EP2598399A1 - Drehmomentenausgleich für einen helikopter - Google Patents
Drehmomentenausgleich für einen helikopterInfo
- Publication number
- EP2598399A1 EP2598399A1 EP11714513.6A EP11714513A EP2598399A1 EP 2598399 A1 EP2598399 A1 EP 2598399A1 EP 11714513 A EP11714513 A EP 11714513A EP 2598399 A1 EP2598399 A1 EP 2598399A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cross
- flow fan
- helicopter
- boom
- thrust
- 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.)
- Withdrawn
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8218—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft wherein the rotor or the jet axis is inclined with respect to the longitudinal horizontal or vertical plane of the helicopter
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8245—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft using air jets
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8254—Shrouded tail rotors, e.g. "Fenestron" fans
Definitions
- tail rotors For torque compensation in helicopters usually axial fans in the form of tail rotors are used to compensate for the torque generated by the main rotor.
- a horizontal i. Almost perpendicular to the vertical axis, directed thrust generated to counteract the rotation of the fuselage about the vertical axis.
- tail rotors are predominantly free on the boom ⁇ arranged and therefore pose a security risk, for example, for people on the ground.
- DE 102008015073 AI presented an enclosed tail rotor, a so-called. Fenestron, with the Both the security risk reduced as well as, for example, noise and vibration can be reduced because the blade tips do not rotate freely.
- the disadvantage is that due to the encapsulation result in a higher weight and a higher construction cost.
- this kind have tail rotors on a comparatively small size, which, however, has the consequence that the only torque ⁇ ment balancing a higher energy demand arises.
- the entire thrust direction i. not just a component
- a corresponding section of the cantilever form the housing of the cross-flow fan.
- a suitable portion of the cantilever is so ⁇ directed that it ensures the function of the actual housing of the cross-flow fan.
- the blower does not require explicitly own or separate housing, so that material and weight can be saved Kgs ⁇ NEN.
- the boom on a cavity which is bounded by a wall which forms the housing of the cross-flow fan.
- the cross-flow fan can be attached externally to the boom.
- a helicopter according to the invention is characterized in that it has the device according to the invention described above.
- a cross-flow fan is mounted on a boom of the helicopter, in particular on the tail boom, which has a thrust in operation, the torque of the main rotor balances.
- the cross-flow fan In operation, the cross-flow fan generates a thrust in one direction, which is at least one component perpendicular to the
- the crossflow fan generates thrust in a direction having at least one component perpendicular to the longitudinal axis of the boom.
- FIG. 2 shows a helicopter with a crossflow fan integrated into the tail boom.
- the Helikop ⁇ ter 100 includes a main rotor 110 for generating the upward and / or for propulsion on for flight operations. During operation, ie during rotation of the main rotor 110, the latter rotates about a rotational axis. tion axis RH and generates known as a torque. This would cause without appropriate compensation that the hull 120 of the helicopter 100 rotates about the axis of rotation RH.
- the cross-flow fan 200 basically consists of a housing 210 and a roller-shaped rotor 220 with a plurality of blades 230 which is rotatably accommodated in the housing.
- the housing is shown in the figure 1 attached to the rear from ⁇ casual 130 of the helicopter 100th
- the direction of the force F generated by the cross-flow fan 200 has the largest possible component in a direction which is oriented both perpendicular to the longitudinal axis of the boom 130 and perpendicular to the axis of rotation RH of the main rotor 110, then the corresponding torque for compensating the torque of the main rotor becomes maximum.
- the tail boom 130 of the helicopter 100 is thus idealerwei ⁇ se designed such that it has a cavity 131 having an internal cross-section and a length which is adapted to the dimensions of the rotor 220 of the cross-flow fan 200 and in which the rotor 220 of the cross-flow fan 200 is accommodated ,
- the corresponding section 132 of the jib 130 or the walls delimiting the cavity 131 comprising two end walls 211, 212 and a lateral surface 213 then form the Housing 210 of the cross-flow blower 200.
- the rotor 220 is shown in addition to sheets 230 with dashed lines, since these components are not visible due to the end wall 212 na ⁇ course . The same applies to the end wall 211st
- the minimum internal diameter of the cavity 131 is, for example, selected such that the blades 230 of the rotor 220, the In ⁇ nenwand of the cavity 131 just do not touch.
- certain tolerances must of course be taken into account.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
- Control Of Turbines (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102010032217A DE102010032217A1 (de) | 2010-07-26 | 2010-07-26 | Drehmomentenausgleich für einen Helikopter |
PCT/EP2011/055259 WO2012013365A1 (de) | 2010-07-26 | 2011-04-05 | Drehmomentenausgleich für einen helikopter |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2598399A1 true EP2598399A1 (de) | 2013-06-05 |
Family
ID=44343841
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11714513.6A Withdrawn EP2598399A1 (de) | 2010-07-26 | 2011-04-05 | Drehmomentenausgleich für einen helikopter |
Country Status (6)
Country | Link |
---|---|
US (1) | US9452832B2 (ru) |
EP (1) | EP2598399A1 (ru) |
CN (1) | CN103052564B (ru) |
DE (1) | DE102010032217A1 (ru) |
RU (1) | RU2568529C2 (ru) |
WO (1) | WO2012013365A1 (ru) |
Families Citing this family (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2511177B1 (en) * | 2011-04-11 | 2013-06-05 | Eurocopter Deutschland GmbH | Helicopter with cycloidal rotor system |
EP2808253B1 (en) * | 2013-05-30 | 2016-12-07 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Helicopter with cross flow fan |
PL3056423T3 (pl) * | 2015-02-16 | 2018-04-30 | Airbus Helicopters Deutschland GmbH | Statek powietrzny z kadłubem, który wyznacza co najmniej obszar wewnętrzny i obszar mieszczący układ napędowy |
US10118695B2 (en) * | 2016-03-18 | 2018-11-06 | Pratt & Whitney Canada Corp. | Directional control system and method of providing directional control |
US10377480B2 (en) | 2016-08-10 | 2019-08-13 | Bell Helicopter Textron Inc. | Apparatus and method for directing thrust from tilting cross-flow fan wings on an aircraft |
US10059428B2 (en) | 2016-08-10 | 2018-08-28 | Bell Helicopter Textron Inc. | Inflight connection of aircraft |
US10279900B2 (en) | 2016-08-10 | 2019-05-07 | Bell Helicopter Textron Inc. | Rotorcraft variable thrust cross-flow fan systems |
US10106253B2 (en) | 2016-08-31 | 2018-10-23 | Bell Helicopter Textron Inc. | Tilting ducted fan aircraft generating a pitch control moment |
US10421541B2 (en) | 2016-08-10 | 2019-09-24 | Bell Helicopter Textron Inc. | Aircraft with tilting cross-flow fan wings |
US10479495B2 (en) | 2016-08-10 | 2019-11-19 | Bell Helicopter Textron Inc. | Aircraft tail with cross-flow fan systems |
US10287012B2 (en) | 2016-08-19 | 2019-05-14 | Bell Helicopter Textron Inc. | Aircraft having radially extendable tailboom assembly |
US10293931B2 (en) | 2016-08-31 | 2019-05-21 | Bell Helicopter Textron Inc. | Aircraft generating a triaxial dynamic thrust matrix |
RU172022U1 (ru) * | 2017-02-08 | 2017-06-26 | Закрытое акционерное общество "Авиастроительная корпорация "Русич" | Устройство установки хвостового винта на одновинтовом вертолете |
US10384776B2 (en) | 2017-02-22 | 2019-08-20 | Bell Helicopter Textron Inc. | Tiltrotor aircraft having vertical lift and hover augmentation |
US10633086B2 (en) * | 2017-03-23 | 2020-04-28 | Bell Helicopter Textron Inc. | Rotorcraft anti-torque and directional control using a centrifugal blower |
DE202017104316U1 (de) * | 2017-07-19 | 2018-10-24 | SBM Development GmbH | Heckrotoranordnung |
US10814967B2 (en) | 2017-08-28 | 2020-10-27 | Textron Innovations Inc. | Cargo transportation system having perimeter propulsion |
CN113022847A (zh) * | 2021-03-11 | 2021-06-25 | 北京航空航天大学 | 一种矢量涵道尾桨高速直升机 |
Family Cites Families (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2473329A (en) * | 1944-12-15 | 1949-06-14 | Borg Warner | Tail rotor for helicopters |
US4200252A (en) * | 1977-12-21 | 1980-04-29 | Summa Corporation | Helicopter antitorque system using circulation control |
US4702437A (en) * | 1985-02-07 | 1987-10-27 | Stearns Jr Hoyt A | Electric air-driven helicopter |
US4660785A (en) * | 1985-12-16 | 1987-04-28 | Munski Michael S | Helicopter antitorque auxiliary propulsion system |
US4948068A (en) * | 1988-05-12 | 1990-08-14 | Mcdonnell Douglas Corporation | Circulation control slots in helicopter yaw control system |
US5174523A (en) * | 1989-01-09 | 1992-12-29 | Westland Helicopters Limited | Compound helicopter with engine shaft power output control |
RU1621346C (ru) * | 1989-02-28 | 1995-09-20 | Анатолий Трофимович Белобаба | Вертолет |
DE4121995A1 (de) | 1991-07-03 | 1992-01-09 | Kastens Karl | Tangentialgeblaese fuer turbotriebwerke |
FR2679199B1 (fr) * | 1991-07-16 | 1997-01-31 | Aerospatiale | Systeme anticouple pour helicoptere. |
US5205512A (en) * | 1991-08-19 | 1993-04-27 | The Boeing Company | Fluid control apparatus |
US5676335A (en) * | 1995-03-08 | 1997-10-14 | Mcdonnell Douglas Helicopter Company | Airflow control system for a helicopter |
US5908185A (en) * | 1995-10-12 | 1999-06-01 | Pawling Corporation | Handrail and bumper combination |
US6007021A (en) * | 1997-11-18 | 1999-12-28 | Tsepenyuk; Mikhail | Flying apparatus for a vertical take off and landing |
US5934608A (en) * | 1998-01-16 | 1999-08-10 | Mcdonnell Douglas Helicopter Company | Efficient bi-directional air flow deflector |
DE19835385B4 (de) * | 1998-08-05 | 2007-08-16 | Uli Streich | Modellhubschrauber |
WO2001007683A1 (en) | 1999-07-22 | 2001-02-01 | Infrastructure Repair Technologies, Inc. | Method of treating corrosion in reinforced concrete structures by providing a uniform surface potential |
CZ289229B6 (cs) * | 1999-10-12 | 2001-12-12 | Jan Ing. Csc. Námisňák | Vznáąivé těleso |
US6352220B1 (en) * | 2000-06-02 | 2002-03-05 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Helicopter tail boom with venting for alleviation and control of tail boom aerodynamic loads and method thereof |
DK1575828T3 (da) * | 2002-12-18 | 2008-12-01 | Iat 21 Innovative Aeronautics | Luftfartöj |
US6755374B1 (en) * | 2003-01-27 | 2004-06-29 | Franklin D. Carson | Anti-Torque and yaw-control system for a rotary-wing aircraft |
WO2006036147A1 (en) | 2004-09-28 | 2006-04-06 | Bell Helicopter Textron Inc. | Propulsive anti-torque system for rotorcraft |
FR2897040B1 (fr) * | 2006-02-06 | 2008-04-11 | Christian Claude Sellet | Dispositif de controle en lacet pour helicopteres. |
US7481290B2 (en) * | 2006-12-22 | 2009-01-27 | Pendzich Jerome S | Vertical lift vehicle |
DE102008015073B4 (de) | 2008-03-19 | 2014-02-13 | Eurocopter Deutschland Gmbh | Hubschrauber mit Mitteln zur aerodynamischen Unterstützung des Drehmomentausgleichs |
CA2817281C (en) * | 2010-11-12 | 2016-01-19 | Bell Helicopter Textron Inc. | Propulsive anti-torque nozzle system with external rotating sleeve for a rotorcraft |
WO2012064344A1 (en) * | 2010-11-12 | 2012-05-18 | Bell Helicopter Textron Inc. | Anti-torque nozzle system with internal sleeve valve for a rotorcraft |
DE102010055676A1 (de) * | 2010-12-22 | 2012-06-28 | Eads Deutschland Gmbh | Hybridrotor |
EP2511177B1 (en) * | 2011-04-11 | 2013-06-05 | Eurocopter Deutschland GmbH | Helicopter with cycloidal rotor system |
-
2010
- 2010-07-26 DE DE102010032217A patent/DE102010032217A1/de not_active Withdrawn
-
2011
- 2011-04-05 WO PCT/EP2011/055259 patent/WO2012013365A1/de active Application Filing
- 2011-04-05 US US13/812,105 patent/US9452832B2/en not_active Expired - Fee Related
- 2011-04-05 RU RU2013108260/11A patent/RU2568529C2/ru not_active IP Right Cessation
- 2011-04-05 EP EP11714513.6A patent/EP2598399A1/de not_active Withdrawn
- 2011-04-05 CN CN201180036280.6A patent/CN103052564B/zh not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2012013365A1 * |
Also Published As
Publication number | Publication date |
---|---|
DE102010032217A1 (de) | 2012-01-26 |
CN103052564B (zh) | 2016-05-11 |
CN103052564A (zh) | 2013-04-17 |
RU2013108260A (ru) | 2014-09-10 |
US9452832B2 (en) | 2016-09-27 |
WO2012013365A1 (de) | 2012-02-02 |
RU2568529C2 (ru) | 2015-11-20 |
US20130119186A1 (en) | 2013-05-16 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
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17P | Request for examination filed |
Effective date: 20130104 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
DAX | Request for extension of the european patent (deleted) | ||
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
INTG | Intention to grant announced |
Effective date: 20150210 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 20150623 |