of the spherical bearing 232 and the snubber bracket 238 is rotatably mounted in a bearing cavity by means of the bearing bolt 234. The bearing bolt 234 is inserted through a bolt hole, the spherical bearing 232 and a bolt hole. The bearing bolt 234 is connected in a rotor hub by the fastening nut and fixed. The fastening nut is engaged with the bearing bolt 234 to keep the stability to the internal bulkhead 223.

公开(公告)号：JP2001018895A

公开(公告)日：2001-01-23

申请号：JP2000182397

申请日：2000-06-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYCON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FAANZU 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: PROBLEM TO BE SOLVED: To provide a rotor type UAV used for a reconnaissance flight and a communication mission over a wide area, especially for a strategic reconnaissance flight. SOLUTION: A unmanned aerial vehicle(UAV) 10 has a complex circular body structure 20 surrounding a rotor assembly 100 including a pair of coaxial multi-blade counter-rotating rotors. The circular body structure 20 includes a circular C-shape structure. The circular C-shape structure defines a detachable panel structure mounted with a combination of a cavity and the circular C-shape structure. The UAV has a drive train assembly having a sprag clutch, an engine coupled subassembly, transmission coupled subassembly, and a drive shaft.

公开(公告)号：WO2014189588A2

公开(公告)日：2014-11-27

申请号：PCT/US2014020264

申请日：2014-03-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZHENG ZHIJUN ,  FOSTER JOSEPH P ,  DAILEY STEPHEN P ,  SANDY DAVID F

IPC: F02C7/20 ,  B64D27/00 ,  F16B21/10

CPC classification number: B64D27/26 ,  B64D2027/266 ,  B64D2027/268 ,  F01D25/24 ,  F01D25/28 ,  F02C7/20 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2230/642 ,  F05D2240/90 ,  F05D2260/311 ,  F16B5/025 ,  Y02T50/44 ,  Y02T50/671

Abstract: An engine mount may include a clevis and a lug defining a hole therethrough. A pin may be joined to the clevis and may extend through the hole of the lug with the pin and the lug defining a clearance therebetween. A trigger system may be disposed on the lug and operatively associated with the pin.

Abstract translation: 发动机支架可以包括U形夹和限定穿过其中的孔的凸耳。 销可以连接到U形夹，并且可以通过销延伸穿过凸耳的孔，并且凸耳在其间限定间隙。 触发器系统可以设置在凸耳上并且与销可操作地相关联。

公开(公告)号：WO2014042774A3

公开(公告)日：2014-07-17

申请号：PCT/US2013052833

申请日：2013-07-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZHENG ZHIJUN ,  SANDY DAVID F

IPC: F02C7/32 ,  B64D27/12 ,  F02C7/00

CPC classification number: B64D27/26 ,  B64D2027/266 ,  Y02T50/44

Abstract: A waiting link to support an engine on an aircraft includes a body portion including a first body portion opening, a second body portion opening, and a space therebetween. A first bearing is received in the first body portion opening and moveable in a generally vertical direction. A second bearing is received in the second body portion opening. The first and second bearings include a first and second bearing opening, respectively, that receives a first and second attachment member, respectively, that secures the body portion to a first and second structure, respectively. A cam is located in the space. The cam is pivotable between a first position and a second position. The waiting link does not provide a load path when the cam is in the first position, and when a primary load path fails, the waiting link provides the load path when the cam is in the second position.

Abstract translation: 用于支撑飞机上的发动机的等待连接器包括主体部分，其包括第一主体部分开口，第二主体部分开口以及它们之间的空间。 第一轴承被容纳在第一主体部分中，并且在大致垂直的方向上可移动。 第二轴承被容纳在第二主体部分开口中。 第一和第二轴承分别包括第一和第二轴承开口，第一和第二轴承开口分别容纳分别将主体部分固定到第一和第二结构的第一和第二附接构件。 一个凸轮位于空间中。 凸轮可在第一位置和第二位置之间枢转。 当凸轮处于第一位置时，等待链接不提供负载路径，当主负载路径发生故障时，当凸轮处于第二位置时，等待连​​接提供负载路径。

公开(公告)号：WO2014021966A2

公开(公告)日：2014-02-06

申请号：PCT/US2013039818

申请日：2013-05-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SANDY DAVID F ,  ZHENG ZHIJUN

IPC: F02C7/20 ,  B64D27/10

CPC classification number: F01D25/28 ,  B64D2027/262 ,  B64D2027/266 ,  B64D2027/268 ,  F02C7/20 ,  Y02T50/671

Abstract: A forward engine mount assembly for a gas turbine engine includes a mount beam having a main body with a fore end and an aft end and a forward shackle assembly supported by the fore end of the mount beam. The forward shackle assembly comprises a first link configured to be connected to a first engine case structure and a second link configured to be connected to a second engine case structure. The first and second links are pivotally attached to each other.

Abstract translation: 用于燃气涡轮发动机的前置发动机支架组件包括安装梁，该安装梁具有带前端和后端的主体以及由安装梁的前端支撑的前向卸扣组件。 前卸扣组件包括构造成连接到第一发动机壳体结构的第一连杆和构造成连接到第二发动机壳体结构的第二连杆。 第一和第二连杆彼此枢转地连接。

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).