JPS60166595A - Anti-torque rotor drive for helicopter - Google Patents
Anti-torque rotor drive for helicopterInfo
- Publication number
- JPS60166595A JPS60166595A JP59223096A JP22309684A JPS60166595A JP S60166595 A JPS60166595 A JP S60166595A JP 59223096 A JP59223096 A JP 59223096A JP 22309684 A JP22309684 A JP 22309684A JP S60166595 A JPS60166595 A JP S60166595A
- Authority
- JP
- Japan
- Prior art keywords
- tubular
- shaft
- drive
- drive shaft
- variable pitch
- 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.)
- Pending
Links
- 230000008878 coupling Effects 0.000 claims description 10
- 238000010168 coupling process Methods 0.000 claims description 10
- 238000005859 coupling reaction Methods 0.000 claims description 10
- OAICVXFJPJFONN-UHFFFAOYSA-N Phosphorus Chemical compound [P] OAICVXFJPJFONN-UHFFFAOYSA-N 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 239000003795 chemical substances by application Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910052698 phosphorus Inorganic materials 0.000 description 1
- 239000011574 phosphorus Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
- B64C27/64—Transmitting means, e.g. interrelated with initiating means or means acting on blades using fluid pressure, e.g. having fluid power amplification
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Accessories For Mixers (AREA)
- Toys (AREA)
- Pulleys (AREA)
- Retarders (AREA)
- Sliding-Contact Bearings (AREA)
Abstract
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
【発明の詳細な説明】
産業上の利用分野
本発明はヘリコプタの反トルクロータ駆動装置に関する
。DETAILED DESCRIPTION OF THE INVENTION Field of the Invention The present invention relates to anti-torque rotor drives for helicopters.
従来の技術
ヘリコプタ用反トルクロータ駆動装置において、中空の
管状駆動軸を使用することは知られている。BACKGROUND OF THE INVENTION It is known to use hollow tubular drive shafts in anti-torque rotor drives for helicopters.
この管状駆動軸は該軸に回動運動を伝達するためその一
端は駆動要素を収容した筐体にょシ回転可能な構成で支
持されている。管状駆動軸の自由端部にハブが組み付け
られ、通常このハブには２個乃至それ以上の可変ピッチ
方式の輻射状羽根が設けられている。This tubular drive shaft is rotatably supported at one end by a housing containing a drive element in order to transmit rotational motion to the shaft. Assembled to the free end of the tubular drive shaft is a hub, which is typically provided with two or more variable pitch radial vanes.
成る公知形式の反トルクロータ駆動において、回転翼ピ
ッチは管状駆動軸の内部に延びかつ該自由端から外方に
突出する１個の制御軸によって制御されるものがある。In some known types of anti-torque rotor drives, the rotor pitch is controlled by a control shaft extending inside the tubular drive shaft and projecting outwardly from its free end.
これは前記制御軸が１つの板部材を支持し、該板部材の
外側リム部分は可変ピッチ連結ロッドにより各可変ピッ
チ翼を支持するようにしている。前記板部材に連結され
た一端の反対端において該制御軸は外側サーｙ１制御軸
の出力部分に結合して該制御軸に軸方向の変位運動を付
与するようにしている。この変位運動は要求された可変
ピッチ変化を設定するために前記連結ロッドを介して回
転翼に伝達される。This is such that the control shaft supports a plate member, and the outer rim portion of the plate member supports each variable pitch blade by a variable pitch connecting rod. At the end opposite to the one end connected to the plate member, the control shaft is coupled to the output portion of the outer circumferential y1 control shaft to impart an axial displacement movement to the control shaft. This displacement movement is transmitted to the rotor via the connecting rod to set the required variable pitch change.
更に公知の反トルクロータ駆動において、可変ピッチ制
御軸は通常二つの部分に分割され、その第一の部分はサ
ーボ制御部材に連結され回動角度的に固定化される。そ
して第２の部分は管状駆動軸と共に回転される。上述し
た二つの部分は通常１個の継手により相互に結合されて
いる。該継手は該二つの部分を軸方向に咬合して一体化
するように設計された推力軸受を具備し、これら二部分
は各軸線のまわりに同時に相互に関係し合って両者の相
互回転作用を許すようにしている。Furthermore, in known anti-torque rotor drives, the variable pitch control shaft is usually divided into two parts, the first part of which is connected to a servo control member and is angularly fixed in rotation. The second part is then rotated together with the tubular drive shaft. The two parts mentioned above are usually connected to each other by a joint. The joint includes a thrust bearing designed to axially interlock and unite the two parts, such that the two parts are interrelated simultaneously about their respective axes to accommodate their mutual rotational action. I try to forgive.
前述した公知形式の反トルクロータ駆動装置は多数の欠
点を有する。その欠点の一つは可変ピッチ制御軸が幾分
長尺部分として管状駆動軸を支持（３）
する筐体に対し角度的に固定化して設けられている点で
ある。また他の欠点として前記推力軸受とサーボ制御部
材の配置構成に問題がある。The known types of anti-torque rotor drives mentioned above have a number of drawbacks. One of its disadvantages is that the variable pitch control shaft is provided as a somewhat elongated section angularly fixed relative to the housing supporting (3) the tubular drive shaft. Another drawback is the arrangement of the thrust bearing and the servo control member.
更に詳しく云えば、前記可変ピッチ制御軸上に成る回転
角度を付与して設定した部分は通常管状駆動軸の内部の
軸受部分により支持されており、この軸受部分の耐用寿
命はその部分に生ずる応力変形のために比較的短命であ
る。この応力変形作用は管状駆動軸に対する前述の可変
ピッチ制御軸部分の相対的回転作用によって生ずる円周
方向の変形と管状駆動軸に対し該制御軸を軸方向に摺動
せしめることにより生ずる軸方向変形とである。More specifically, the portion on the variable pitch control shaft that is set with a rotation angle is usually supported by a bearing portion inside the tubular drive shaft, and the service life of this bearing portion depends on the stress generated in that portion. Relatively short-lived due to deformation. This stress deformation effect is caused by the circumferential deformation caused by the relative rotation of the variable pitch control shaft portion with respect to the tubular drive shaft, and the axial deformation caused by sliding the control shaft in the axial direction with respect to the tubular drive shaft. That is.
推力軸受についていえば、該軸受は通常前述の筐体内部
或は管状駆動軸内部に配設されているため手の届かない
接近不能な状態下に置かれ即座に点検することは不可能
でありかつ日常の保守管理或は交換作業は極端に厄介と
なる。前述したサーが制御部材について云えば、普通該
部材はヘリコプタの尾部の一部詳しくは即ちそのフィン
の固着部分に直接的に結合されている。これは殊更に製
作（４）
することが困難でありまたフィンの重量を増加する。As for thrust bearings, they are usually located inside the above-mentioned housing or inside the tubular drive shaft, so they are inaccessible and cannot be inspected immediately. Moreover, daily maintenance or replacement work becomes extremely troublesome. In reference to the control member mentioned above, this member is normally connected directly to a portion of the tail of the helicopter, specifically to a fixed portion of its fin. This is particularly difficult to manufacture (4) and increases the weight of the fin.
発明が解決しようとする問題点とその解決手段上記の目
的志向を念頭において、本発明はヘリコプタ用の反トル
クロータ駆動装置を次のように構成する。即ちその反ト
ルク駆動装置は駆動筐体と、該筐体から突出し筐体に対
し回転する管状駆動軸と、前記管状駆動軸の自由端上に
取付けたロータと、前記管状駆動軸内部にその一部が収
容された可変ピッチ制御軸と、前記管状駆動軸に関して
可変ピッチ制御軸に可変のピッチ軸方向運動を起すため
のサーボ制御部材と、前記可変ピッチ制御軸とサーボ制
御部材間に構成した軸受型結合装置と、これら２軸両者
を回転角度的に結合するための結合手段を具備するもの
であり、その特徴とするところは次のように構成される
。即ち前記可変ピッチ制御軸は管状駆動軸に沿って延在
し装入配置部材を以って軸方向に摺動しかつ回転角度的
に設定される態様下に管状駆動軸内に支持され、更に、
該可変ピッチ制御軸の一端は管状駆動軸と駆動筐体とか
ら突出して前記軸受型結合機構により連結され、更に前
記サー？制御部材は管状形状に形成されて前記駆動筐体
内部に配置されて可変ピッチ制御軸を取囲むように構成
されているものである。Problems to be Solved by the Invention and Means for Solving the Problems With the above objectives in mind, the present invention configures an anti-torque rotor drive device for a helicopter as follows. That is, the anti-torque drive device includes a drive housing, a tubular drive shaft that projects from the housing and rotates relative to the housing, a rotor mounted on the free end of the tubular drive shaft, and a rotor mounted inside the tubular drive shaft. a variable pitch control shaft in which the variable pitch control shaft is housed; a servo control member for producing variable pitch axial movement of the variable pitch control shaft with respect to the tubular drive shaft; and a bearing configured between the variable pitch control shaft and the servo control member. It is equipped with a mold coupling device and a coupling means for coupling both of these two shafts in terms of rotational angle, and its features are as follows. That is, the variable pitch control shaft extends along the tubular drive shaft and is supported within the tubular drive shaft in an axially sliding and angularly set manner with a charging arrangement member; ,
One end of the variable pitch control shaft protrudes from the tubular drive shaft and the drive housing and is connected by the bearing type coupling mechanism, and further includes the servo shaft. The control member is formed in a tubular shape, is disposed inside the drive housing, and is configured to surround the variable pitch control shaft.
以下添付図面に示す一実施例を参照して本発明を説明す
るが、該図面は該装置の軸方向断面を示し、これによっ
て本発明を限定するものではない。The invention will now be described with reference to an embodiment shown in the accompanying drawings, which show an axial section through the device and are not intended to limit the invention thereby.
図面において符号１はヘリコプタの反トルクロータ駆動
装置を示す。該装置は管状駆動軸２を有し、該駆動軸２
は駆動筐体又はハウジング３から突出し回転駆動部４を
具えて該駆動軸２の自由端部には図示しない全体的に符
号５で示された反トルク駆動ロータのハブ上に取付けら
れている。In the drawings, reference numeral 1 indicates a counter-torque rotor drive of a helicopter. The device has a tubular drive shaft 2, the drive shaft 2
comprises a rotary drive 4 projecting from a drive housing or housing 3 and mounted on the free end of the drive shaft 2 on the hub of a counter-torque drive rotor, generally designated 5, not shown.
駆動筐体３は本質的にカップ形状をした２個の合体部分
即ち円筒状の筐体本体部分６と円錐台状の筐体本体部分
７により形成されている。筐体３の内部に配置された管
状駆動軸２の一部と一体的に結合されたベベルギヤの背
後においてこれらの合体された筐体本体部分６と７は互
に向き合わされ、凹状の側面壁体を構成して設けられて
いる。The drive housing 3 is formed by two essentially cup-shaped integral parts: a cylindrical housing body part 6 and a truncated conical housing body part 7. Behind the bevel gear, which is integrally connected with a part of the tubular drive shaft 2 arranged inside the housing 3, these combined housing body parts 6 and 7 face each other and form a concave side wall. It is set up as follows.
ベベルギヤ８は前記回転駆動部４の駆動軸ｌｏ上の小形
ベベルギヤ９と噛み合っている。回転駆動軸１０は円筒
状の筐体本体部分６に成形した管状付加部材１１を通り
、筐体３の内部に貫通している。該回転駆動軸１０の内
方端は軸受１２により回転自在に軸架される。円筒状筐
体本体部分６は管状駆動軸２と同軸心配置の取外し可能
な端蓋１３を含む。この端蓋１３には軸方向外方の管状
付加部分１４が形成される。端蓋１３は円筒状筐体本体
部分６の環状部分１５と一体的に固定される。この環状
部分１５は軸受１６を介して管状駆動軸２の端部を回転
自在に支承している。筐体３には外方に突出する２個の
側方付加部材１７を具備し、その１個は円筒状筐体本体
部分６の外壁から突き出し、他方の１個は管状付加部材
１１から突き出されている。これらの側方付加部材１７
の各々に取付は穴１８が設けられ、これは図示されてな
いヘリコプタの尾部部分に筐体３を固装するために設け
である。該円錐状筐体本体部分７は実（７）
質的に円錐台形状に形成され、その太径端壁は円筒状本
体部分６に対面しかつ円錐状本体部分７の小径端壁２３
を貫通する中心穴２２に対応して整合する中心穴２１が
形成されている。これらの中心穴２１．２２は両軸受２
４．２４を介して管状駆動軸２の中間部分を支持収容す
る。The bevel gear 8 meshes with a small bevel gear 9 on the drive shaft lo of the rotary drive section 4. The rotational drive shaft 10 passes through a tubular additional member 11 formed on the cylindrical housing main body portion 6 and penetrates into the interior of the housing 3. The inner end of the rotary drive shaft 10 is rotatably supported by a bearing 12 . The cylindrical housing body portion 6 includes a removable end cap 13 coaxially arranged with the tubular drive shaft 2 . This end cap 13 is formed with an axially outer tubular extension 14 . The end cover 13 is integrally fixed to the annular portion 15 of the cylindrical housing body portion 6. This annular portion 15 rotatably supports the end of the tubular drive shaft 2 via a bearing 16. The housing 3 is provided with two outwardly projecting lateral addition members 17, one of which projects from the outer wall of the cylindrical housing body portion 6 and the other one of which projects from the tubular addition member 11. ing. These side additional members 17
A mounting hole 18 is provided in each of the mounting holes 18, which is provided for fixing the housing 3 to the tail portion of a helicopter (not shown). The conical housing main body portion 7 is formed in a qualitatively truncated conical shape, with its large diameter end wall facing the cylindrical main body portion 6 and the small diameter end wall 23 of the conical main body portion 7.
A center hole 21 is formed to correspond to and align with the center hole 22 that passes through the center hole 22 . These center holes 21, 22 have both bearings 2
4.24 supports and accommodates the intermediate part of the tubular drive shaft 2.
この管状駆動軸２の内部を通して可変ピッチ制御軸２５
が延在し、該制御軸２５は一体に成形された２つの同心
配置の管状部分２６と２７から成る。その一方の管状部
分２７は円錐台状筐体本体部分７の内側に配置された装
入ブツシュにより管状駆動軸２内に軸線方向へ摺動可能
に支持されている。他方の管状部分２６は円筒状筐体本
体部分６と管状付加部材１４との内部を通って延在し、
付加部材１４から突き出され、柱状ビン２９の上端部分
が管状部分２６と一体に結合されている。A variable pitch control shaft 25 is passed through the inside of this tubular drive shaft 2.
extends, and the control shaft 25 consists of two concentrically arranged tubular sections 26 and 27 molded in one piece. One of the tubular sections 27 is axially slidably supported in the tubular drive shaft 2 by means of a charging bush arranged inside the frustoconical housing body section 7 . The other tubular portion 26 extends through the interior of the cylindrical housing body portion 6 and the tubular additional member 14;
The upper end portion of the columnar bottle 29 protrudes from the additional member 14 and is integrally connected to the tubular portion 26 .
前記ピン２９に２個の推力軸受３０の各内輪が固設され
るが、該内輪はピン２９の旋條ねじ部３２にナツト３１
をねじ込むことによりピン２９上にその軸方向にねじ締
め固定される。ピン２９は軸（８）
受３０を介して軸受は筒体３３を回転自在に支持する。Each inner ring of two thrust bearings 30 is fixed to the pin 29, and the inner ring is connected to the turning threaded portion 32 of the pin 29 by a nut 31.
is screwed onto the pin 29 in the axial direction thereof. The pin 29 is a shaft (8).The bearing rotatably supports the cylinder 33 via the bearing 30.
軸受は筒体３３はピン２９と同心状の筒状部分３４を有
し、この筒状部分３４は可変ぎツナ制御用揺動腕３６の
一つの腕部分を構成する二叉フォーク腕３５の間に挟入
されて取付けられる。In the bearing, the cylindrical body 33 has a cylindrical portion 34 concentric with the pin 29, and this cylindrical portion 34 is located between two forked fork arms 35 constituting one arm portion of a swinging arm 36 for controlling the variable pitch tension. It is inserted and attached to the
軸受は筒体３３には図示されていないが、その直径上の
両側には向き合って穿設された半径方向の穴があり、こ
れらの穴は二叉フォーク３５の両又部に穿設した嵌入穴
と一致整合している。これら整合穴の各対は小ねじ３９
により二叉フォーク３５の両腕に結合されたノｆッド３
８から突出するピン３７に嵌合する。揺動腕３６中央部
分は連結リンク４０の一端にヒンジ結合されその他端は
管状付加部材１４から半径方向外方に延びる付加形成部
分４１にヒンジ結合手段により連結されている。Although the bearings are not shown in the cylinder body 33, there are radial holes drilled facing each other on both diametrically opposite sides of the cylinder body 33. Match the holes and be consistent. Each pair of these alignment holes is fitted with a machine screw 39.
Nofd 3 connected to both arms of forked fork 35 by
It fits into a pin 37 protruding from 8. The central portion of the swinging arm 36 is hinged to one end of a connecting link 40, and the other end is connected to an additional forming portion 41 extending radially outwardly from the tubular additional member 14 by means of a hinge connection.
管状付加部材１４は端蓋１３と一体に形成されかつ符号
１３により全体的に表示した三部分のサー？制御部材４
３の外側管状体４２の一部を形成する。サー？制御部材
４３は駆動筐体３の内部に延在し、管状本体４２の内部
表面に固定した内部すング４４によって２つの同長部分
に分割され管状ロッド４５を摺動運動可能に係合する。The tubular add-on member 14 is integrally formed with the end cap 13 and includes a three-part circulator generally indicated by the numeral 13. Control member 4
It forms part of the outer tubular body 42 of No. 3. Sir? The control member 43 extends inside the drive housing 3 and is divided into two equal length sections by an internal tongue 44 fixed to the internal surface of the tubular body 42 and slidably engages the tubular rod 45 .
管状ロッド４５の一端は管状付加部材１４から張出され
、前記軸受は筒体３３の付加形成部分３４と一体に結合
される。One end of the tubular rod 45 extends from the tubular additional member 14 , and the bearing is integrally connected to the additional formed portion 34 of the barrel 33 .
管状ロッド４５は可変ピッチ制御軸２５の同心状形成部
分２６に沿って正しく嵌合され管状本体４２上の両端リ
ング４６においてはその外側が水密性を保持し摺動可能
に結合されている。管状本体４２と管状ロッド４５間に
おいて、リング部材４４と４６は管状ロッド４５上の各
環状ピストン４８と共に上記空間をそれぞれ２つの環状
シリンダ４７に形成している。The tubular rod 45 is properly fitted along the concentrically formed portion 26 of the variable pitch control shaft 25, and is slidably coupled to both end rings 46 on the tubular body 42 with the outer sides maintaining watertightness. Between the tubular body 42 and the tubular rod 45, the ring members 44 and 46, together with a respective annular piston 48 on the tubular rod 45, define the space into two annular cylinders 47, respectively.
前述した記載は軸受３０によシ可変ピッチ制御軸２５全
体がいかに管状駆動軸２と角度的に一体化して回動制御
されるかを示しており、これによって装入ブツシュ２８
上に生ずる内部応力歪が比較的に減殺しうるものである
。この装置の他に例のみない機能は管状駆動軸２に沿っ
て可変ピッチ制御軸２５をその軸方向に摺動を案内する
ことで（１１）
グ、４７・・・環状シリンダ、４８・・・環状ピストン
。The foregoing description shows how the entire variable pitch control shaft 25 is angularly integrated with the tubular drive shaft 2 and rotationally controlled by the bearing 30, thereby controlling the rotation of the charging bush 28.
The internal stress strain that occurs above can be relatively reduced. The unique function of this device is to guide the sliding movement of the variable pitch control shaft 25 in the axial direction along the tubular drive shaft 2 (11), 47... annular cylinder, 48... Annular piston.
ある。be.
更に駆動筐体３の外側に軸受３０を配置したことはサー
ボ制御機構４に対する可変ピッチ制御軸２５の連結部の
点検を簡潔化する。このようにして簡潔化された点検操
作はブツシュ３５と軸受３０をビン２９から引出すため
にナツト３１を単に弛めるだけで行ない得ることになる
。Furthermore, arranging the bearing 30 outside the drive housing 3 simplifies inspection of the connection portion of the variable pitch control shaft 25 to the servo control mechanism 4. This simplified inspection operation can be accomplished by simply loosening the nut 31 in order to pull the bushing 35 and bearing 30 out of the bin 29.
図面は本発明に係るヘリコプタの反トルクロータ駆動装
置の軸方向に沿った断面を示す。
１・・・ヘリコプタの反トルクロータ駆動装置、２・・
・管状駆動軸、３・・・駆動筐体、４・・・回転駆動部
、６・・・筒状筐体本体部分、７・・・円錐台状の筐体
本体部分、８，９・・・ベベルギヤ、１０・・・駆動回
転軸、１３・・・端蓋、１５・・・管状本体、２０・・
・大径端壁、２３・・・小径端壁、２５・・・可変ピッ
チ制御軸、２８・・・装入プツシ−１２９・・・柱状ビ
ン、３０・・・軸受、３３・・・軸受は筒体、３５・・
・二叉フォーク、３６・・・可変ピッチ制御揺動腕、４
０・・・連結リンク、４２・・・管状本体、４５・・・
管状ロッド、４６・・・端部リン（１２）
特許出願人
コストウルツィオニ アエロナウチチェ ジオバンニア
グスタ ソチェタ ペルアツィオニ
特許出願代理人
弁理士 青 木 朗
弁理士 西 舘 和 之
弁理士 吉 １）正 行
弁理士 山 口 昭 之
弁理士 西 山 雅 也The drawing shows a cross section along the axial direction of the anti-torque rotor drive device for a helicopter according to the present invention. 1... Helicopter anti-torque rotor drive device, 2...
- Tubular drive shaft, 3... Drive casing, 4... Rotation drive section, 6... Cylindrical casing main body part, 7... Frame-shaped casing main part, 8, 9...・Bevel gear, 10... Drive rotation shaft, 13... End cover, 15... Tubular body, 20...
・Large diameter end wall, 23...Small diameter end wall, 25...Variable pitch control shaft, 28...Charging pushy 129...Columnar bottle, 30...Bearing, 33...Bearing Cylindrical body, 35...
・Two-pronged fork, 36...Variable pitch control swinging arm, 4
0... Connecting link, 42... Tubular body, 45...
Tubular rod, 46...end phosphorus (12) Patent applicant Costurzioni Aeronautice Giovanni Agusta Soceta Perazioni Patent agent Akira Aoki Patent attorney Kazuyuki Nishidate Patent attorney Tadashi 1) Akira Yamaguchi, Patent Attorney Masaya Nishiyama
Claims (1)
し相対的に回動する管状駆動軸と、該管状駆動軸の自由
端に取付けられたロータと、前記管状駆動軸内部に一部
が収容されている可変ピッチ制御軸と、前記管状駆動軸
に対し該制御軸を軸方向の可変ピッチ運動を付与するた
めのサーブ制御部材と、前記可変ピッチ制御軸とサーブ
制御部材間を結合する軸受型結合機構及び前記駆動軸と
ピッチ制御軸の両者間を回転角度的に結合する結合機構
とを具備する反トルクロータ駆動装置であって、前記可
変ピッチ制御軸（２５）は前記管状駆動軸（２）に沿っ
て延在しかつ装入部材（２８）を配置した管状駆動軸（
２）により軸方向摺動作用と成る回転角度を以って固定
化された状態で支持され、前記可変ピッチ制御軸（２５
）の一端は管状駆動軸（２）と駆動筐体（３）から突出
しかつ前記軸受型結合装置（３０，３３）に結合され、
更に前記サーブ制御部材（４３）は管状に形成されて前
記駆動筐体（３）内部に配置されかつ前記可変ピッチ制
御軸（２５）を囲むように構成されていることを特徴と
するヘリコプタの反トルクロータ駆動装置。 ２、特許請求の範囲第１項記載の装置において、前記軸
受型結合装置は可変ピッチ制御軸（２５）の端部に設け
た少くとも１個の推力軸受（３０）と、該推力軸受（３
０）により回転可能に支持されてサーブ制御部材（４３
）の出力部（４５）に結合された軸受は筒体（３３）と
により構成されていることを特徴とするヘリコプタの反
トルクロータ駆動装置。 ３、特許請求の範囲第２項記載の装置において、前記サ
ーが制御部材（４３）は該部材自体の中を通されて延在
し、かつ前記可変ピッチ制御軸（２５）に沿って正しく
整合された出力管状ロッド（４５）を具備し、該出力管
状ロッド（４５）の一端は前記軸受は筒体３３に結合さ
れていることを特徴とするヘリコプタの反トルクロータ
駆動装置。[Scope of Claims] 1. A drive casing, a tubular drive shaft that protrudes from the drive casing and rotates relative to the casing, and a rotor attached to the free end of the tubular drive shaft; a variable pitch control shaft partially housed within the tubular drive shaft; a serve control member for imparting variable pitch movement in the axial direction to the control shaft with respect to the tubular drive shaft; and the variable pitch control shaft. an anti-torque rotor drive device comprising: a bearing-type coupling mechanism for coupling between the drive shaft and the serve control member; and a coupling mechanism for coupling the drive shaft and the pitch control shaft in terms of rotational angle, the anti-torque rotor drive device comprising: (25) is a tubular drive shaft (2) extending along the tubular drive shaft (2) and disposed with a charging member (28);
The variable pitch control shaft (25) is supported in a fixed state with a rotation angle for axial sliding motion by
) protrudes from the tubular drive shaft (2) and the drive housing (3) and is coupled to the bearing type coupling device (30, 33);
Furthermore, the serve control member (43) is formed in a tubular shape, is disposed inside the drive housing (3), and is configured to surround the variable pitch control shaft (25). Torque rotor drive. 2. The device according to claim 1, wherein the bearing-type coupling device includes at least one thrust bearing (30) provided at the end of the variable pitch control shaft (25);
0) is rotatably supported by the serve control member (43
1. An anti-torque rotor drive device for a helicopter, characterized in that a bearing coupled to an output portion (45) of the helicopter is constituted by a cylindrical body (33). 3. The apparatus of claim 2, wherein the control member (43) extends through itself and is properly aligned along the variable pitch control axis (25). An anti-torque rotor drive device for a helicopter, characterized in that the output tubular rod (45) has an output tubular rod (45) having a bearing, and one end of the output tubular rod (45) is connected to the cylindrical body 33.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| IT68108A/83 | 1983-10-26 | ||
| IT68108/83A IT1161530B (en) | 1983-10-26 | 1983-10-26 | TRANSMISSION FOR HELICOPTER ANTI-COPY ROTOR |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS60166595A true JPS60166595A (en) | 1985-08-29 |
Family
ID=11307904
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP59223096A Pending JPS60166595A (en) | 1983-10-26 | 1984-10-25 | Anti-torque rotor drive for helicopter |
Country Status (5)
| Country | Link |
|---|---|
| JP (1) | JPS60166595A (en) |
| DE (1) | DE3437582A1 (en) |
| FR (1) | FR2554082B1 (en) |
| GB (1) | GB2148818A (en) |
| IT (1) | IT1161530B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2014510663A (en) * | 2011-02-17 | 2014-05-01 | アグスタウエストランド リミテッド | Gearbox lubrication mechanism |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2113179C (en) * | 1991-08-02 | 2001-01-23 | Rene A. Desjardins | Ducted tail rotor for rotary wing aircraft providing torque reaction and yaw attitude control |
| JP2768826B2 (en) * | 1991-08-02 | 1998-06-25 | ザ、ボーイング、カンパニー | Duct fan and pitch controller for tail rotor of rotary wing aircraft |
| CN105035315B (en) * | 2015-08-03 | 2016-11-02 | 深圳供电局有限公司 | Multi-rotor unmanned aerial vehicle based on laser light accurate line drop inspection and operation method |
| CH717147A2 (en) * | 2020-02-18 | 2021-08-31 | Marenco Ag | Hydraulic servo actuator. |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB601952A (en) * | 1942-12-05 | 1948-05-14 | Andre Aime Lucien Bruel | Improvements in aircraft with sustaining airscrews |
| GB628861A (en) * | 1946-04-17 | 1949-09-06 | Firestone Tire & Rubber Co | Improvements in or relating to torque counteracting rotors for helicopters |
| GB615156A (en) * | 1946-07-30 | 1949-01-03 | Cierva Autogiro Co Ltd | Improvements in and relating to aircraft with rotary-wings |
| US2581923A (en) * | 1947-11-25 | 1952-01-08 | Firestone Tire & Rubber Co | Auxiliary rotor for helicopters |
| GB734888A (en) * | 1953-04-30 | 1955-08-10 | Short Brothers & Harland Ltd | An improved helicopter rotor hub |
| GB777076A (en) * | 1954-02-19 | 1957-06-19 | United Aircraft Corp | Improvements in and relating to helicopter rotors |
-
1983
- 1983-10-26 IT IT68108/83A patent/IT1161530B/en active
-
1984
- 1984-10-13 DE DE3437582A patent/DE3437582A1/en not_active Withdrawn
- 1984-10-19 GB GB08426451A patent/GB2148818A/en not_active Withdrawn
- 1984-10-24 FR FR8416308A patent/FR2554082B1/en not_active Expired
- 1984-10-25 JP JP59223096A patent/JPS60166595A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2014510663A (en) * | 2011-02-17 | 2014-05-01 | アグスタウエストランド リミテッド | Gearbox lubrication mechanism |
| US9611929B2 (en) | 2011-02-17 | 2017-04-04 | Agustawestland Limited | Gearbox lubrication |
| US9897193B2 (en) | 2011-02-17 | 2018-02-20 | Agustawestland Limited | Gearbox lubrication |
Also Published As
| Publication number | Publication date |
|---|---|
| GB8426451D0 (en) | 1984-11-28 |
| IT1161530B (en) | 1987-03-18 |
| GB2148818A (en) | 1985-06-05 |
| FR2554082B1 (en) | 1987-01-23 |
| IT8368108A0 (en) | 1983-10-26 |
| DE3437582A1 (en) | 1985-05-09 |
| FR2554082A1 (en) | 1985-05-03 |
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