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1. 发明专利

JP2013531579A Power supply to the apparatus to be supported by the rotor of an aircraft engine 有权
公开(公告)号：JP2013531579A
公开(公告)日：2013-08-08
申请号：JP2013514757
申请日：2011-06-08
申请人：イスパノ・シユイザ
发明人：ドウ・ウエルジフオセ，エリツク , デユバル，セドリツク
IPC分类号： B64C11/44 , F02C7/00 , F02C7/32 , H02K19/16
CPC分类号： F01D7/00 , B64C11/306 , B64D15/12 , B64D2027/005 , Y02T50/66
摘要：本発明は、ステータ（２）と、主軸（３）と、第１のロータ（４）と、第２のロータ（５）と、伝達機構（６）と、第１のロータによって支持される第１の電気装置と、第２のロータによって支持される第２の電気装置とを備える航空機エンジン（１）であって、ステータによって支持される少なくとも１つの第１の界磁巻線（８）と、直流電流を前記第１の界磁巻線に流すことができる制御ユニット（１２）と、第１のロータによって支持され前記第１の電気装置に接続される少なくとも１つの第１の電機子巻線（１０）および第２のロータによって支持され前記第２の電気装置に接続される少なくとも１つの第２の電機子巻線（１１）と、を含むことを特徴とする航空機エンジン（１）に関する。

2. 发明专利

JPS6432996A VARIABLE PITCH PROPELLER SYSTEM 失效
公开(公告)号：JPS6432996A
公开(公告)日：1989-02-02
申请号：JP16865588
申请日：1988-07-06
申请人： UNITED TECHNOLOGIES CORP
发明人： ARUBAATO JIEI UIROSUTEKU , MIRAADO JII MEIYO
IPC分类号： B63H3/06 , B64C11/44
摘要： PURPOSE: To reduce the noise and the maintenance cost, in a transmission mechanism of propeller pitch control information, by providing between a stationary plate and a rotating plate a communication link in which a capacitor on one side forms a high potential signal path and that on the other side forms a low potential return path. CONSTITUTION: A capacitor link 34 is constituted in such a way that it is protected by shrouds 76, 78, 82 between the stationary side 12 and the rotating side 16 of a propeller system 10 and comprises a high potential capacitor 64 and a low potential capacitor 66. In each of the capacitors 64, 66, a pair of ring-shaped plates 68, 70 are coaxially arranged with the rotating center 71 of a hub as the center. The control signal of high potential is sent between the plates 68 via an electrode 72, and the feedback signal of low potential is sent between the plates 70 fitted by bolts and nuts 74, by means of capacitance coupling. Thus, as compared with the conventional control information transmitting mechanism having a brush and a slip ring, noise and maintenance cost can be remarkably reduced.

3. 发明专利

JPS5642001B2 失效
公开(公告)号：JPS5642001B2
公开(公告)日：1981-10-01
申请号：JP1431374
申请日：1974-02-04
IPC分类号： B63H3/08 , B64C11/44 , G05B9/02

4. 发明专利

JP2021146826A 推力発生装置审中-公开
公开(公告)号：JP2021146826A
公开(公告)日：2021-09-27
申请号：JP2020047058
申请日：2020-03-17
申请人：日本精工株式会社
发明人：熊谷浩保 , 郡司大輔
IPC分类号： B64C11/32 , B64C11/44 , B64C27/68 , B64D27/24 , B64C27/605
摘要：【課題】回転翼を理想的な向きに簡単に高い精度で配列することができ、小型化および軽量化を実現することができる推力発生装置を提供する。【解決手段】推力発生装置は、複数の回転翼を回転させる推力発生モータと、回転翼のピッチ角を変更するピッチ角変更モータと、ピッチ角変更モータの回転を直動軸の直線運動に変換する第1の運動変換部と、回転翼のピッチ角を変更する第2の運動変換部を備える。第2の運動変換部は、回転翼を支持する複数のグリップの内側端部が挿入される複数のスラスト軸受と、リング状の複数のスラストワッシャを備える。回転翼の回転時に、グリップにかかる遠心力がスラスト軸受に与えられる。スラスト軸受によって外側に押圧されたスラストワッシャは、ケースの外端壁の内面に接触して支持され、スラストワッシャの湾曲面がケースの円形孔の内周面に形成された湾曲面にフィットする。【選択図】図18

5. 发明专利

JP2011522151A Simplified system for controlling the setting of the propeller blades for aircraft turboshaft engines 有权
公开(公告)号：JP2011522151A
公开(公告)日：2011-07-28
申请号：JP2011510985
申请日：2009-05-26
申请人：スネクマ
发明人：フランソワ・ガレ
IPC分类号： F02C7/042 , B64C11/44
CPC分类号： F01D7/00 , F04D29/323 , F04D29/364 , F05D2260/4023 , F05D2260/50 , F05D2260/79 , Y02T50/671 , Y02T50/673
摘要： A system for controlling pitch of a propeller blade of a turboshank engine, including two automatic locking members making it possible, depending on their controlled position, to lock rotation of a blade root in both directions of rotation, or to allow the rotation of the blade root support in either of the two directions.

6. 发明专利

JPH08216997A ROTOR BLADE FOR HELICOPTER 失效
公开(公告)号：JPH08216997A
公开(公告)日：1996-08-27
申请号：JP2677095
申请日：1995-02-15
申请人： MITSUBISHI HEAVY IND LTD
发明人： YAMAGUCHI HITOSHI
IPC分类号： B64C11/44 , B64C13/50 , B64C27/46 , B64C27/615
摘要： PURPOSE: To perform free, uniform, or local control of a pitch angle throughout a span direction according to an hourly state by a method wherein a skin in the vicinity of the rear edge of a blade is formed of a piezoelectric element and expandably at least in the direction of a chord. CONSTITUTION: A skin 2 having abundant flexibility of which a wing cross section consists togetherwith a spar 1a is arranged in such a manner to be coupled with the vicinity of the rear edge of a blade 1, namely, the rear upper and lower surfaces of the spar 1a being rigid, the skin 2 consisting of a resilient plate 3 and a piezoelectric element 4. The piezoelectric element 4 is formed of a square ceramics and a plurality of the piezoelectric elements arranged in a row-form manner in the direction of the span of the blade 1 and in the direction of a chord are arranged by mounting the piezoelectric elements on the upper surface (the surface) and the under surface (the back surface) of the resilient plate 3. By operating a charge pressure applier 5 in a direction in which the direction (y) of the piezoelectric element 4 on the upper surface side of the blade 1 is expanded and the direction (y) of the piezoelectric element 4 on the under surface side is contracted, the rear edge of the skin 2 is lowered and the blade 1 is brought into a rise pitch angle.

7. 发明专利

JPH06190152A CONTROLLER FOR ATTITUDE OF RADIO CONTROL HELICOPTER FOR HOBBY 失效
公开(公告)号：JPH06190152A
公开(公告)日：1994-07-12
申请号：JP35911792
申请日：1992-12-25
申请人： SAKOMU KK
发明人： AKIYAMA MAMORU , OGINO MASAMI , OGUCHI TETSUO
IPC分类号： A63H27/133 , A63H27/30 , A63H30/04 , B64C11/44 , B64C13/20
摘要： PURPOSE:To provide a controller capable of safely and simply remote-controlling a radio control helicopter. CONSTITUTION:This controller is used by mounting it on a radio control helicopter for a hobby together with an existing radio control receiver. In such a state, when the radio control helicopter is flying, an angular velocity detecting means detects angular velocity at the time when the body of the radio control helicopter rotates to the left and the right with a yaw axis as axis. An angle calculating means integrates detected angular velocity of the angular velocity detecting means and derives an angle at which the body of the radio control helicopter rotates to the left and the right with the yaw axis as axis. A manipulated variable determining means determines a manipulated variable of rudder servo based on a manipulated variable inputted by a manipulated variable input means, the detected angular velocity by the angular velocity detecting means, and the angle derived by the angle calculating means. A manipulated variable output means outputs the manipulated variable determined by its manipulated variable determining means to the rudder servo. As a result, in accordance with the manipulated variable, the rudder servo is operated.

8. 实用新型

JPH0541594U 失效
公开(公告)号：JPH0541594U
公开(公告)日：1993-06-08
申请号：JP10228791
申请日：1991-11-15
IPC分类号： A63H27/133 , B64C11/44

9. 发明专利

JPH0524585A PITCH CONTROL DEVICE FOR VARIABLE PITCH PROPELLER 失效
公开(公告)号：JPH0524585A
公开(公告)日：1993-02-02
申请号：JP20865491
申请日：1991-07-25
申请人： TOYOTA MOTOR CORP
发明人： MORIYA YOSHITO
IPC分类号： B64C11/40 , B64C11/44
摘要： PURPOSE:To always properly control the pitch of a propeller by correcting a control signal on a difference in the computed number of revolutions of an engine during the steady flight state of an aircraft in which the pitch of the propeller is controlled on a difference between the number of revolutions of the engine and its target number of revolutions. CONSTITUTION:An engine speed detecting means 1 detects the number of revolutions of an engine to rotate a propeller, and a target engine speed setting means 2 sets the target number of revolutions of the engine on an output lever operating state. An engine speed difference computing means 3 computes a difference between the number of revolutions of the engine and its target number of revolutions, and a control signal sending means 4 sends a control signal to control the pitch of the propeller for making a pitch control mechanism 5 control the pitch. In this case, a steady flight state judging means 6 is provided, and when the flight state is fudged to be steady, a control signal value correcting means 7 corrects the value of the control signal basing on the above number of revolution difference. Thus the slippage of control quantity caused by a change with the passage of time in a hydraulic pressure actuator or the like can be corrected.

10. 发明专利

JPS626897A CONTROLLER FOR PROPELLER 失效
公开(公告)号：JPS626897A
公开(公告)日：1987-01-13
申请号：JP11095086
申请日：1986-05-16
申请人： GEN ELECTRIC
发明人： SUTANREI GOODON DEI
IPC分类号： B64C11/44 , B64C11/48 , B64C11/50 , H02P5/52

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