-
公开(公告)号：US10676181B2
公开(公告)日：2020-06-09
申请号：US15507178
申请日：2015-09-25
IPC分类号： B64C27/10 , B64C27/00 , B64D35/06 , F16F15/02 , B64C27/14 , B64C1/00 , B64C7/00 , B64C13/18 , B64C13/50 , B64C19/00 , B64C27/12 , B64C27/16 , B64C27/32 , B64C27/33 , B64C27/473 , B64C27/48 , B64C27/51 , B64C27/52 , B64C27/54 , B64C27/78 , B64C27/80 , B64C27/82 , B64D39/00 , B64D39/06 , B64D45/02 , F16H37/02 , G05D1/00 , G05D1/02 , B64C13/04 , G05D1/08 , B64C27/57 , B64C27/467 , B64C27/08 , F02C9/28 , F16D13/52 , F16D13/72 , F16D13/74
摘要： An aircraft is provided including an airframe, an extending tail, a counter-rotating, coaxial main rotor assembly having an upper rotor assembly and a lower rotor assembly, and a translational thrust system including a propeller positioned at the extending tail. The translational thrust system is configured to provide translational thrust to the airframe when the aircraft is in a non-autorotation state and to generate power when in an autorotation state. A gearbox interconnects the propeller and the main rotor assembly to drive the main rotor assembly and the translational thrust system in the non-autorotation state. When the aircraft is in autorotation, the power generated by the propeller drives rotation of the main rotor assembly via the gearbox.
-
公开(公告)号：US20170297692A1
公开(公告)日：2017-10-19
申请号：US15515897
申请日：2015-09-28
IPC分类号： B64C27/467 , B64C27/82 , B64C27/10
CPC分类号： F16F15/02 , B64C13/04 , B64C13/50 , B64C27/001 , B64C27/006 , B64C27/10 , B64C27/14 , B64C27/467 , B64C27/57 , B64C2027/004 , B64C2027/8236 , B64D35/06 , G05D1/0816 , G05D1/0858
摘要： A rotary wing aircraft includes an airframe, one or more engines supported by the airframe, and a plurality of rotor blades operatively connected to the one or more engines. Each of the plurality of rotor blades includes a rotor lift-to-drag (L/De) ratio greater than 9 at airspeeds between about 150 KTAS and about 210 KTAS, and the rotary wing aircraft includes an aircraft lift-to drag (L/D) ratio of greater than about 4 between about 99 KTAS and about 210 KTAS.
-
公开(公告)号：US20170267338A1
公开(公告)日：2017-09-21
申请号：US15503633
申请日：2015-06-18
CPC分类号： F16F15/02 , B64C13/04 , B64C13/50 , B64C27/001 , B64C27/006 , B64C27/10 , B64C27/14 , B64C27/467 , B64C27/57 , B64C2027/004 , B64C2027/8236 , B64D35/06 , G05D1/0816 , G05D1/0858
摘要： An aircraft is provided including an airframe, an extending tail, and a counter rotating coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system including a propeller is positioned at the extending tail. The translational thrust system provides translational thrust to the airframe. A drive system is configured to operate both the main rotor system and the translational thrust system. The drive system includes a clutch configured to selectively couple or decouple the propeller from the drive system.
-
公开(公告)号：US20180305003A1
公开(公告)日：2018-10-25
申请号：US15774659
申请日：2016-10-07
摘要： A fairing system, includes a hub fairing and a fixed fairing, such as a shaft fairing or a pylon fairing, both arranged about a rotation axis. A gap is defined between the hub fairing and the fixed fairing, and a seal assembly is axially interposed between the hub fairing and the fixed fairing. The fixed fairing and the hub fairing are both removably mounted to the seal assembly such that either or both of the fairings can be dismounted from the seal assembly without disturbing the seal assembly to provide access to components disposed within the fairing.
-
公开(公告)号：US20170305543A1
公开(公告)日：2017-10-26
申请号：US15516080
申请日：2015-10-01
发明人： Robert C. Moffitt , William J. Eadie , David H. Hunter , Bryan Kenneth Baskin , Chris Paul Butler , Lance Halcom , Eric Lucien Nussenblatt
CPC分类号： F16F15/02 , B64C13/04 , B64C13/50 , B64C27/001 , B64C27/006 , B64C27/10 , B64C27/14 , B64C27/467 , B64C27/57 , B64C2027/004 , B64C2027/8236 , B64D35/06 , G05D1/0816 , G05D1/0858
摘要： An aircraft 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; an upper hub fairing positioned at the upper rotor assembly; a lower hub fairing positioned at the lower rotor assembly; and a shaft fairing disposed between the upper hub fairing and the lower hub fairing; wherein the upper hub fairing is substantially sealed to the shaft fairing and the lower hub fairing is substantially sealed to the shaft fairing.
-
公开(公告)号：US20170305539A1
公开(公告)日：2017-10-26
申请号：US15513301
申请日：2015-07-14
发明人： Mark R. Alber , William J. Eadie
IPC分类号： B64C27/10 , B64C27/473 , B64C27/82 , B64C27/14
摘要： An aircraft includes an airframe having an extending tail and a longitudinal axis extending from a nose of the airframe defining a length of the airframe. A counter rotating, coaxial main rotor assembly is located at the airframe and includes an upper rotor assembly and a lower rotor assembly. The upper rotor assembly and the lower rotor assembly rotate about an axis of rotation. The axis of rotation intersects the longitudinal axis forward of a midpoint of the longitudinal axis.
-
公开(公告)号：US10167079B2
公开(公告)日：2019-01-01
申请号：US15508346
申请日：2015-09-29
发明人： Steven D. Weiner , William J. Eadie
IPC分类号： G05D1/00 , B64C27/82 , B64C27/10 , B64C27/12 , B64C27/14 , B64C13/04 , B64C13/18 , G05D1/08 , B64C13/50 , B64C27/57 , G05D1/02 , B64C27/00 , B64D39/00 , B64D39/06 , B64C27/80 , B64D35/06 , F16H37/02 , B64C27/51 , B64C27/52 , B64C27/32 , B64C27/33 , B64C27/473 , B64C27/48 , B64C27/16 , B64C1/00 , B64C19/00 , B64C27/54 , B64C27/78 , B64C27/467 , B64C7/00 , B64D45/02 , F16D13/52 , F16D13/72 , F16D13/74 , B64C27/08 , G06F19/00 , F02C9/28
摘要： 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. A flight control computer is configured to control a main rotor rotational speed of the upper and the lower rotor assemblies of the main rotor assembly as a function of airspeed of the aircraft. A method of operating an aircraft includes retrieving a threshold main rotor rotational speed of the dual coaxial main rotor assembly and calculating an actual main rotor rotational speed according to an environment of the aircraft. The actual main rotor rotational speed is maintained to remain at or below the threshold main rotor speed according to an airspeed of the aircraft.
-
公开(公告)号：US20170305544A1
公开(公告)日：2017-10-26
申请号：US15515882
申请日：2015-09-30
CPC分类号： F16F15/02 , B64C13/04 , B64C13/50 , B64C27/001 , B64C27/006 , B64C27/10 , B64C27/14 , B64C27/467 , B64C27/57 , B64C2027/004 , B64C2027/8236 , B64D35/06 , G05D1/0816 , G05D1/0858
摘要： An aircraft composed of an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the extending tail. The translational thrust system provides translational thrust to the airframe. The aircraft includes a turn radius between about (595) feet and about (2440) feet for an airspeed between about (120) knots and about (210) knots at a constant altitude.
-
公开(公告)号：US20170283047A1
公开(公告)日：2017-10-05
申请号：US15508346
申请日：2015-09-29
发明人： Steven D. Weiner , William J. Eadie
CPC分类号： F16F15/02 , B64C1/0009 , B64C7/00 , B64C13/04 , B64C13/18 , B64C13/50 , B64C13/503 , B64C19/00 , B64C27/001 , B64C27/006 , B64C27/008 , B64C27/08 , B64C27/10 , B64C27/12 , B64C27/14 , B64C27/16 , B64C27/32 , B64C27/322 , B64C27/33 , B64C27/467 , B64C27/473 , B64C27/48 , B64C27/51 , B64C27/52 , B64C27/54 , B64C27/57 , B64C27/78 , B64C27/80 , B64C27/82 , B64C2027/004 , B64C2027/8209 , B64C2027/8227 , B64C2027/8236 , B64C2027/8263 , B64C2027/8272 , B64C2027/8281 , B64C2201/024 , B64D35/06 , B64D39/00 , B64D39/06 , B64D45/02 , F02C9/28 , F05D2220/329 , F05D2270/021 , F16D13/52 , F16D13/72 , F16D13/74 , F16H37/02 , G05D1/0077 , G05D1/0202 , G05D1/0204 , G05D1/08 , G05D1/0816 , G05D1/0858 , G06F19/00
摘要： 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. A flight control computer is configured to control a main rotor rotational speed of the upper and the lower rotor assemblies of the main rotor assembly as a function of airspeed of the aircraft. A method of operating an aircraft includes retrieving a threshold main rotor rotational speed of the dual coaxial main rotor assembly and calculating an actual main rotor rotational speed according to an environment of the aircraft. The actual main rotor rotational speed is maintained to remain at or below the threshold main rotor speed according to an airspeed of the aircraft.
-
公开(公告)号：US20170275014A1
公开(公告)日：2017-09-28
申请号：US15504250
申请日：2015-10-01
发明人： William J. Eadie , Patrick Boyle
摘要： 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.
-
-
-
-
-
-
-
-
-
搜索结果
19 条记录 (耗时 0.017 秒)
