EP2598399A1 - Drehmomentenausgleich für einen helikopter - Google Patents

Drehmomentenausgleich für einen helikopter

Info

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Withdrawn
Application number
EP11714513.6A
Other languages
German (de)
English (en)
French (fr)
Inventor
Oliver Heid
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP2598399A1 publication Critical patent/EP2598399A1/de
Withdrawn legal-status Critical Current

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)
EP11714513.6A 2010-07-26 2011-04-05 Drehmomentenausgleich für einen helikopter Withdrawn EP2598399A1 (de)

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)

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* Cited by examiner, † Cited by third party
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

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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
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US5205512A (en) * 1991-08-19 1993-04-27 The Boeing Company Fluid control apparatus
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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

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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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