JP4312228B2 - ヘリコプタ構造並びにその振動の減少方法及び装置 - Google Patents
ヘリコプタ構造並びにその振動の減少方法及び装置 Download PDFInfo
- Publication number
- JP4312228B2 JP4312228B2 JP2006315946A JP2006315946A JP4312228B2 JP 4312228 B2 JP4312228 B2 JP 4312228B2 JP 2006315946 A JP2006315946 A JP 2006315946A JP 2006315946 A JP2006315946 A JP 2006315946A JP 4312228 B2 JP4312228 B2 JP 4312228B2
- Authority
- JP
- Japan
- Prior art keywords
- helicopter
- actuator
- rotating system
- vibration
- sensor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/001—Vibration damping devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F7/00—Vibration-dampers; Shock-absorbers
- F16F7/10—Vibration-dampers; Shock-absorbers using inertia effect
- F16F7/1005—Vibration-dampers; Shock-absorbers using inertia effect characterised by active control of the mass
- F16F7/1017—Vibration-dampers; Shock-absorbers using inertia effect characterised by active control of the mass by fluid means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/001—Vibration damping devices
- B64C2027/002—Vibration damping devices mounted between the rotor drive and the fuselage
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Vibration Prevention Devices (AREA)
Description
本発明の第1の側面によると、回転系を支持するか該回転系により支持される機体を含む構造からなり、該構造は、励振周波数で相対運動が可能なパーツを有すると共に、該パーツ間に接続される複数のアクチュエータを有するヘリコプタであって、前記励振周波数に実質的に相当する周波数で前記アクチュエータを連続的に振動させる振動手段と、選択された位置で前記回転系に取り付けられ、回転中に前記選択された位置での動的変化を表す信号を発生するようになっている複数のセンサーと、該センサーからの前記信号を処理して、前記アクチュエータにより発生される付与力の位相及び大きさを制御すると共に、前記回転系の動的特性の変化を補償して前記機体の全振動レベルを減少するように前記付与力の位相及び大きさの特性を変更するために出力信号を発生する処理装置とを備えるヘリコプタが提供される。
Claims (13)
- 回転系を支持するか該回転系により支持される機体を含む構造からなり、前記回転系はサステイニング用の主ロータであり、前記回転系は複数のブレードが取り付けられるロータヘッドを備え、前記構造は、励振周波数で相対運動が可能なパーツを有すると共に、該パーツ間に接続される複数のアクチュエータを有するヘリコプタであって、
前記励振周波数に実質的に相当する周波数で前記アクチュエータを連続的に振動させる振動手段と、
前記ブレードの前記ロータヘッドに近い位置に取り付けられ、回転中に選択された位置での動的変化を表す信号を発生するようになっている複数のセンサーと、
該センサーからの前記信号を処理して、前記アクチュエータにより発生される付与力の位相及び大きさを制御すると共に、前記回転系の動的特性の変化を補償して前記機体の全振動レベルを減少するように前記付与力の位相及び大きさの特性を変更するために出力信号を発生する処理装置と
を備えるヘリコプタ。 - 前記構造の1つのパーツは、前記構造の別のパーツに関して相対運動が可能であって、前記回転系のエンジン、トランスミッション及び支持構造のうちの1つから、或いは1つ以上の組み合わせからなる請求項1記載のヘリコプタ。
- 前記構造の1つのパーツは、複数の弾性取付手段により前記構造の別のパーツに取り付けられている請求項2記載のヘリコプタ。
- 前記弾性取付手段と前記アクチュエータは数が等しい請求項3記載のヘリコプタ。
- 各アクチュエータは弾性取付手段と一体のユニットである請求項4記載のヘリコプタ。
- 前記アクチュエータの各々は電気油圧式のアクチュエータである請求項1〜5のいずれか1つに記載のヘリコプタ。
- 前記回転系の各ブレードについてセンサーが設けられている請求項1〜6のいずれか一項記載のヘリコプタ。
- 前記センサーのうちの1つは前記回転系のロータ駆動軸に装着されている請求項1〜7のいずれか1つに記載のヘリコプタ。
- 前記センサーは加速度計である請求項1〜8のいずれか1つに記載のヘリコプタ。
- 前記回転系にある前記センサーに加え、1つ以上のセンサーが前記ヘリコプタの機体に設けられていて、該機体の動的加速度を表す信号を発生する請求項1〜9のいずれか1つに記載のヘリコプタ。
- 回転系を支持するか該回転系により支持される機体を含むヘリコプタ構造であって、サステイニング用の主ロータを有し、前記回転系は複数のブレードが取り付けられるロータヘッドを備え、前記ヘリコプタ構造のパーツが励振周波数で相対運動が可能である前記ヘリコプタ構造の振動を減少するために、
前記ヘリコプタ構造の前記相対運動が可能なパーツ間に接続されるようになっている複数のアクチュエータと、
使用時に、前記励振周波数に実質的に相当する周波数で前記アクチュエータを連続的に振動させる振動手段と、
前記ブレードの前記ロータヘッドに近い位置に取り付けられ、回転中に選択された位置での動的変化を表す信号を使用時に発生するようになっている複数のセンサーと、
該センサーからの前記信号を処理して、前記アクチュエータにより発生される付与力の位相及び大きさを制御すると共に、前記回転系の動的特性の変化を補償するように前記付与力の位相及び大きさの特性を変更するために出力信号を発生するようになっている処理装置と
を備える、ヘリコプタ構造の振動減少装置。 - 前記アクチュエータは電気油圧式アクチュエータである請求項11記載の振動減少装置。
- 前記センサーは加速度計である請求項11又は請求項12記載の振動減少装置。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GBGB9523651.9A GB9523651D0 (en) | 1995-11-18 | 1995-11-18 | Helicopter and method for reucing vibration of a helicopter fuselage |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP30661496A Division JP4042922B2 (ja) | 1995-11-18 | 1996-11-18 | ヘリコプタ構造並びにその振動の減少方法及び装置 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2007055602A JP2007055602A (ja) | 2007-03-08 |
JP4312228B2 true JP4312228B2 (ja) | 2009-08-12 |
Family
ID=10784118
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP30661496A Expired - Lifetime JP4042922B2 (ja) | 1995-11-18 | 1996-11-18 | ヘリコプタ構造並びにその振動の減少方法及び装置 |
JP2006315946A Expired - Lifetime JP4312228B2 (ja) | 1995-11-18 | 2006-11-22 | ヘリコプタ構造並びにその振動の減少方法及び装置 |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP30661496A Expired - Lifetime JP4042922B2 (ja) | 1995-11-18 | 1996-11-18 | ヘリコプタ構造並びにその振動の減少方法及び装置 |
Country Status (5)
Country | Link |
---|---|
US (1) | US5853144A (ja) |
EP (1) | EP0774411B1 (ja) |
JP (2) | JP4042922B2 (ja) |
DE (1) | DE69613542T2 (ja) |
GB (1) | GB9523651D0 (ja) |
Families Citing this family (37)
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US6138947A (en) * | 1997-08-22 | 2000-10-31 | Sikorsky Aircraft Corporation | Active noise control system for a defined volume |
US6105900A (en) * | 1997-12-23 | 2000-08-22 | Sikorsky Aircraft Corporation | Active noise control system for a helicopter gearbox mount |
FR2784351B1 (fr) * | 1998-10-12 | 2000-12-08 | Eurocopter France | Dispositif et procede pour reduire les vibrations engendrees sur la structure d'un aeronef a voilure tournante, notamment un helicoptere |
US6229898B1 (en) * | 1998-12-23 | 2001-05-08 | Sikorsky Aircraft Corporation | Active vibration control system using on-line system identification with enhanced noise reduction |
DE10001159A1 (de) * | 2000-01-13 | 2001-07-26 | Liebherr Aerospace Gmbh | Schwingungsisolator für Helikopter |
GB2361757B (en) * | 2000-04-28 | 2003-12-03 | Bae Sys Electronics Ltd | Improvements in or relating to the damping of vibration |
US6832973B1 (en) | 2000-07-21 | 2004-12-21 | William A. Welsh | System for active noise reduction |
US6467723B1 (en) | 2000-10-10 | 2002-10-22 | Lord Corporation | Active vibration control system for helicopter with improved actustor placement |
US6869375B2 (en) * | 2001-02-27 | 2005-03-22 | Sikorsky Aircraft Corporation | High output force actuator for an active vibration control system |
ITBO20010560A1 (it) * | 2001-09-17 | 2003-03-17 | Marposs Spa | Metodo e apparecchiatura per l'equilibratura dinamica di una struttura rotante |
DE10154391A1 (de) | 2001-11-06 | 2003-05-22 | Eurocopter Deutschland | Vorrichtung und Verfahren zur Schwingungsisolation in einem Übertragungspfad |
US7017857B2 (en) * | 2002-09-16 | 2006-03-28 | Foster-Miller, Inc. | Active vibration control system |
US7958801B2 (en) * | 2003-10-01 | 2011-06-14 | Sikorsky Aircraft Corporation | Harmonic force generator for an active vibration control system |
US7118328B2 (en) * | 2004-03-12 | 2006-10-10 | Sikorsky Aircraft Corporation | Gearbox mounted force generator |
CN100535473C (zh) * | 2004-06-10 | 2009-09-02 | 洛德公司 | 控制直升机振动的方法和系统 |
US7448854B2 (en) * | 2004-08-30 | 2008-11-11 | Lord Corporation | Helicopter vibration control system and rotary force generator for canceling vibrations |
US8162606B2 (en) * | 2004-08-30 | 2012-04-24 | Lord Corporation | Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations |
DE602005008019D1 (de) * | 2005-05-16 | 2008-08-21 | Agusta Spa | Hubschrauber mit verbesserter Schwingungskontrollvorrichtung |
US8113321B2 (en) * | 2006-05-06 | 2012-02-14 | Lord Corporation | Helicopter reduced vibration isolator axial support strut |
US7648338B1 (en) * | 2006-09-14 | 2010-01-19 | Sikorsky Aircraft Corporation | Dual higher harmonic control (HHC) for a counter-rotating, coaxial rotor system |
EP1961657A1 (en) * | 2007-02-22 | 2008-08-27 | Steadicopter Ltd. | Improved stabilization for flight platforms |
WO2008107867A2 (en) * | 2007-03-07 | 2008-09-12 | Steadicopter Ltd. | Improved stabilization for flight platforms |
DK2071213T3 (da) | 2007-12-11 | 2015-01-19 | Gen Electric | Gearkassestøjreduktion med elektrisk drevstyring |
DE102008025298B4 (de) * | 2008-05-27 | 2010-12-16 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Verfahren und Vorrichtung zur aktiven Dämpfung von Vertikalschwingungen bei einem Hubschrauber mit angehängter Außenlast |
EP2241502B1 (en) * | 2009-04-13 | 2017-03-08 | Sikorsky Aircraft Corporation | Active vibration suppression via power minimization |
GB2492965B (en) * | 2011-07-15 | 2018-05-02 | Agustawestland Ltd | A system and method for reducing the transmission of vibration from a first vibrating body to a second body |
US10099780B2 (en) * | 2013-10-07 | 2018-10-16 | Sikorsky Aircraft Corporation | Active vibration control actuator |
US9284048B2 (en) | 2013-10-14 | 2016-03-15 | Sikorsky Aircraft Corporation | Global airframe health characterization |
US9580187B2 (en) | 2014-04-22 | 2017-02-28 | Sikorsky Aircraft Corporation | Rotor index sensor system |
US20170283044A1 (en) * | 2014-09-26 | 2017-10-05 | Sikorsky Aircraft Corporation | Damage adaptive vibration control |
FR3052209B1 (fr) | 2016-06-02 | 2018-06-01 | Airbus Helicopters | Resonateur, et aeronef muni de ce resonateur |
FR3064247B1 (fr) * | 2017-03-27 | 2021-09-17 | Safran Helicopter Engines | Amortissement des vibrations dans un aeronef a voilure tournante |
US20180372210A1 (en) * | 2017-06-26 | 2018-12-27 | Bell Helicopter Textron Inc. | Safety Bypass Valve |
EP3599164B1 (en) * | 2018-07-27 | 2020-11-25 | LEONARDO S.p.A. | Helicopter kit |
EP3599163B1 (en) * | 2018-07-27 | 2020-11-11 | LEONARDO S.p.A. | Helicopter kit |
US11584520B1 (en) * | 2021-10-14 | 2023-02-21 | Textron Innovations Inc. | Method and system for regulation of speed and position of a rotor in wing-borne flight |
US12024307B2 (en) | 2021-10-14 | 2024-07-02 | Textron Innovations Inc. | Method and system for regulation of speed and position of a rotor in wing-borne flight |
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FR2680848B1 (fr) * | 1991-08-29 | 1995-03-17 | Aerospatiale Ste Nat Indle | Procede et dispositif pour filtrer les excitations vibratoires transmises entre deux pieces, notamment entre le rotor et le fuselage d'un helicoptere. |
-
1995
- 1995-11-18 GB GBGB9523651.9A patent/GB9523651D0/en active Pending
-
1996
- 1996-11-13 DE DE69613542T patent/DE69613542T2/de not_active Revoked
- 1996-11-13 EP EP96118229A patent/EP0774411B1/en not_active Revoked
- 1996-11-18 JP JP30661496A patent/JP4042922B2/ja not_active Expired - Lifetime
- 1996-11-18 US US08/751,622 patent/US5853144A/en not_active Expired - Lifetime
-
2006
- 2006-11-22 JP JP2006315946A patent/JP4312228B2/ja not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
US5853144A (en) | 1998-12-29 |
EP0774411B1 (en) | 2001-06-27 |
DE69613542T2 (de) | 2001-10-18 |
JP4042922B2 (ja) | 2008-02-06 |
GB9523651D0 (en) | 1996-01-17 |
JP2007055602A (ja) | 2007-03-08 |
DE69613542D1 (de) | 2001-08-02 |
EP0774411A3 (en) | 1997-11-26 |
JPH09169300A (ja) | 1997-06-30 |
EP0774411A2 (en) | 1997-05-21 |
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