WO2017161700A1 - Hélice à pas variable adaptatif, et aéronef - Google Patents

Hélice à pas variable adaptatif, et aéronef Download PDF

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Publication number
WO2017161700A1
WO2017161700A1 PCT/CN2016/085192 CN2016085192W WO2017161700A1 WO 2017161700 A1 WO2017161700 A1 WO 2017161700A1 CN 2016085192 W CN2016085192 W CN 2016085192W WO 2017161700 A1 WO2017161700 A1 WO 2017161700A1
Authority
WO
WIPO (PCT)
Prior art keywords
main shaft
connecting rod
adaptive variable
paddle
rotor head
Prior art date
Application number
PCT/CN2016/085192
Other languages
English (en)
Chinese (zh)
Inventor
鲍静云
范晋红
刘双
殷兰兰
Original Assignee
深圳市龙云创新航空科技有限公司
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 深圳市龙云创新航空科技有限公司 filed Critical 深圳市龙云创新航空科技有限公司
Publication of WO2017161700A1 publication Critical patent/WO2017161700A1/fr

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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

Definitions

  • This invention relates to the field of propellers, and more particularly to a variable pitch propeller, and to an aircraft.
  • variable pitch propellers The propellers of fixed-wing aircraft are divided into two types: fixed distance and variable pitch.
  • the pitch of fixed-distance propellers is fixed. Different pitches can only adapt to different ranges of speed. For low-speed pitches, it is difficult to adapt to high speed (efficiency). Low) Conversely, it is difficult to adapt to low speed (low efficiency) for high speed pitch, so the fixed pitch propeller can only have higher efficiency in the selected speed range.
  • the variable pitch propeller can adjust the pitch, so that the propeller has higher efficiency at different speeds.
  • the variable pitch propeller is generally calculated and analyzed by the control system before passing through the driving device. To achieve variable pitch, however, this method requires a complicated control system and driving device, which has high cost, high technical requirements, complicated mechanism, difficult maintenance, and low reliability.
  • the present invention provides an adaptive variable pitch propeller capable of adaptively changing the propeller pitch as the flight speed changes, so that the aircraft can have higher efficiency at different speeds;
  • the mechanical structure completes the automatic variable pitch, eliminating the need for a control system and additional drive devices, low cost and technical requirements, simple mechanism and high reliability.
  • the present invention provides an aircraft.
  • An adaptive variable pitch propeller includes a main shaft and at least two blades, and further includes a rotor head, a spring, a paddle, a connecting rod and a connecting rod fixing member, wherein
  • the rotor head is sleeved on the main shaft and slidable along the same, the connecting rod fixing member is mounted on the main shaft, and the spring is disposed between the rotor head and the connecting rod fixing member;
  • One end of the paddle is fixed to the blade, and the other end is rotatably connected with the rotor head, and the connecting rod is respectively rotatably connected with the connecting rod fixing member and the paddle clamp;
  • the paddle can drive the blade to slide along the main shaft with the rotor head, and is driven by the connecting rod during the sliding process to rotate relative to the rotor head to adjust the angle between the blade and the plane of rotation.
  • the spring can follow the axial direction of the rotor head. The movement is deformed.
  • the blades are two, and are symmetrically disposed on both sides of the main shaft.
  • the rotor head includes a cylinder, and a central portion of the cylinder is provided with a radial through hole through which the sleeve is sleeved.
  • the first end of the paddle is provided with a rotating portion, and the rotating portion is provided with an axial through hole, and a connecting screw passes through the through hole and is screwed into the end of the cylindrical body, and the rotating portion is A thrust bearing is disposed between the ends of the cylinder.
  • the tail end of the paddle is provided with two horizontal clamping arms, and the trailing end of the blade is located between the clamping arms and fixed by a screw that vertically penetrates the clamping arm and the blade.
  • the link fixing member is mounted on the top end of the main shaft, and the spring is respectively abutted against the link fixing member and the rotor head.
  • the outer side of the paddle protrudes from a shaft perpendicular to the main shaft
  • the connecting rod includes a shaft and a sleeve disposed at a bottom of the rod body and perpendicular thereto, the top of the rod body is hinged with the connecting rod fixing member, and the bottom portion passes through the shaft.
  • the sleeve is hinged to the shaft.
  • An aircraft comprising the above-described adaptive variable pitch propeller.
  • the propeller pitch can be adaptively changed with the change of flight speed, so that the aircraft can have higher efficiency at different speeds; the automatic variable pitch can be completed by mechanical structure, no need for control system and additional driving device, cost and technical requirements Low, simple mechanism and high reliability.
  • Figure 1 is a schematic overall view of an embodiment of the present invention
  • Figure 2 is an exploded perspective view of one embodiment of the present invention
  • Figure 3 is a schematic view of a small pitch of the present invention.
  • Figure 4 is a schematic illustration of the large pitch of the present invention.
  • FIG. 1 and 2 there is shown a related schematic view of an embodiment of the present invention, including a main shaft 1 and at least two blades 2, and a rotor head 3, a spring 4, a paddle 5, a connecting rod 6 and a connecting rod fixed Item 7.
  • the main shaft 1 is a main component of the rotation of the blade, preferably mounted on a base 101 provided with holes for connection to other components.
  • the rotor head 3 is sleeved on the main shaft 1 and can slide back and forth along the axial direction of the main shaft.
  • the connecting rod fixing member 7 is mounted on the main shaft 1.
  • the spring 4 is arranged between the rotor head 3 and the connecting rod fixing member 7, and the connecting rod is fixed.
  • the piece 7 is used on the one hand for mounting the connecting rod and on the other hand for limiting the spring.
  • the paddle 5 is used to realize the connection between the blade 2 and the rotor head 3, one end of which is fixed to the blade 2, the other end is rotatably connected with the rotor head 3, and the connecting rod 6 is rotated with the link fixing member 7 and the paddle 5, respectively. Connection, so that with the rotation of the blade 2, the paddle 5 can drive the blade 2 to slide along the main shaft 1 with the rotor head 3, and is driven by the link 6 during the sliding process to rotate relative to the rotor head 3 to adjust The angle between the blade 2 and the plane of rotation, and then adjust the pitch of the propeller.
  • the spring 4 can be deformed along with the axial movement of the rotor head 3, and the specific embodiment of the present embodiment will be described with reference to FIG. 3 and FIG.
  • the variable pitch process is used to realize the connection between the blade 2 and the rotor head 3, one end of which is fixed to the blade 2, the other end is rotatably connected with the rotor head 3, and the connecting rod 6 is rotated with the link fixing member 7 and the paddle 5, respectively
  • the pitch of the propeller will be automatically adjusted with the change of the speed and flight speed. For example, when the propeller speed (tangential speed) is rapidly increased to a certain value, the propeller tension is increased. On the other hand, the flying speed is increased, and on the other hand, the paddle 5 is raised along the main shaft to reduce the pitch, thereby causing the pulling force to gradually decrease, the aircraft resistance is gradually increased, and the speed increasing trend is gradually slowed down.
  • the spring will be in a compressed state, giving the rotor head a downward returning force.
  • the pulling force is reduced to a certain extent (ie, the pulling force is equal to the resistance)
  • a dynamic balance is also formed between the spring and the rotor head.
  • the flight speed, the rotational speed of the aircraft, The blade angle of attack and the propeller pull are the same, and the airplane is fixed at a speed.
  • the paddle clamp automatically adjusts its position on the main shaft under the action of the spring and the tension, and then changes the pitch to reach the balance again, ensuring that the aircraft can be compared at different flight speeds. High efficiency.
  • the blades are two and symmetrically disposed on both sides of the main shaft. It can be understood that the blades can also be three or more, and the rotor head can be simply adjusted. The shape and/or number of the paddle and the link mechanism are sufficient.
  • the rotor head 3 includes a cylindrical body 31.
  • the middle portion of the cylindrical body is provided with a radial through hole, and the through hole is sleeved on the main shaft.
  • the two ends of the cylindrical body have grooves, and the center of the groove is set. There are threaded holes.
  • the rotating end of the rotating portion 51 is also provided with a groove, and the center of the groove is provided with an axial through hole.
  • the threaded hole in the end of the body ensures that the paddle 5 can move up and down along the main axis integrally with the rotor head 3, and can rotate relative to the screw 501 with respect to the rotor head 3, and further, the concave portion between the rotating portion and the end of the barrel A thrust bearing 8 is provided in the groove.
  • the rear end of the paddle 5 is provided with two horizontal clamping arms 52, the trailing ends of which are located between the clamping arms 52 and are fixed by a screw 502 that extends perpendicularly through the clamping arms and the blades.
  • the link fixing member 7 is attached to the top end of the main shaft 1, and the spring 4 is abutted against the link fixing member 7 and the rotor head 3, respectively.
  • the outer side of the paddle 5 protrudes from a shaft 53 perpendicular to the main shaft.
  • the connecting rod 6 includes a rod body 61 and a sleeve 62 disposed at the bottom of the rod body 61 and perpendicular thereto.
  • the top of the rod body 61 is hinged to the rod fixing member 7, and the bottom portion passes through
  • the sleeve 62 is hinged to the rotating shaft 53 to form a link mechanism between the link fixing member 7, the link 6 and the rotor head 3.
  • the present invention also discloses an aircraft comprising the above-described adaptive variable pitch propeller.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne une hélice à pas variable adaptatif, et un aéronef. L'hélice comprend un arbre principal (1), des pales (2), une tête de rotor (3), un ressort (4), des éléments de fixation (5) de pale, des bielles (6) et un élément de fixation (7) de bielle. La tête de rotor (3) est emmanchée sur l'arbre principal (1) et reliée à celui-ci, et peut coulisser le long de celui-ci. L'élément de fixation (7) de bielle est monté sur une partie d'extrémité de l'arbre principal (1). Le ressort (4) est agencé entre la tête de rotor (3) et l'élément de fixation (7) de bielle. Les éléments de fixation (5) de pale comportent une première extrémité fixée à l'une des pales (2), et l'autre extrémité est reliée rotative à la tête de rotor (3). Les bielles (6) sont reliées rotatives à l'élément de fixation (7) de bielle et aux éléments de fixation (5) de pale. Les éléments de fixation (5) de pale peuvent entraîner le coulissement des pales (2) le long de l'arbre principal (1) avec la tête de rotor (3) en tant que corps intégré, et sont entraînés, pendant le mouvement de coulissement, par les bielles (6) pour tourner par rapport à la tête de rotor (3), de telle sorte que des angles des pales (2) par rapport au plan de rotation sont changés, et le ressort (4) peut présenter une déformation avec le mouvement axial de la tête de rotor (3). L'hélice à pas variable adaptatif peut modifier de façon adaptative le pas d'hélice avec le changement de vitesse de vol, permettant ainsi à un aéronef d'avoir une meilleure efficacité à différentes vitesses. L'hélice à pas variable adaptatif permet d'obtenir une variation de pas automatisée au moyen d'une structure mécanique, ce qui élimine le besoin d'un système de commande ou d'un dispositif d'entraînement supplémentaire.
PCT/CN2016/085192 2016-03-21 2016-06-08 Hélice à pas variable adaptatif, et aéronef WO2017161700A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201620217092.3 2016-03-21
CN201620217092.3U CN205499338U (zh) 2016-03-21 2016-03-21 一种自适应变距螺旋桨与飞机

Publications (1)

Publication Number Publication Date
WO2017161700A1 true WO2017161700A1 (fr) 2017-09-28

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PCT/CN2016/085192 WO2017161700A1 (fr) 2016-03-21 2016-06-08 Hélice à pas variable adaptatif, et aéronef

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CN (1) CN205499338U (fr)
WO (1) WO2017161700A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115246477A (zh) * 2022-09-21 2022-10-28 北京航空航天大学 一种转动自平衡的系留无人机
CN118144991A (zh) * 2024-02-21 2024-06-07 南昌三瑞智能科技股份有限公司 一种密封式桨距调节机构、旋翼及飞行器

Families Citing this family (13)

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Publication number Priority date Publication date Assignee Title
CN106915437A (zh) * 2017-04-14 2017-07-04 西安天问智能科技有限公司 旋翼飞行器内变桨距机构及旋翼飞行器
CN108438210B (zh) * 2017-12-07 2022-03-15 中国航空工业集团公司西安航空计算技术研究所 一种活塞式航空发动机螺旋桨变距方法
CN109050884B (zh) * 2018-06-21 2022-02-18 深圳市龙云创新航空科技有限公司 一种自动变距的螺旋桨旋翼头以及无人机
CN209467315U (zh) * 2018-11-06 2019-10-08 珠海隆华直升机科技有限公司 直升机尾桨变距调节系统及直升机
CN109278985B (zh) * 2018-11-20 2023-09-29 西安君晖航空科技有限公司 一种变桨距装置及其安装方法
CN109677602B (zh) * 2018-12-26 2020-08-07 张耀天 一种无人机机翼
CN109835468B (zh) * 2019-01-03 2022-04-26 上海歌尔泰克机器人有限公司 一种随飞行高度自动变距的变距机构和变距桨
CN110040240B (zh) * 2019-05-24 2023-09-22 安阳市豪克航空科技有限公司 单驱动螺旋桨变距、顺桨、停桨位锁定系统
CN110254694A (zh) * 2019-07-25 2019-09-20 埃游科技（深圳）有限公司 一种螺旋桨自动变矩机构
CN110834717B (zh) * 2019-11-21 2021-01-12 北京航空航天大学 一种自适应螺旋桨装置
CN115071957A (zh) * 2022-03-04 2022-09-20 任秋泽 一种可自动调螺距螺旋桨调节组件及装配方法
KR102641056B1 (ko) * 2022-03-08 2024-02-28 에어 앤드 에이치 에어로스페이스 인크 싸이클릭 스윙 로터 조립체
CN116280188B (zh) * 2023-04-18 2024-05-28 安阳市豪克航空科技有限公司 一种无轴承变距螺旋桨

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2569243B1 (fr) * 1984-08-17 1988-12-30 Aubertin Edouard Rotor a helice a pas variable, en particulier pour moteur eolien
CN1439805A (zh) * 2003-02-27 2003-09-03 哈尔滨工程大学 用于潮流能转换的直叶式自适应变螺距水轮机
KR200391653Y1 (ko) * 2005-05-20 2005-08-05 오원섭 가변피치 회전익 수직이착륙기
WO2013026963A1 (fr) * 2011-08-25 2013-02-28 Kokkelink Rene Felix Charles Système de rotor d'hélicoptère et hélicoptère comprenant un tel système de rotor
CN103161661A (zh) * 2011-12-09 2013-06-19 顾根新 机械式自动变矩风机
CN103786888A (zh) * 2014-01-17 2014-05-14 江苏艾锐泰克无人飞行器科技有限公司 变距飞行器
JP3201100U (ja) * 2015-09-09 2015-11-19 李宏富 マルチローター可変ピッチヘリコプター

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2569243B1 (fr) * 1984-08-17 1988-12-30 Aubertin Edouard Rotor a helice a pas variable, en particulier pour moteur eolien
CN1439805A (zh) * 2003-02-27 2003-09-03 哈尔滨工程大学 用于潮流能转换的直叶式自适应变螺距水轮机
KR200391653Y1 (ko) * 2005-05-20 2005-08-05 오원섭 가변피치 회전익 수직이착륙기
WO2013026963A1 (fr) * 2011-08-25 2013-02-28 Kokkelink Rene Felix Charles Système de rotor d'hélicoptère et hélicoptère comprenant un tel système de rotor
CN103161661A (zh) * 2011-12-09 2013-06-19 顾根新 机械式自动变矩风机
CN103786888A (zh) * 2014-01-17 2014-05-14 江苏艾锐泰克无人飞行器科技有限公司 变距飞行器
JP3201100U (ja) * 2015-09-09 2015-11-19 李宏富 マルチローター可変ピッチヘリコプター

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115246477A (zh) * 2022-09-21 2022-10-28 北京航空航天大学 一种转动自平衡的系留无人机
CN118144991A (zh) * 2024-02-21 2024-06-07 南昌三瑞智能科技股份有限公司 一种密封式桨距调节机构、旋翼及飞行器

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