CN203780797U - Double-motor variable-pitch multi-rotor aircraft - Google Patents
Double-motor variable-pitch multi-rotor aircraft Download PDFInfo
- Publication number
- CN203780797U CN203780797U CN201420133586.4U CN201420133586U CN203780797U CN 203780797 U CN203780797 U CN 203780797U CN 201420133586 U CN201420133586 U CN 201420133586U CN 203780797 U CN203780797 U CN 203780797U
- Authority
- CN
- China
- Prior art keywords
- pitch
- variable
- rotor
- propulsion source
- frame
- 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.)
- Expired - Fee Related
Links
Abstract
The utility model discloses a double-motor variable-pitch multi-rotor aircraft. The double-motor variable-pitch multi-rotor aircraft comprises a rack, at least two power sources, a transmission mechanism and at least four groups of variable-pitch rotor mechanisms, wherein at least two power sources are arranged on the rack; the transmission mechanism is meshed with the power sources; at least four groups of variable-pitch rotor mechanisms are symmetrically arranged on the rack, connected with the transmission mechanism and driven by the transmission mechanism. By virtue of the power sources, reverse rotation power is respectively fed to the variable-pitch rotor mechanisms, so that the variable-pitch rotor mechanisms are isomerously driven respectively to form lifting force; meanwhile, the power sources are selectively used for providing different rotation speeds and matched with the corresponding variable-pitch rotor mechanisms to realize differential control at different pitch angles, thereby accelerating the action response time in the flight and the sensitivity of yaw control of the double-motor variable-pitch multi-rotor aircraft.
Description
Technical field
The utility model has about rotor craft technical field, particularly can shorten rotor craft, a kind of double motor variable-pitch multi-rotor aerocraft of action response time and lifting driftage manipulation sensitivity when flight.
Background technology
Known many rotor structures, as No. M453639 eight rotor disaster relief cross-country car folder thing robots of TaiWan, China patent announcement, the content being disclosed from known front case, each rotor separate connection one electric motor, and drive rotor action by electric motor, make rotor produce corresponding lift, relend the control by each electric motor rotating speed, and reach when flight direction transformation and the object of flight.
Though case can be reached the objects such as flight, stagnant sky before M453639, many not attaining improve part but still have in structure, for example, each rotor needs independently to arrange an electric motor and motor speed controller, except electric motor and the increase of motor speed controller cost, also cause the increase of overall weight, and excessively power consumption cannot flying for long time.Moreover, the rotor of known front case cannot be made variable-pitch angle and drive, therefore can only be merely by the rotating speed mode of controlling electric motor, flare maneuver while adjusting flight, therefore, all flare maneuvers only can reach by speed difference, tend to cause under severe or high wind environment, the phenomenons such as control response and speed of response are not good, this disappearance will cause flying time because action response is too slow, so that cannot real-time response, or manipulation flight skill difficulty is high, and the disappearance such as environment and scope of limitation application.
For solving the disappearance of case before M453639, before industry separately proposes No. M388969, case, as solution, is utilized the mechanisms such as single power source mate gear and belt to be connected multiple rotors, and is made each rotor form synchronous driving.Mate again servomotor and make each rotor can optionally do pitch adjustment, to reach flare maneuver control.But many rotors provide propulsion source by single motor, therefore the rotating speed of each rotor is consistent, makes response time and the substantivity of yawed flight action still restricted, more cannot coordinate different rotating speeds to obtain yawed flight action response ability faster, moreover; Each rotor rotating Vortex has been ignored reactive torque problem.According to the main rotor general knowledge of general helicopter type, main rotor is responsible for lift, and afterbody can install a small-sized vertical end rotor and be responsible for the reactive torque that offset by the level of rotor produces.Although the reactive torque mode of offset by the level of rotor has various ways design, but the problem of the reactive torque that can produce when main rotor rotation is identified, the most obvious way is to provide the main rotor of another hand of rotation and is offset, and before No. M388969 in the powerdriven annexation of case, each main rotor is all same direction turn design.On the cost of motor, be to have reduced, in the counteracting of reactive torque, there is no relevant treatment means, though still can ascend to heaven, but; On the manipulation sensitieness of the handling and flight of entirety, be less-than-ideal.
Utility model content
The purpose of this utility model is to provide a kind of double motor variable-pitch multi-rotor aerocraft, it is except can be by changing each rotor angle of inclination mode (the pitch adjustment of rotor) change of flight state, more can be further by the rotating speed that changes each rotor, to increase action response speed when yawed flight, so reach be easy to manipulation, overall volume is dwindled and can strengthen carrier volume and offset many effects such as reactive torque.
In order to achieve the above object, the utility model provides a kind of double motor variable-pitch multi-rotor aerocraft, and it mainly comprises:
One frame;
At least two propulsions source, be arranged at this frame, this propulsion source comprises the first propulsion source that one first hand of rotation is provided, and provide the second propulsion source of one second hand of rotation, and the mouth of this first propulsion source is socketed with one first driven wheel, the mouth of this second propulsion source is socketed with one second driven wheel;
One transmission device, what comprise each other interlock not is arranged at that one of this frame cogs and a lower gear, and this cogs and this lower gear is meshed with corresponding this first driven wheel and this second driven wheel respectively; And
At least four group variable-pitch rotor mechanisms, respectively this variable-pitch rotor mechanism symmetry be arranged at this frame, and cog with this respectively and this lower gear engages with symmetrical quantity, wherein, respectively this variable-pitch rotor mechanism comprises a ring gear, one is connected in series the belt pulley of interlock with this ring gear, one end is fixedly arranged on the support tube of this frame, one is hubbed at the rotating shaft unit of this support tube other end, one is hubbed at the variable-pitch rotor clip device in this rotating shaft unit, two are connected in the just contrary rotor of this variable-pitch rotor clip device, one connects the belt of this belt pulley and this rotating shaft unit, and one drive this variable-pitch rotor clip device to make the servomotor of pitch control.
This cog and this lower gear overlapped in this frame, and there is a diff-H.
This first propulsion source adopts a motor or an engine.
This second propulsion source adopts a motor or an engine.
This variable-pitch rotor mechanism cogs and engages by this ring gear and this.
This variable-pitch rotor mechanism engages with this lower gear by this ring gear.
Adopt after such scheme, the utility model double motor variable-pitch multi-rotor aerocraft provides respectively contrary extremely each variable-pitch rotor mechanism of rotary power by each propulsion source, make the driving respectively of the numbers such as each variable-pitch rotor mechanism form lift, and optionally make each propulsion source that different rotating speeds is provided, to coordinate corresponding each variable-pitch rotor mechanism pitch drives, the action response time while accelerating the flight of the utility model double motor variable-pitch multi-rotor aerocraft and the sensitivity of manipulation.
Brief description of the drawings
Fig. 1 is the utility model double motor variable-pitch multi-rotor aerocraft embodiment schematic perspective view;
Fig. 2 is Local Members schematic diagram embodiment illustrated in fig. 1;
Fig. 3 is another visual angle Local Members schematic diagram embodiment illustrated in fig. 1;
Fig. 4 is Local Members decomposing schematic representation embodiment illustrated in fig. 1.
Detailed description of the invention
Below please refer to correlative type and further illustrate the utility model double motor variable-pitch multi-rotor aerocraft structure embodiment.For ease of understanding the utility model embodiment, below same components adopt same-sign indicate explanation.
Refer to shown in Fig. 1 to Fig. 4, the utility model double motor variable-pitch rotor craft structure, it mainly comprises: a frame 100, be located at the propulsion source 200 of frame 100 at least two, one transmission device 300 engaging with each propulsion source 200, being disposed at frame 100 and being connected with transmission device 300 and the variable-pitch rotor mechanism 400 that is driven by it of at least four group symmetries, provide respectively contrary extremely each variable-pitch rotor mechanism 400 of rotary power by each propulsion source 200, what make each variable-pitch rotor mechanism 400 numbers such as grade produces respectively the lift that matches and just, reactive torque, and by optionally rotation speed change of each propulsion source 200, to coordinate the 400 pitch controls of corresponding variable-pitch rotor mechanism, action response time while shortening the utility model yawed flight, promote the sensitieness of manipulation.
Above-mentioned propulsion source 200, be arranged at frame 100, comprise the first propulsion source 220 that one first hand of rotation is provided, and second propulsion source 240 that the second hand of rotation is provided, and corresponding corresponding one second driven wheel 242 that connects of mouth that connects one first driven wheel 222, the second propulsion source 240 of the mouth of the first propulsion source 220.When enforcement, each propulsion source 200 can be motor or engine.
Above-mentioned transmission device 300, comprise serial connection but not one of the frame 100 that is arranged at of interlock cog 320 and a lower gear 340, and cog 320, the first plane and the second plane that lower gear 340 is arranged at respectively tool height potential difference.
Above-mentioned each variable-pitch rotor mechanism 400, the symmetrical frame 100 that is disposed at, wherein, each variable-pitch rotor mechanism 400 comprises a ring gear 410 engaging with transmission device 300, one is connected in series the belt pulley 420 of interlock with ring gear 410, one end is fixedly arranged on the support tube 430 of frame 100, one is hubbed at the rotating shaft unit 440 of support tube 430 other ends, one be located in rotating shaft unit 440 and relatively rotating shaft unit 440 do beat move variable-pitch rotor clip device 442, be located at the just contrary rotor 450 at variable-pitch rotor clip device 442 two ends for two, and each just contrary rotor 450 is subject to the motion of rotating shaft unit 440 and synchronous rotary interlock, the belt 470 of one connection rotating shaft unit 440 and belt pulley 420, belt transmits the power of belt pulley 420, and interlock rotating shaft unit 440 affects just contrary rotor 450 to rotate, and the servomotor 460 being connected with variable-pitch rotor clip device 442, servomotor 460 is controlled by user and is optionally driven variable-pitch rotor clip device 442 to carry out pitch control, this pitch control refers to regulate the wing plate angle of two just contrary rotors 450 to change, to obtain the control (prior art) of just contrary rotor 450 lift.When enforcement, each variable-pitch rotor mechanism 400 taking etc. several as one group, respectively by ring gear 410 and transmission device 300 cog 320 or lower gear 340 engage, and servomotor 460 is known telecontrol engineering, therefore seldom repeat.
Be a kind of double motor variable-pitch multi-rotor aerocraft that the utility model one preferred embodiment provides therefore above-mentioned, the introduction of each portion member and assembling mode thereof, is then described as follows its handling characteristics again:
When enforcement, transmission device 300, adopts the design of diff-H (the first plane, the second planimetric position), therefore can make the member engaging with transmission device 300, the configuration of relative work solid, significantly reduces the shared plan area of each member.
Utilize the first propulsion source 220, the second propulsion source 240 that the power of the first hand of rotation and the second hand of rotation is provided respectively, and the first hand of rotation, the second hand of rotation are contrary, make the second driven wheel 242 of the first driven wheel 222, second propulsion source 240 mouths of the first propulsion source 220 mouths drive respectively that engagement cogs 320, lower gear 340, and interlock with cog 320, each variable-pitch rotor mechanism 400 of the corresponding engagement of lower gear 340.
The ring gear of each variable-pitch rotor mechanism 400 is cogged 320, lower gear 340 drives, and synchronous interlock belt pulley 242, and transmit the first propulsion source 220 by belt 470, the power of the second propulsion source 240 and interlock rotating shaft unit 440 is moved, to drive variable-pitch rotor clip device 442 and just contrary rotor 450 to rotate, and start servomotor 460 and control variable-pitch rotor clip device 442 set in rotating shaft unit 440 and carry out pitch control, the wing plate angle of the just contrary rotor 450 of this pitch control adjustable two changes, produce lift to obtain just contrary rotor 450.Because adopting symmetrical quantity, each variable-pitch rotor mechanism 400 is connected with the first propulsion source 220, the second propulsion source 240, the rotor that produces respectively first direction and second direction of each variable-pitch rotor mechanism 400 numbers such as grade is driven, so as to the forward and reverse moment of torsion of cancelling out each other.
Coordinate remote control equipment (RCE) (known techniques, not shown in the figures) driving of remote control servomotor 460, carry out pitch control with the variable-pitch rotor clip device 442 of adjusting in rotating shaft unit 440, and then each wing plate angle of inclination of the just contrary rotor 450 of change, the lift that just contrary rotor 450 is produced because of rotation, by the tilt variation of each wing plate and be converted to the strength of promotion, and can coordinate the adjustment of rotational speed of the first propulsion source 220, the second propulsion source 240, accelerate controller performance and response time that the utility model double motor variable-pitch multi-rotor aerocraft drives.
The above explanation, it is only preferred embodiments of the present utility model, be intended to feature clearly of the present utility model, not in order to limit the scope of the utility model embodiment, the equalization that those skilled in the art in the art do according to the utility model changes, and the change known of those skilled in that art, must belong to the scope that the utility model is contained.
Claims (6)
1. a double motor variable-pitch multi-rotor aerocraft, is characterized in that: mainly comprise:
One frame;
At least two propulsions source, be arranged at this frame, this propulsion source comprises the first propulsion source that one first hand of rotation is provided, and provide the second propulsion source of one second hand of rotation, and the mouth of this first propulsion source is socketed with one first driven wheel, the mouth of this second propulsion source is socketed with one second driven wheel;
One transmission device, what comprise each other interlock not is arranged at that one of this frame cogs and a lower gear, and this cogs and this lower gear is meshed with corresponding this first driven wheel and this second driven wheel respectively; And
At least four group variable-pitch rotor mechanisms, respectively this variable-pitch rotor mechanism symmetry be arranged at this frame, and cog with this respectively and this lower gear engages with symmetrical quantity, wherein, respectively this variable-pitch rotor mechanism comprises a ring gear, one is connected in series the belt pulley of interlock with this ring gear, one end is fixedly arranged on the support tube of this frame, one is hubbed at the rotating shaft unit of this support tube other end, one is hubbed at the variable-pitch rotor clip device in this rotating shaft unit, two are connected in the just contrary rotor of this variable-pitch rotor clip device, one connects the belt of this belt pulley and this rotating shaft unit, and one drive this variable-pitch rotor clip device to make the servomotor of pitch control.
2. double motor variable-pitch multi-rotor aerocraft as claimed in claim 1, is characterized in that: this cog and this lower gear overlapped in this frame, and there is a diff-H.
3. double motor variable-pitch multi-rotor aerocraft as claimed in claim 1, is characterized in that: this first propulsion source adopts a motor or an engine.
4. double motor variable-pitch multi-rotor aerocraft as claimed in claim 1, is characterized in that: this second propulsion source adopts a motor or an engine.
5. double motor variable-pitch multi-rotor aerocraft as claimed in claim 1, is characterized in that: this variable-pitch rotor mechanism cogs and engages by this ring gear and this.
6. double motor variable-pitch multi-rotor aerocraft as claimed in claim 1, is characterized in that: this variable-pitch rotor mechanism engages with this lower gear by this ring gear.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420133586.4U CN203780797U (en) | 2014-03-24 | 2014-03-24 | Double-motor variable-pitch multi-rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420133586.4U CN203780797U (en) | 2014-03-24 | 2014-03-24 | Double-motor variable-pitch multi-rotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203780797U true CN203780797U (en) | 2014-08-20 |
Family
ID=51317008
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420133586.4U Expired - Fee Related CN203780797U (en) | 2014-03-24 | 2014-03-24 | Double-motor variable-pitch multi-rotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203780797U (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104309802A (en) * | 2014-10-21 | 2015-01-28 | 深圳大学 | Fuel power quadrotor unmanned aerial vehicle |
| CN104443372A (en) * | 2014-11-26 | 2015-03-25 | 大连宏翼航空科技发展有限公司 | Variable-pitch and multi-rotor aircraft adopting multi-engine oil drive |
| CN104986328A (en) * | 2015-06-24 | 2015-10-21 | 辽宁锐翔通用航空有限公司 | Variable-propeller-pitch multi-rotor aircraft driven by multiple oil engines |
| CN105015769A (en) * | 2015-08-26 | 2015-11-04 | 许博男 | Multi-rotor craft |
| CN106043680A (en) * | 2016-07-28 | 2016-10-26 | 易瓦特科技股份公司 | Aviation engine |
| CN106467166A (en) * | 2015-08-21 | 2017-03-01 | 李少泽 | A kind of multi-rotor aerocraft |
| CN106647789A (en) * | 2016-12-23 | 2017-05-10 | 徐州飞梦电子科技有限公司 | UAV maximum inclination control method |
| CN106828906A (en) * | 2017-03-27 | 2017-06-13 | 必扬星环（北京）航空科技有限公司 | Double hair turbine wheel shaft power depopulated helicopters |
| JP6471255B1 (en) * | 2018-04-11 | 2019-02-13 | 株式会社Ｔｋｋワークス | Multicopter |
-
2014
- 2014-03-24 CN CN201420133586.4U patent/CN203780797U/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104309802A (en) * | 2014-10-21 | 2015-01-28 | 深圳大学 | Fuel power quadrotor unmanned aerial vehicle |
| CN104443372A (en) * | 2014-11-26 | 2015-03-25 | 大连宏翼航空科技发展有限公司 | Variable-pitch and multi-rotor aircraft adopting multi-engine oil drive |
| CN104986328A (en) * | 2015-06-24 | 2015-10-21 | 辽宁锐翔通用航空有限公司 | Variable-propeller-pitch multi-rotor aircraft driven by multiple oil engines |
| CN106467166A (en) * | 2015-08-21 | 2017-03-01 | 李少泽 | A kind of multi-rotor aerocraft |
| CN105015769A (en) * | 2015-08-26 | 2015-11-04 | 许博男 | Multi-rotor craft |
| CN106043680A (en) * | 2016-07-28 | 2016-10-26 | 易瓦特科技股份公司 | Aviation engine |
| CN106647789A (en) * | 2016-12-23 | 2017-05-10 | 徐州飞梦电子科技有限公司 | UAV maximum inclination control method |
| CN106828906A (en) * | 2017-03-27 | 2017-06-13 | 必扬星环（北京）航空科技有限公司 | Double hair turbine wheel shaft power depopulated helicopters |
| JP6471255B1 (en) * | 2018-04-11 | 2019-02-13 | 株式会社Ｔｋｋワークス | Multicopter |
| WO2019198256A1 (en) * | 2018-04-11 | 2019-10-17 | 株式会社Ｔｋｋワークス | Multicopter |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203780797U (en) | Double-motor variable-pitch multi-rotor aircraft | |
| CN104760696B (en) | A kind of multi-rotor aerocraft | |
| US9616994B2 (en) | Asymmetric multirotor helicopter | |
| CN203318676U (en) | Coaxial double-wing aircraft with moving centre-of-gravity ball | |
| CN100391790C (en) | Multi-rotor aerocraft | |
| CN102951290A (en) | Non-co-axial multi-rotor aircraft and attitude control method thereof | |
| CN103991539A (en) | Device for driving multiple rotors of airplane | |
| CN106585976A (en) | Aircraft layout of tilt rotors/lift fan during high-speed long endurance | |
| CN204979218U (en) | Many rotors of oil -electricity hybrid vehicle unmanned vehicles | |
| CN104691753A (en) | Oil-relay multi-rotor helicopter driving system | |
| CN203094440U (en) | Non-coaxial multi-rotor wing air vehicle | |
| CN204527626U (en) | Bevel gear set, shaft drive four rotor wing unmanned aerial vehicle | |
| CN203767067U (en) | Centre-of-gravity shift yawing device for helicopters | |
| CN102490897A (en) | Multi-driving embedded rotor manned helicopter | |
| CN104973241A (en) | Unmanned aerial vehicle with main and auxiliary multi-rotor structure | |
| CN204776020U (en) | Unmanned vehicles with many rotors of major -minor structure | |
| CN207997982U (en) | Screw mechanism and VTOL fixed wing unmanned aerial vehicle vert | |
| CN204660022U (en) | A kind of eight-rotary wing aircraft | |
| CN105015768A (en) | Multi-rotor aircraft | |
| CN207466966U (en) | A kind of dynamic displacement quadrotor unmanned plane of oil | |
| CN203996887U (en) | A kind of oil moves multirotor helicopter drive system | |
| CN110615094A (en) | Multi-shaft multi-directional tilting type multi-rotor aircraft transmission system | |
| EP3737609A1 (en) | Transmission system for aircraft structure | |
| CN201362363Y (en) | Saucer-shaped aircraft | |
| CN104943859A (en) | Unmanned helicopter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140820 Termination date: 20180324 |