CN203958613U - The coaxial multi-rotor aerocraft of duct - Google Patents
The coaxial multi-rotor aerocraft of duct Download PDFInfo
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- CN203958613U CN203958613U CN201420303405.8U CN201420303405U CN203958613U CN 203958613 U CN203958613 U CN 203958613U CN 201420303405 U CN201420303405 U CN 201420303405U CN 203958613 U CN203958613 U CN 203958613U
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- 230000005540 biological transmission Effects 0.000 claims description 13
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 9
- 229910052799 carbon Inorganic materials 0.000 claims description 9
- 238000005096 rolling process Methods 0.000 claims description 5
- 230000008859 change Effects 0.000 abstract description 4
- 238000005516 engineering process Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- TVEXGJYMHHTVKP-UHFFFAOYSA-N 6-oxabicyclo[3.2.1]oct-3-en-7-one Chemical compound C1C2C(=O)OC1C=CC2 TVEXGJYMHHTVKP-UHFFFAOYSA-N 0.000 description 1
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
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- 238000012544 monitoring process Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
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Abstract
The utility model discloses the coaxial multi-rotor aerocraft of a kind of duct, belong to special device field.Comprise housing construction, power system and control system, housing construction comprises that center duct, main rotor and several are evenly distributed on the secondary rotor of duct periphery, center; Main rotor comprises screw propeller and lower screw propeller, and upper and lower screw propeller is fixed in the duct of center, being centered close on same vertical axis of upper and lower screw propeller, and hand of rotation is contrary; The outside connection of rotating device of supporting construction, secondary rotor is by being connected with wheel word by folding and unfolding rocking arm, and wheel word is controlled rocking arm and is driven the point of connection rotation with supporting construction around it of secondary rotor.Secondary rotor in the utility model all can freely be rotated movement, makes aircraft according to flight, to need the lift distribution of change of flight device, has realized the good maneuvering performance of aircraft; Secondary rotor can be taken in to the inside of center duct, to dwindle the volume of aircraft, is convenient in narrow spaceflight.
Description
Technical field
The present invention relates to a kind of aircraft, the coaxial multi-rotor aerocraft of especially a kind of duct, belongs to special device field.
Background technology
At present, multi-rotor aerocraft has good manoevreability and handling, but it does not have the ability that wheelbase changes in-flight, and the lift that only relies on rotor to produce moves, and flight efficiency is lower; Though and the manoevreability of duct coaxial rotor flying vehicle and handling not as multi-rotor aerocraft, it produces by duct and rotor the lift that lift produces considerably beyond multi-rotor aerocraft jointly.Therefore the advantage in conjunction with this two classes aircraft combines the large lift efficiency of duct coaxial aircraft and the control stiffness of multi-rotor aerocraft, becomes the emphasis direction of current rotor craft research.
On September 25th, 2013, Chinese invention patent application CN103318406A discloses a kind of combined type rotor craft, comprise aircraft body, energy source device, hard disk and control setup, aircraft body comprises main thruster and some auxiliary propellers, main thruster comprises main rotor one, main rotor two and main duct, main rotor one and main rotor two are fixed in main duct by main duct bracing frame, the outer rim of main duct bracing frame is positioned at main duct inside and is arranged with some vertical pipe links, the bottom of vertical pipe link all outside level is provided with cantilever, the outer end of cantilever is equipped with auxiliary propeller.It has adopted the comprehensive of multiple rotor flying mode, alerting ability, stability and the reliability of flight efficiency and aircraft have been improved, but its cannot change of flight device in flight course whole flight axis distance, maneuvering performance is poor, cannot adapt to the flight requirement of specific occasion.
Summary of the invention
Technical matters to be solved by this invention is to overcome prior art defect, provides a kind of flight maneuver performance the good coaxial multi-rotor aerocraft of duct requiring to adapt to specific occasion flight.
In order to solve the problems of the technologies described above, the coaxial multi-rotor aerocraft of duct provided by the invention, comprises housing construction, power system and control system, and described housing construction comprises that center duct, main rotor and several are evenly distributed on the secondary rotor of duct periphery, center; Described main rotor comprises screw propeller and lower screw propeller, described upper screw propeller and lower screw propeller by support construction supports in the duct of center, being centered close on same vertical axis of described upper screw propeller and lower screw propeller, hand of rotation is contrary, the outside of described supporting construction is fixedly connected with wheel word, described secondary rotor is connected with wheel word by rocking arm, and described wheel word is controlled rocking arm and driven the point of connection rotation with supporting construction around it of secondary rotor.
In the present invention, described wheel word comprises steering wheel, bearing, arm revolving gear and rocking arm strut bar, and described steering wheel, bearing are all fixed in supporting construction, and bearing outside switches through moving gear; rocking arm strut bar is fixed on arm revolving gear, described arm revolving gear and the engagement of steering wheel gear.
In the present invention, the junction of described rocking arm and secondary rotor is provided with rolling brake ring.
In the present invention, described control system is arranged on the bottom of supporting construction, comprises flight attitude control desk, voltage changing module, amperemeter, battery pack and the electronic transmission of controlling gyroplane rotate speed.
In the present invention, described electronic transmission comprises the secondary electronic transmission of controlling the main electronic transmission of main rotor rotating speed and controlling secondary gyroplane rotate speed.
In the present invention, described power system comprises the drive motor being connected with upper screw propeller, lower spiral and several secondary rotors respectively.
In the present invention, described secondary rotor is equipped with secondary rotor duct outward.
In the present invention, described supporting construction is the bracing frame that upper and lower double-layer structure is identical, by center carbon plate and support carbon pipe, connects to form; Between described upper and lower bracing frame, by pipe link, be connected, pipe link is positioned at the outside of bracing frame.
Beneficial effect of the present invention: the secondary rotor in (1), the coaxial multi-rotor aerocraft of duct of the present invention all can freely be rotated movement, make aircraft can according to flight, need the lift distribution of change of flight device awing, realized the good maneuvering performance of aircraft; (2), the secondary rotor of aircraft surrounding of the present invention can take in to the inside of center duct, to dwindle the volume of aircraft, is convenient to fly between narrow city housing-group, can be applied to the fields such as investigation, monitoring, photography, rescue and special operations; (3), by electronic transmission, adjust the different rotating speeds of major and minor rotor, be convenient to the main hoisting force of aircraft and flight attitude to carry out quick adjustment.
Accompanying drawing explanation
Fig. 1 is the coaxial multi-rotor aerocraft unfolding assumption diagram of duct of the present invention;
Fig. 2 is rocking arm rotating mechanism cut-away view;
Fig. 3 is the coaxial multi-rotor aerocraft collapsed configuration of duct of the present invention figure;
Fig. 4 is that in the coaxial multi-rotor aerocraft of duct of the present invention, secondary rotor is expanded to other position views;
Fig. 5 is the coaxial multi-rotor aerocraft birds-eye view 1 of duct of the present invention;
Fig. 6 is the coaxial multi-rotor aerocraft birds-eye view 2 of duct of the present invention;
Fig. 7 is the coaxial multi-rotor aerocraft deployed condition of duct of the present invention lateral plan;
Fig. 8 is the coaxial multi-rotor aerocraft collapsed state of duct of the present invention lateral plan;
In figure: the secondary rotor duct of 1-, the secondary rotor drive motor of 2-, the secondary rotor of 3-, 4-strut bar fixed block, the secondary rotor set collar of 5-, 6-strut bar, 7-rocking arm, 8-rocking arm support ring, 9-rocking arm strut bar, 10-center duct, the upper main screw of 11-, main screw under 12-, 13-supports carbon pipe, 14-set collar, 15-center carbon plate, the upper screw propeller drive motor of 16-, screw propeller drive motor under 17-, 18-pipe link, 19-steering wheel, 20-bearing, 21-contiguous block, 22-rolling brake ring, 23-steering wheel permanent seat, 24-steering wheel gear, 25-bearing carrier ring, 26-arm revolving gear.
The specific embodiment
Below in conjunction with accompanying drawing, the invention will be further described.
As Fig. 1, 2, 4, 5, 6, shown in 7, the body of the coaxial multi-rotor aerocraft of duct of the present invention comprises center duct 10, in center duct 10, be provided with upper and lower two-layer bracing frame, the structure of the upper and lower bracing frame is identical, by center carbon plate 15 and four support carbon pipes 13, be formed by connecting, on, between lower layer support frame, by four pipe links 18, be connected, pipe link 18 is positioned at the outside of upper and lower bracing frame, on, on lower two-layer center carbon plate 15, install respectively screw propeller drive motor 16, lower screw propeller drive motor 17, on upper screw propeller drive motor 16, install screw propeller 11 fixing by set collar 14, lower screw propeller 12 is installed on lower screw propeller drive motor 17 and is fixed by set collar, upper screw propeller 11 and lower screw propeller 12 form the main rotor of aircraft, upper screw propeller 11 and lower screw propeller 12 centers are arranged on same vertical axis, and hand of rotation is contrary each other, thereby at when hovering offset torque and control flight course during in maneuvering flight.The periphery of center duct 10 is evenly distributed with four secondary rotors 3, four secondary rotors 3 are positioned in same level, secondary rotor 3 is arranged on retractable rocking arm 7 one end, by secondary rotor fixed block 4, be connected with rocking arm 7, the below equal auxiliary connection rotor drive motor 2 of each secondary rotor 3, the secondary rotor set collar 5 that passes through of secondary rotor 3 is connected on secondary rotor drive motor 2, rocking arm 7 is provided with rolling brake ring 22 with the junction of secondary rotor drive motor 2, vertical installation site for locating pair rotor motor 2, prevent that secondary rotor motor 2 from twisting around installation shaft, play the effect of spacing location, the secondary rotor duct 1 of each secondary rotor 3 peripheral suit, secondary rotor duct 1 is fixed on and is connected on strut bar fixed block 4 by strut bar 6, and strut bar fixed block 4 is fixed on rocking arm 7, the other end connecting rocker arm support ring 8 of rocking arm 7, rocking arm support ring 8 is fixedly connected with rocking arm strut bar 9, bearing 20 is socketed in the below of pipe link 18, fixing with pipe link 18 by upper and lower two fixed blocks 21 respectively, is set with arm revolving gear 26 on bearing carrier ring 25, and rocking arm strut bar 9 is bolted on arm revolving gear 26, steering wheel 19 is fixed on steering wheel permanent seat 23, steering wheel permanent seat 23 is fixedly connected on pipe link 18, steering wheel gear 24 and arm revolving gear 26 engagements, drive arm revolving gear 26 to rotate, and then control rocking arm strut bar 9, the secondary rotor 3 of control rocking arm 7 drive around pipe link 18 rotations, with the whole flight axis distance of change of flight device, provide different control torques, realize different maneuvering performancies, to be suitable for multiple flight occasion.The main lift of the coaxial multi-rotor aerocraft of duct is provided by the interior upper screw propeller 11 of center duct 10 and the lower screw propeller 12 at aircraft middle part, the secondary rotor 3 of center duct 10 peripheries provides attitude control torque, realizes aircraft around maneuvering flight actions such as its axis all around and rotations.
Bracing frame bottom in center duct 10 is provided with flight control system, comprise flight attitude control desk, voltage changing module, amperemeter, battery pack and the electronic transmission of controlling gyroplane rotate speed, electronic transmission comprises controls upper screw propeller 11 and four main electronic transmissions of lower screw propeller 12 rotating speed in main rotor, controls respectively four four secondary electronic transmissions controlling secondary rotor 3 rotating speeds.
As shown in Fig. 3,8, by controlling steering wheel 19, by driving rocking arm 7 to rotate, four secondary rotors 3 of control can be received to the inside that is stacked to center duct 10, be convenient to, in narrow space flight, improve the manoevreability of aircraft, to adapt to the demand of each row flight environment of vehicle.
As shown in Figure 5, upper screw propeller 11 and lower screw propeller 12 contrarotations, two the secondary rotor wing rotation opposite directions of arbitrary neighborhood in four secondary rotors 3; The flight altitude control of the coaxial multi-rotor aerocraft of duct is controlled by upper screw propeller 11 and lower screw propeller 12, and pitching and rolling are controlled by four secondary rotors 3 of surrounding and controlled, and aircraft course is by upper screw propeller 11, lower screw propeller 12 and four secondary rotor 3 co-controllings.
As shown in 4,6, the coaxial multi-rotor aerocraft of duct of the present invention, in flight course, is controlled rocking arm 7 by steering wheel 19 and is rotated to different directions, drives four secondary rotors 3 to carry out the adjustment of different angles, realizes the better manoevreability of aircraft.
The above is only the preferred embodiment of the present invention, it should be pointed out that for those skilled in the art, can also make some improvement under the premise without departing from the principles of the invention, and these improvement also should be considered as protection scope of the present invention.
Claims (8)
1. the coaxial multi-rotor aerocraft of duct, comprises housing construction, power system and control system, and described housing construction comprises that center duct (10), main rotor and several are evenly distributed on the secondary rotor (3) of duct periphery, center; Described main rotor comprises screw propeller (11) and lower screw propeller (12), described upper screw propeller (11) and lower screw propeller (12) by support construction supports in center duct (10), being centered close on same vertical axis of described upper screw propeller (11) and lower screw propeller (12), hand of rotation is contrary, it is characterized in that: the outside of described supporting construction is fixedly connected with wheel word, described secondary rotor (3) is connected with wheel word by rocking arm (7), and described wheel word control rocking arm (7) drives secondary rotor (3) around the point of connection rotation of itself and supporting construction.
2. the coaxial multi-rotor aerocraft of duct according to claim 1, it is characterized in that: described wheel word comprises steering wheel (19), bearing (20), arm revolving gear (26) and rocking arm strut bar (9), described steering wheel (19), bearing (20) are all fixed in supporting construction, bearing (20) overcoat switches through moving gear (26); it is upper that rocking arm strut bar (9) is fixed on arm revolving gear (26), described arm revolving gear 26 and steering wheel gear (24) engagement.
3. the coaxial multi-rotor aerocraft of duct according to claim 1 and 2, is characterized in that: described rocking arm (7) is provided with rolling brake ring (22) with the junction of secondary rotor (3).
4. the coaxial multi-rotor aerocraft of duct according to claim 3, it is characterized in that: described control system is arranged on the bottom of supporting construction, comprise flight attitude control desk, voltage changing module, amperemeter, battery pack and the electronic transmission of controlling gyroplane rotate speed.
5. the coaxial multi-rotor aerocraft of duct according to claim 4, is characterized in that: described electronic transmission comprises the secondary electronic transmission of controlling the main electronic transmission of main rotor rotating speed and controlling secondary gyroplane rotate speed.
6. the coaxial multi-rotor aerocraft of duct according to claim 3, is characterized in that: described power system comprises the drive motor being connected with upper screw propeller (11), lower spiral (12) and several secondary rotors (13) respectively.
7. according to the coaxial multi-rotor aerocraft of duct described in claim 3 any one, it is characterized in that: the outer secondary rotor duct (1) that is equipped with of described secondary rotor (3).
8. the coaxial multi-rotor aerocraft of duct according to claim 3, is characterized in that: described supporting construction is the bracing frame that upper and lower double-layer structure is identical, by center carbon plate (15) and support carbon pipe (13), connects to form; Between described upper and lower bracing frame, by pipe link (18), be connected, pipe link (18) is positioned at the outside of bracing frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420303405.8U CN203958613U (en) | 2014-06-10 | 2014-06-10 | The coaxial multi-rotor aerocraft of duct |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420303405.8U CN203958613U (en) | 2014-06-10 | 2014-06-10 | The coaxial multi-rotor aerocraft of duct |
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| CN203958613U true CN203958613U (en) | 2014-11-26 |
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| CN201420303405.8U Withdrawn - After Issue CN203958613U (en) | 2014-06-10 | 2014-06-10 | The coaxial multi-rotor aerocraft of duct |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104085530A (en) * | 2014-06-10 | 2014-10-08 | 南京航空航天大学 | Ducted coaxial multi-rotor type aircraft |
| CN104554726A (en) * | 2014-12-01 | 2015-04-29 | 嵊州领航信息科技有限公司 | Special intelligent unmanned aerial vehicle for agriculture and forestry |
| CN104554720A (en) * | 2014-12-31 | 2015-04-29 | 昆明天龙经纬电子科技有限公司 | Compound power helicopter |
| CN104743109A (en) * | 2015-04-17 | 2015-07-01 | 何春旺 | Power system and aircraft |
| CN104787317A (en) * | 2015-04-17 | 2015-07-22 | 何春旺 | Aircraft and control method thereof |
| GB2529896A (en) * | 2014-09-05 | 2016-03-09 | Richard Nathan Hadder | Multirotor |
| WO2016199995A1 (en) * | 2015-06-09 | 2016-12-15 | 한국항공우주연구원 | Propeller unit deployment-type unmanned aerial vehicle |
| CN106585952A (en) * | 2016-12-20 | 2017-04-26 | 深圳市元征科技股份有限公司 | Multi-rotor unmanned aerial machine |
| CN109050898A (en) * | 2018-08-16 | 2018-12-21 | 南京壹诺为航空科技有限公司 | Non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula |
| CN109153445A (en) * | 2016-02-17 | 2019-01-04 | 雅顿技术有限公司 | Multi-rotor aerocraft with different purposes propellers |
| JP7360754B1 (en) | 2022-07-07 | 2023-10-13 | 俊朗 飯島 | flying object |
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2014
- 2014-06-10 CN CN201420303405.8U patent/CN203958613U/en not_active Withdrawn - After Issue
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104085530B (en) * | 2014-06-10 | 2016-07-13 | 南京航空航天大学 | The coaxial multi-rotor aerocraft of duct |
| CN104085530A (en) * | 2014-06-10 | 2014-10-08 | 南京航空航天大学 | Ducted coaxial multi-rotor type aircraft |
| GB2529896A (en) * | 2014-09-05 | 2016-03-09 | Richard Nathan Hadder | Multirotor |
| GB2529896B (en) * | 2014-09-05 | 2016-09-14 | Nathan Hadder Richard | Multirotor |
| CN104554726A (en) * | 2014-12-01 | 2015-04-29 | 嵊州领航信息科技有限公司 | Special intelligent unmanned aerial vehicle for agriculture and forestry |
| CN104554720A (en) * | 2014-12-31 | 2015-04-29 | 昆明天龙经纬电子科技有限公司 | Compound power helicopter |
| CN104743109B (en) * | 2015-04-17 | 2018-03-27 | 珠海磐磊智能科技有限公司 | Dynamical system and aircraft |
| CN104743109A (en) * | 2015-04-17 | 2015-07-01 | 何春旺 | Power system and aircraft |
| CN104787317A (en) * | 2015-04-17 | 2015-07-22 | 何春旺 | Aircraft and control method thereof |
| CN104787317B (en) * | 2015-04-17 | 2019-01-25 | 珠海磐磊智能科技有限公司 | Aircraft and its control method |
| WO2016199995A1 (en) * | 2015-06-09 | 2016-12-15 | 한국항공우주연구원 | Propeller unit deployment-type unmanned aerial vehicle |
| US10807698B2 (en) | 2015-06-09 | 2020-10-20 | Korea Aerospace Research Institute | Unfolding propeller unit type unmanned aerial vehicle |
| CN109153445A (en) * | 2016-02-17 | 2019-01-04 | 雅顿技术有限公司 | Multi-rotor aerocraft with different purposes propellers |
| CN106585952A (en) * | 2016-12-20 | 2017-04-26 | 深圳市元征科技股份有限公司 | Multi-rotor unmanned aerial machine |
| CN109050898A (en) * | 2018-08-16 | 2018-12-21 | 南京壹诺为航空科技有限公司 | Non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula |
| JP7360754B1 (en) | 2022-07-07 | 2023-10-13 | 俊朗 飯島 | flying object |
| JP2024008808A (en) * | 2022-07-07 | 2024-01-19 | 俊朗 飯島 | Flight vehicle |
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Granted publication date: 20141126 Effective date of abandoning: 20160713 |
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| C25 | Abandonment of patent right or utility model to avoid double patenting |