WO2017049422A1 - Four-rotor aircraft with dynamical variations - Google Patents
Four-rotor aircraft with dynamical variations Download PDFInfo
- Publication number
- WO2017049422A1 WO2017049422A1 PCT/CN2015/000660 CN2015000660W WO2017049422A1 WO 2017049422 A1 WO2017049422 A1 WO 2017049422A1 CN 2015000660 W CN2015000660 W CN 2015000660W WO 2017049422 A1 WO2017049422 A1 WO 2017049422A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- blade
- rotor
- engine
- rotors
- aircraft
- Prior art date
Links
- 230000007246 mechanism Effects 0.000 claims description 18
- 238000013016 damping Methods 0.000 claims description 2
- 125000004122 cyclic group Chemical group 0.000 abstract 1
- 230000008859 change Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/20—Vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U40/00—On-board mechanical arrangements for adjusting control surfaces or rotors; On-board mechanical arrangements for in-flight adjustment of the base configuration
- B64U40/10—On-board mechanical arrangements for adjusting control surfaces or rotors; On-board mechanical arrangements for in-flight adjustment of the base configuration for adjusting control surfaces or rotors
Definitions
- the software can be programmed to make the quadrotor take off and land vertically, rotate, turn left and right, and roll. It can be more flexible than a helicopter. But the biggest drawback of the four-rotor is that it is very slow.
- the aircraft shown in Figure 1 can be seen as a deformed quadrotor, which is also convenient for helicopter functions. But the speed is much faster.
- a paddle is considered as the research object, and the paddle is the plane in which the blade rotates. That is, when the rotor rotates, the rotor has two variables, one is the lift generated by the rotational speed of the rotor, and the other is the torque. Now I want to change my mind and think of two paddles that are in a plane, mutually constant speed, reverse, and different axes as a whole. Looking at the whole from the outside, there is only one parameter lift, and no torque, because the two blades produce the same amount of torque and the opposite direction. It can be called a lift unit.
- Figure 1 is a front view of the aircraft
- Figure 2 is a schematic view of the rotation of the engine
- Figure 3 is a schematic illustration of rotor total moment adjustment.
- the engine is fixed at this point and the shaft is rotatable in the direction of the fuselage and fixed to the rotating mechanism.
- the wing engine 12 is provided with a hub 20 at the upper end of the engine main shaft 7, a paddle 2 is mounted on the hub 20, a bevel gear 19 is fixed on the paddle, and the bevel gear 19 is connected to the bevel gear 18, and the bevel gear 18 is fixed on one end of the long gear 4.
- the other end of the long gear 4 is connected to the output shaft 21 of the stepping motor 22.
- the long gear 4 passes through a hole in the middle of the main shaft 7. Install a damper brake device between the main shaft 7 and the hub.
- the slider 16 on the ball screw of the stepping motor 10 is connected to the connecting rod 14, and the connecting rod 14 is connected to the motor base 13, and the motor base 13 fixes the engine 12.
- the vertical take-off and landing of the aircraft can be realized, forward and backward, left and right corners, and after the take-off is completed, it can be converted into a mode flight of the rotorcraft, and can also be changed into a fixed-wing mode flight.
- the slider 16 is moved to the left and right along the ball screw, and the motor seat can be driven to perform circular motion at 11 o'clock. This allows the blades on the engine to be rotated to the desired angle.
- the motor shaft 21 drives the long gear 4 to rotate
- the long gear 4 drives the bevel gear 18,
- the bevel gear 18 drives the bevel gear 19, and the blade 2 can rotate along the axial direction of the blade, which can be 360. Rotate freely within degrees.
- Figure 1 is a front view of the aircraft.
- the right side of the fuselage and the left side do not generate torque.
- the balance between the front and the back is to adjust the angle between the four blades and the ground: four blades (2, 17, 23, 24) are simultaneously adjusted synchronously, and the adjustment of the lift force is adjusted to a helicopter with the newly invented total moment adjustment mechanism 3.
- the mode is complete. This completely replaces the complex cycle variation and total moment adjustment mechanism of the current helicopter.
- the blades 2 and the blades 17 rotate in opposite directions and the rotational speed is the same, there is no difference in the force of the forward and backward blades of the helicopter, which may cause rolling moments, causing the helicopter to roll. In this way, the blade does not need to swing down the rotating surface, and there is no need for a seesaw and a pre-lag fully twisted mechanism.
- the second stage accelerates the leveling: after the aircraft leaves the ground for a certain distance, the rotation mechanism adjusts the blade 17 and the blade 23 to tilt toward the head, and the blade 2 and the blade 24 remain, and the blade 17 continues to rotate.
- the aircraft can slowly accelerate, the blade 17 and the blade 23 are constantly tilted, the thrust is greater, and the speed of the aircraft is greater.
- the lift generated by the wing 8 is slowly increased, and the blade 2 and the blade 24 can be slowly decelerated to reduce energy consumption. Until the blade 2 and the blade 24 are stopped.
- the paddles 17 and the blades 23 are turned to the horizontal direction.
- the third stage becomes the rotorcraft mode flight: the blade 2 and the blade 24 are adjusted to the rotorcraft mode by the total moment adjustment mechanism, and are separated from the engine, at which time the blades are free to rotate.
- the fourth stage fixed-wing mode At this time, the damper brake device can be activated to keep the blade 2 and the blade 24 fixed relative to the fuselage, the blade 17 and the blade 23 are unchanged, and the thrust is continued to be fixed. Wing mode.
- the aircraft needs to be retracted, after the take-off, it is only necessary to rotate the blade 17 and the blade 23 along the fuselage toward the tail by the rotating mechanism 6, and the aircraft has a backward thrust. This way the aircraft can be retreated.
Abstract
Description
Claims (1)
- 一种动态变化的四旋翼机,其特征在于:A dynamically changing quadrotor is characterized by:1,包括在机身的两边对称的安装两个旋转方向相反的旋翼2和旋翼17,旋翼23和旋翼24。旋翼2和旋翼23是一个旋转方向,旋翼17和旋翼24是另一个相反的旋转方向。旋翼也能换成螺旋桨,如果换成了螺旋桨,就可去掉总矩调整机构3。旋翼也可以安装相对与机身对称的8个,左边四个,右边四个。1, comprising two rotors 2 and rotors 17, rotors 23 and rotors 24 that are symmetrically mounted on opposite sides of the fuselage. The rotor 2 and the rotor 23 are in one direction of rotation, and the rotor 17 and the rotor 24 are in the opposite direction of rotation. The rotor can also be replaced by a propeller. If the propeller is replaced, the total moment adjustment mechanism 3 can be removed. The rotor can also be mounted with 8 symmetrical objects, four on the left and four on the right.2,包括在每个发动机上都安装旋转机构6,内含步进电机19,滚珠丝杠15,滑块16,连杆14,电机座13,和发动机固定在该点并以该轴沿机身方向可旋转的并固定在旋转机构上的轴11。2, comprising installing a rotating mechanism 6 on each engine, comprising a stepping motor 19, a ball screw 15, a slider 16, a connecting rod 14, a motor seat 13, and an engine fixed at the point and along the axis A shaft 11 that is rotatable in the body and fixed to the rotating mechanism.3,包括总矩调整机构3,内含步进电机22,电机轴21,长齿轮4,伞齿轮18,伞齿轮19。3. The total torque adjustment mechanism 3 includes a stepping motor 22, a motor shaft 21, a long gear 4, a bevel gear 18, and a bevel gear 19.4,包括阻尼刹车装置。 4, including damping brakes.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/CN2015/000660 WO2017049422A1 (en) | 2015-09-24 | 2015-09-24 | Four-rotor aircraft with dynamical variations |
PCT/CN2016/000248 WO2017049806A1 (en) | 2015-09-24 | 2016-05-09 | Quadrotor jet aircraft with simultaneously dynamically varying pitches |
CN201680055534.1A CN108025810B (en) | 2015-09-24 | 2016-05-09 | Four-rotor jet aircraft with inclination angle capable of being dynamically changed simultaneously |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/CN2015/000660 WO2017049422A1 (en) | 2015-09-24 | 2015-09-24 | Four-rotor aircraft with dynamical variations |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2017049422A1 true WO2017049422A1 (en) | 2017-03-30 |
Family
ID=58385453
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/CN2015/000660 WO2017049422A1 (en) | 2015-09-24 | 2015-09-24 | Four-rotor aircraft with dynamical variations |
PCT/CN2016/000248 WO2017049806A1 (en) | 2015-09-24 | 2016-05-09 | Quadrotor jet aircraft with simultaneously dynamically varying pitches |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/CN2016/000248 WO2017049806A1 (en) | 2015-09-24 | 2016-05-09 | Quadrotor jet aircraft with simultaneously dynamically varying pitches |
Country Status (2)
Country | Link |
---|---|
CN (1) | CN108025810B (en) |
WO (2) | WO2017049422A1 (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN108827302A (en) * | 2018-04-24 | 2018-11-16 | 大连理工大学 | Multi-rotor aerocraft air navigation aid based on rotor tachometric survey |
WO2019062140A1 (en) * | 2017-09-30 | 2019-04-04 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
CN110092000A (en) * | 2019-06-04 | 2019-08-06 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of all-electric tilting rotor wing unmanned aerial vehicle |
CN110422328A (en) * | 2019-08-26 | 2019-11-08 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of tilting rotor wing unmanned aerial vehicle linear power configuration method and structure |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104210655A (en) * | 2014-09-03 | 2014-12-17 | 西北农林科技大学 | Double-rotor-wing unmanned plane |
RU2547950C1 (en) * | 2013-12-19 | 2015-04-10 | Общество с ограниченной ответственностью научно-производственное предприятие "Измерон-В" (ООО НПП "Измерон-В") | Quadrocopter |
CN204279938U (en) * | 2014-10-27 | 2015-04-22 | 深圳九星智能航空科技有限公司 | The rotor unmanned aircraft that blade can be dismantled separately |
CN204279937U (en) * | 2014-10-27 | 2015-04-22 | 深圳九星智能航空科技有限公司 | The collapsible double-rotor aerobat overhang of lower blade |
CN104859836A (en) * | 2015-05-06 | 2015-08-26 | 浙江工业大学之江学院 | Unmanned aerial vehicle |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE202005003894U1 (en) * | 2005-03-10 | 2005-06-30 | Schraufstetter, Wilfried | Vertical take off and landing aircraft has lift and propulsion producing rotors, whose axes are not coaxial, and a control pod and main coupling unit linked by control lines via carrying pipes to rotor couplings |
CN1907806A (en) * | 2005-08-02 | 2007-02-07 | 韩培洲 | helicopter with tilted front rotary wing |
US7861967B2 (en) * | 2008-04-25 | 2011-01-04 | Abe Karem | Aircraft with integrated lift and propulsion system |
CN101314409B (en) * | 2008-07-10 | 2012-04-18 | 周武双 | Swallow type inclined rotation rotorcraft |
KR20100026130A (en) * | 2008-08-29 | 2010-03-10 | 임채호 | Taking off and landing airplane using variable rotary wings |
EP2406131B1 (en) * | 2009-03-12 | 2016-05-11 | Bell Helicopter Textron Inc. | Tiltrotor aircraft and method of controlling yaw movement therefor |
PT2551198E (en) * | 2011-07-29 | 2013-12-27 | Agustawestland Spa | Convertiplane |
CN202728576U (en) * | 2012-02-10 | 2013-02-13 | 田瑜 | Transformable composite aircraft formed by fixed wing and electric multi-propeller |
DE102013109392A1 (en) * | 2013-08-29 | 2015-03-05 | Airbus Defence and Space GmbH | Fast-flying, vertically launchable aircraft |
CN103935511A (en) * | 2014-04-15 | 2014-07-23 | 西安交通大学 | Tilt-three-rotor craft |
CN104369863A (en) * | 2014-10-31 | 2015-02-25 | 吴建伟 | Composite vertical take-off/landing aircraft |
-
2015
- 2015-09-24 WO PCT/CN2015/000660 patent/WO2017049422A1/en active Application Filing
-
2016
- 2016-05-09 CN CN201680055534.1A patent/CN108025810B/en not_active Expired - Fee Related
- 2016-05-09 WO PCT/CN2016/000248 patent/WO2017049806A1/en active Application Filing
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2547950C1 (en) * | 2013-12-19 | 2015-04-10 | Общество с ограниченной ответственностью научно-производственное предприятие "Измерон-В" (ООО НПП "Измерон-В") | Quadrocopter |
CN104210655A (en) * | 2014-09-03 | 2014-12-17 | 西北农林科技大学 | Double-rotor-wing unmanned plane |
CN204279938U (en) * | 2014-10-27 | 2015-04-22 | 深圳九星智能航空科技有限公司 | The rotor unmanned aircraft that blade can be dismantled separately |
CN204279937U (en) * | 2014-10-27 | 2015-04-22 | 深圳九星智能航空科技有限公司 | The collapsible double-rotor aerobat overhang of lower blade |
CN104859836A (en) * | 2015-05-06 | 2015-08-26 | 浙江工业大学之江学院 | Unmanned aerial vehicle |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2019062140A1 (en) * | 2017-09-30 | 2019-04-04 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
CN108827302A (en) * | 2018-04-24 | 2018-11-16 | 大连理工大学 | Multi-rotor aerocraft air navigation aid based on rotor tachometric survey |
CN110092000A (en) * | 2019-06-04 | 2019-08-06 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of all-electric tilting rotor wing unmanned aerial vehicle |
CN110422328A (en) * | 2019-08-26 | 2019-11-08 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of tilting rotor wing unmanned aerial vehicle linear power configuration method and structure |
Also Published As
Publication number | Publication date |
---|---|
CN108025810A (en) | 2018-05-11 |
WO2017049806A1 (en) | 2017-03-30 |
CN108025810B (en) | 2022-01-04 |
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