| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 旋翼机转子毂体 | CN91111677.X | 1991-12-27 | CN1026880C | 1994-12-07 | 雷纳·路易·摩勒 |
| 旋翼机转子毂体1的形式为每个桨叶2靠铰关节及连结构件与该载体1相连结，并包含有二个强力元件7，8，其二平面大体上互相平行且与转子桅杆3的轴线相垂直。以二元件互相分开造成的空间有足够大以容纳上述的铰关节，止挡托架16之一与相应桨叶2的足部成整体地移动，而另一托架17相对于载体二个元件来说是固定的并布置在该二元件的周边附近以构成一刚性带撑。该二元件为一个外侧环7及一个内侧环8，每环形成一刚性环缘并由一主要呈柱状的薄壁9连结在一起，此薄壁要包含有至少和桨叶2数相同的开口10数，每个开口10的尺寸要足以通过带折叠偏角的相应桨叶的铰关节及连结构件。 | ||||||
| 2 | 包括牵引/滞后邻抵机构的旋翼及飞行器 | CN201510198884.0 | 2015-04-22 | CN105015772A | 2015-11-04 | S·马泽特; S·本卡迪诺 |
| 一种旋翼(2)，其具有桨毂(3)和多个提升组件(10)，所述旋翼(2)的每个提升组件(10)具有一个保持和运动构件(15)。每个邻抵机构(20)包括弹性体隔离条(30)和分别接合在第一基部(32)和第二基部(33)上的两个C形金属夹片(40)。两个紧固销(50)的每个都穿过夹片(40)和基底(32、34)的纵向伸出部(35、36)并且穿过桨毂的孔口。 | ||||||
| 3 | 包括牵引/滞后邻抵机构的旋翼及飞行器 | CN201510198884.0 | 2015-04-22 | CN105015772B | 2017-04-12 | S·马泽特; S·本卡迪诺 |
| 一种旋翼(2)，其具有桨毂(3)和多个提升组件(10)，所述旋翼(2)的每个提升组件(10)具有一个保持和运动构件(15)。每个邻抵机构(20)包括弹性体隔离条(30)和分别接合在第一基部(32)和第二基部(33)上的两个C形金属夹片(40)。两个紧固销(50)的每个都穿过夹片(40)和基底(32、34)的纵向伸出部(35、36)并且穿过桨毂的孔口。 | ||||||
| 4 | 旋翼机转子毂体 | CN91111677.X | 1991-12-27 | CN1062876A | 1992-07-22 | 雷纳·路易·摩勒 |
| 旋翼机转子毂体1的形式为每个桨叶2靠铰关节及连结构件与该载体1相连结，并包含有二个强力元件7，8，其二平面大体上互相平行且与转子桅杆3的轴线相垂直。以二元件互相分开造成的空间有足够大以容纳上述的铰关节，止挡托架16之一与相应桨叶2的足部成整体地移动，而另一托架17相对于载体二个元件来说是固定的并布置在该二元件的周边附近以构成一刚性带撑。该二元件为一个外侧环7及一个内侧环8，每环形成一刚性环缘并由一主要呈柱状的薄壁9连结在一起，此薄壁要包含有至少和桨叶2数目相同的开口10，每个开口10的尺寸要足以通过带折叠偏角的相应桨叶的铰关节及连结构件。 | ||||||
| 5 | 낮은 높이의 조정 가능한 틸트 로터 다운스톱 | KR1020000044511 | 2000-08-01 | KR1020010049953A | 2001-06-15 | 리안마이클제이; 짐머만브레트알 |
| PURPOSE: A low-height tunable tilt rotor downstop is provided which separates a horizontal load and has a low height by providing a pivotally movable striker assembly and a down stop assembly including a cradle assembly formed so as to receive the striker assembly freely to be removed. CONSTITUTION: A striker assembly(31) includes a base member(33) formed so as to receive an adjustable striker arm(35) formed with angle. The base member(33) includes an installation opening part(36). The striker arm(35) is formed into an L-shape having a post part(37) and a leg part(39). A down stop assembly is moved from a tip part(49) to a leg part(39) of the post part(37) generated by a tilt rotor assembly in the flying mode by the striker assembly(31). With this structure, a cradle assembly can be maintained at a low height. | ||||||
| 6 | The rotor of the rotary-wing aircraft | JP15945184 | 1984-07-31 | JPH0764316B2 | 1995-07-12 | ジヤン・リユ・ルマン; ロベール・ジヤン・シユジ |
| 7 | JPH0479880B2 - | JP23121683 | 1983-12-06 | JPH0479880B2 | 1992-12-17 | EMIRIO PARIAANI |
| 8 | JPS6341800B2 - | JP5703980 | 1980-04-28 | JPS6341800B2 | 1988-08-18 | DONARUDO REROI FUERISU; PIITAA CHEISU OOGURU |
| 9 | JPS5833160B2 - | JP10128275 | 1975-08-22 | JPS5833160B2 | 1983-07-18 | KENESU WATOSON |
| 10 | Helicopter rotor | JP5703980 | 1980-04-28 | JPS55148696A | 1980-11-19 | DONARUDO REROI FUERISU; PIITAA CHIEISU OOGURU |
| 11 | ******** Shi * ho *** i ***** ne *** ha ******* e ***** e *** ku *** su *** ****** shi * ku ** | JP196676 | 1976-01-09 | JPS5195396A | 1976-08-20 | |
| 12 | ROTORCRAFT FALL RESTRAINT PROTECTION ATTACH POINTS AND MECHANISM SYSTEMS | US15343678 | 2016-11-04 | US20180126199A1 | 2018-05-10 | Bob Thornton; Chyau Tzeng; Brian Mesing; Kevin Knott; Mark Wiinikka; Edith Richard; David Platz; Joshua Edler; Sarah Villanueva; Thomas Mast; Joseph Leachman; Daniel John Burns |
| The present invention includes a safety apparatus and method for protecting users during maintenance operations for a rotorcraft comprising: at least one permanent, semi-permanent, or detachable safety bar, strap, fastener, hook, or loop that is attached or attachable to a rotorcraft, wherein the safety bar, strap, fastener, hook, or loop is positioned in an area or surface between a windshield of the rotorcraft and a tail boom of the rotorcraft and is connectable to a user safety device to provide fall protection from the area or surface. | ||||||
| 13 | ROTORCRAFT ROTOR AND PROPELLER SPEED | US15504250 | 2015-10-01 | US20170275014A1 | 2017-09-28 | William J. Eadie; Patrick Boyle |
| An aircraft includes an airframe having an extending tail, a counter rotating, coaxial main rotor assembly disposed at the airframe including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the extending tail and providing translational thrust to the airframe, the translational thrust system including a propeller. A gearbox system is operably connected to the main rotor assembly and the propeller to drive rotation of the main rotor assembly and the propeller. The gearbox is configured to maintain a main rotor assembly tip speed below Mach 0.9 and a propeller helical tip speed below Mach 0.88. | ||||||
| 14 | LIFT OFFSET CONTROL OF A ROTARY WING AIRCRAFT | US15503617 | 2015-09-30 | US20170233068A1 | 2017-08-17 | Erez Eller; Matthew T. Luszcz; Kenneth C. Arifian; Kevin L. Bredenbeck; Bryan S. Cotton |
| An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly composed of a plurality of blades and a lower rotor assembly composed of a plurality of blades. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A flight control system to control the upper rotor assembly and the lower rotor assembly, wherein the flight control system is configured to control lift offset of the upper rotor assembly and the lower rotor assembly. | ||||||
| 15 | DUAL ROTOR, ROTARY WING AIRCRAFT | US15514595 | 2015-09-29 | US20170217582A1 | 2017-08-03 | Kevin L. BREDENBECK; Bryan S. COTTON; Kenneth C. ARIFIAN; Erez ELLER; Matthew T. LUSZCZ |
| An aircraft is provided and includes an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe, at least one sensor and at least one inertial measurement unit (IMU) to sense current flight conditions of the aircraft, an interface to execute controls of a main rotor assembly in accordance with control commands and at least one flight control computer (FCC) to issue the control commands. The at least one FCC includes a central processing unit (CPU) and a memory having logic and executable instructions stored thereon, which, when executed, cause the CPU to issue the control commands based on the current flight conditions and a result of an execution of the logic for the current flight conditions. | ||||||
| 16 | Bearing Restraint for Rotor Systems | US13346912 | 2012-01-10 | US20130175384A1 | 2013-07-11 | Chad L. Jarrett; Frank B. Stamps; Mark Wiinikka; Scott Hemmen |
| According to one embodiment, a rotor system comprises a yoke, a grip, an elastomeric bearing, and a bearing restraint. The grip is positioned around a portion of the yoke and has both a closed end and an open end. The elastomeric bearing is coupled to the closed end of the grip and located between the closed end and the yoke. The bearing restraint is coupled to the grip between the yoke and the open end at a distance from the closed end such that the yoke contacts the bearing restraint when the rotor system is subject to a first centrifugal force but does not contact the bearing restraint when the rotor system is subject to a second centrifugal force greater than the first centrifugal force | ||||||
| 17 | Elastomeric bearing elements for droop stop mechanisms | US11251732 | 2005-10-17 | US07354248B2 | 2008-04-08 | David A. Zinni |
| An elastomeric bearing element having an outer race, an inner race, and at least two elastomeric segments secured between the inner and outer races is provided. The elastomeric segments are spaced from one another by a corresponding number of expansion segments. The elastomeric segments provide a first spring rate when a first force applied to the outer race places the elastomeric segments in compression and a second spring rate when a second force applied to the outer race places the elastomeric segments in shear. The second spring rate is lower than the first spring rate. | ||||||
| 18 | Rotocraft rotor with hinged blades and lockable retractable flapping abutments | US11411135 | 2006-04-26 | US20070059175A1 | 2007-03-15 | Stephane Mazet; Jean Mondet; Philippe Antomarchi; Jean-Marc Latorre |
| A rotorcraft rotor with hinged blades, includes: a hub; a plurality of blades hinged to flap relative to the hub; bottom abutments of the hub, and bottom abutments of the blades suitable for co-operating with the bottom abutments of the hub; and top abutments of the hub, and top abutments of the blades suitable for co-operating with the top abutments of the hub; the top abutments of the hub being movable between a deployed position in which they extend facing the top abutments of the blades, and a retracted position in which they are offset angularly away from the top abutments of the blades. The rotor also includes elements for locking the top abutments of the hub in the deployed position, and inertial means for releasing the top abutments of the hub and for deactivating the locking means. | ||||||
| 19 | Gyroplane rotor with double-plate hub and external pitch control | US09242218 | 1999-05-12 | US06203277B1 | 2001-03-20 | Philippe Maurice René Legendre; Etienne Jean Rampal |
| A rotorcraft, in particular helicopter, rotor includes a tubular pylon driven in rotation about its axis, which is the rotation axis of the rotor, from its foot. A hub is attached to the pylon by a flared base and includes two annular plates substantially radial to the rotor axis and spaced from each other along the rotor axis so that relative to the pylon one is an axially inside plate and the other is an axially outside plate. Each of at least two blades has its root connected to the hub by retaining and articulation arrangements retained between the plates of the hub and enabling relative angular movement of the blade at least in pitch about a longitudinal blade pitch change axis controlled by displacement by a pitch rod of a pitch lever attached to the blade root. The base has lateral openings through which pass arms of a pitch control plate which rotates with the hub and is mobile at least axially in the base, the end of each arm, outside the base, being articulated to one end of a pitch rod articulated at the other end to the pitch lever of a respective rotor blade. | ||||||
| 20 | Hub for rotor head of rotary-wing aircraft and rotor head with such hub | US09171533 | 1998-10-21 | US06200097B1 | 2001-03-13 | René Mouille |
| A hub for the rotor head of a rotary-wing aircraft having a plurality of blades radially linked to the hub by a blade root provided with a rigid hub includes spherical stops associated with the blades, which stops have an inner armature linked to the root of the blade and an outer armature linked to the hub. The hub includes an upper plate and a lower plate formed of two separate components which are assembled with an outer armature of spherical stops being interposed therebetween, so that the spherical stops are housed in the space defined by the plates. The outer armature is arranged at the periphery of the plates so that a hollow hub is obtained without requiring a sidewall with apertures, so as to facilitate the mounting and/or removal of the blades and the spherical stops. The plates may have a triangular shape with cutoff corners wherein a plurality of outer armatures is arranged near the cut-off corner. | ||||||
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