CN201793017U - Rotary retractable four-rotor flight device - Google Patents
Rotary retractable four-rotor flight device Download PDFInfo
- Publication number
- CN201793017U CN201793017U CN201020532777XU CN201020532777U CN201793017U CN 201793017 U CN201793017 U CN 201793017U CN 201020532777X U CN201020532777X U CN 201020532777XU CN 201020532777 U CN201020532777 U CN 201020532777U CN 201793017 U CN201793017 U CN 201793017U
- Authority
- CN
- China
- Prior art keywords
- drive motor
- connecting rod
- rotor
- output shaft
- driving motor
- 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
Images
Abstract
The utility model discloses a rotary retractable four-rotor flight device. The device at least comprises a stand (1) and rotor mechanisms, wherein each rotor mechanism consists of a driving motor I (2), a rotary encoder I (3), a rotary connecting rod (4), a driving motor II (5), a rotary encoder II (6), a lengthening connecting rod (7), a propeller driving motor (8) and a propeller (9); the flight device is characterized in that the propeller (9) is fixed on the output shaft of the propeller driving motor (8), wherein the propeller driving motor (8) is connected with one end of the lengthening connecting rod (7); the other end of the lengthening connecting rod (7) is connected with the output shaft of the driving motor II (5) and is in a close fit state; the driving motor II (5) is fixed at one end of the rotary connecting rod (4); the other end of the rotary connecting rod (4) is connected with the output shaft of the driving motor I (2) and is in the close fit state; the driving motor I (2) is arranged on the stand (1); and four rotor mechanisms are arranged on the stand (1).
Description
Technical field:
The present invention relates to a kind of rotation contraction type four rotor flight instrumentses.
Background technology:
Many rotors flight instruments is the motor-driven that is evenly distributed by 3～16, compare with the fixed-wing flight instruments with the butterfly of routine, the novel compactness of many rotors flight instruments topology layout, big, the mobility strong, safe and reliable of lift, can fly with various attitudes on fast and flexible ground, as hover, precedingly fly, side flies and inverted flight etc., and then dwindle swinging radius greatly, and therefore, can the work of efficient quick ground.
But, even many rotors flight instruments is not when flying, the stretched condition when its rotor is still keeping flying, it is very big to take up room, and exists problems such as storage and transportation inconvenience that is:.And three rotary wind type flight instrumentses then can't continue flight if one of them rotor damages, and five rotary wind type flight instrumentses (perhaps the sum of rotor surpasses five flight instruments) are because the increase of its rotor number must make its structure complicated.
Summary of the invention:
The present invention's purpose is:
Propose a kind of rotation contraction type that can shrink freely four rotor flight instrumentses, make it simple in structure, storage and convenient transportation.
In order to realize the present invention's purpose, intend by the following technical solutions:
The present invention comprises at least: frame, by drive motor I, be arranged on the rotary encoder I of drive motor I bottom, the rotation connecting rod, drive motor II, be arranged on the rotary encoder II of drive motor II bottom, add long connecting rod, the rotor mechanism that screw propeller drive motor and screw propeller are formed, it is characterized in that: screw propeller is fixed on the output shaft of screw propeller drive motor, the screw propeller drive motor is connected with an end that adds long connecting rod, this other end that adds long connecting rod links to each other with the output shaft of drive motor II and is in the flush fit state, drive motor II is fixed on an end of rotation connecting rod, the output shaft of this drive motor II is in the running-fit state with the rotation connecting rod, the other end of rotation connecting rod links to each other with the output shaft of drive motor I and is in the flush fit state, drive motor I is installed on the frame, and output shaft and the frame of this drive motor I are in the running-fit state.---above-mentioned frame is provided with four rotor mechanisms.
Characteristics of the present invention are:
Even if one of them rotor among the present invention suffers to damage and can't work on, the present invention still can continue working flight by the lift of other three rotors.The present invention by rotation connecting rod and the rotation that adds long connecting rod be punctured into whole device under obsolete state overall volume dwindle the condition created, be convenient to storage and transportation.
Description of drawings:
State when Fig. 1 has illustrated that the present invention works.
Contraction state when Fig. 2 has illustrated inoperative of the present invention.
Fig. 3 is the cutaway view of one of them rotor mechanism of the present invention among Fig. 1.
1, frame; 2, drive motor I; 3, rotary encoder I; 4, rotation connecting rod; 5, drive motor II; 6, rotary encoder II; 7, add long connecting rod; 8, screw propeller drive motor; 9, screw propeller; 10, bolt; 11, bolt.
The specific embodiment:
Of the present invention is to be provided with four rotor mechanisms respectively on four angles of square frame 1, wherein the structure of rotor mechanism is achieved like this: screw propeller 9 is fixed on the output shaft of screw propeller drive motor 8, screw propeller drive motor 8 is fixed on an end that adds long connecting rod 7, this other end that adds long connecting rod 7 links to each other with the output shaft of drive motor II5 and is in flush fit state (realizing this flush fit state by the fastening or welding manner of bolt 11), the bottom of drive motor II5 is provided with rotary encoder II6, drive motor II5 is fixed on an end of rotation connecting rod 4, the output shaft of this drive motor II5 is in the running-fit state with rotation connecting rod 4, link to each other with the output shaft of drive motor I2 and be in flush fit state (realizing this flush fit state) at the other end of this rotation connecting rod 4 by the fastening or welding manner of bolt 10, the bottom of drive motor I2 is provided with rotary encoder I3, drive motor I2 is installed on the frame 1, and output shaft and the frame 1 of this drive motor I2 are in the running-fit state.
When the present invention need carry out aerial mission, the present invention is as schematically shown in Figure 1 state of flight from the elongation of as schematically shown in Figure 2 contraction state: come driven in rotation connecting rod 4 by starting drive motor I2, make rotation connecting rod 4 and add a end that long connecting rod 7 is connected to direction rotation away from frame 1, rotary encoder I3 records the rotational angle adjustment rotation connecting rod 4 of drive motor I2 rotor, simultaneously, drive and add long connecting rod 7 by starting drive motor II5, make to add the end that long connecting rod 7 is connected with screw propeller drive motor 8 and rotate to the direction away from frame 1, the rotational angle adjustment that rotary encoder II6 records drive motor II5 rotor adds long connecting rod 7.Adjustment by rotary encoder I3 and rotary encoder II6 realizes rotating connecting rod 4 and adds the rotational angle of long connecting rod 7, thereby comes adjustable screw oar 9 to the distance between the frame 1, has created condition for realizing stable flight flexibly of the present invention.
When needs storages or carrying are of the present invention, the present invention is punctured into as schematically shown in Figure 2 contraction state from as schematically shown in Figure 1 state of flight: come driven in rotation connecting rod 4 by starting drive motor I2, make rotation connecting rod 4 and add a end that long connecting rod 7 is connected to direction rotation near frame 1, rotary encoder I3 records the rotational angle adjustment rotation connecting rod 4 of drive motor I2 rotor, simultaneously, drive and add long connecting rod 7 by starting drive motor II5, make and add the end that long connecting rod 7 is connected with screw propeller drive motor 8 and rotate to direction near frame 1, the rotational angle adjustment that rotary encoder II6 records drive motor II5 rotor adds long connecting rod 7, the final rotation connecting rod 4 that makes is retracted to as schematically shown in Figure 2 contraction state with adding long connecting rod 7, thus for convenient storage or carrying the invention condition.
Claims (2)
1. one kind is rotated contraction type four rotor flight instrumentses, which comprises at least: frame (1), by drive motor I (2), be arranged on the rotary encoder I (3) of drive motor I (2) bottom, rotation connecting rod (4), drive motor II (5), be arranged on the rotary encoder II (6) of drive motor II (5) bottom, add long connecting rod (7), the rotor mechanism that screw propeller drive motor (8) and screw propeller (9) are formed, it is characterized in that: screw propeller (9) is fixed on the output shaft of screw propeller drive motor (8), screw propeller drive motor (8) is connected with an end that adds long connecting rod (7), this other end that adds long connecting rod (7) links to each other with the output shaft of drive motor II (5) and is in the flush fit state, drive motor II (5) is fixed on an end of rotation connecting rod (4), the output shaft of this drive motor II (5) is in the running-fit state with rotation connecting rod (4), the other end of rotation connecting rod (4) links to each other with the output shaft of drive motor I (2) and is in the flush fit state, drive motor I (2) is installed on the frame (1), and the output shaft of this drive motor I (2) and frame (1) are in the running-fit state.
2. a kind of rotation contraction type four rotor flight instrumentses according to claim 1, it is characterized in that: described frame (1) is provided with four rotor mechanisms.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201020532777XU CN201793017U (en) | 2010-09-16 | 2010-09-16 | Rotary retractable four-rotor flight device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201020532777XU CN201793017U (en) | 2010-09-16 | 2010-09-16 | Rotary retractable four-rotor flight device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201793017U true CN201793017U (en) | 2011-04-13 |
Family
ID=43847938
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201020532777XU Expired - Fee Related CN201793017U (en) | 2010-09-16 | 2010-09-16 | Rotary retractable four-rotor flight device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201793017U (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102991663A (en) * | 2012-11-05 | 2013-03-27 | 上海交通大学无锡研究院 | System for mooring stratospheric telecommunication platform with rotor wing |
| CN103625641A (en) * | 2013-11-18 | 2014-03-12 | 北京中科飞鸿科技有限公司 | Transverse folding type four-rotor aircraft |
| CN104085530A (en) * | 2014-06-10 | 2014-10-08 | 南京航空航天大学 | Ducted coaxial multi-rotor type aircraft |
| CN104260878A (en) * | 2014-10-16 | 2015-01-07 | 北京理工大学 | Four-rotor aircraft rack with capacity of automatic folding and spreading |
| CN104260605A (en) * | 2014-10-16 | 2015-01-07 | 北京理工大学 | Air-ground amphibious spherical metamorphic robot based on metamorphic principle |
| CN104401484A (en) * | 2014-10-16 | 2015-03-11 | 北京理工大学 | Six-rotor aircraft rack capable of being folded and expanded automatically |
| CN104648667A (en) * | 2015-02-17 | 2015-05-27 | 何春旺 | Aircraft |
| TWI508763B (en) * | 2014-01-08 | 2015-11-21 | Univ Nat Formosa | Foldable Shaped six rotorcraft |
| CN105460211A (en) * | 2015-12-30 | 2016-04-06 | 联想(北京)有限公司 | Flight device |
| CN105866626A (en) * | 2016-04-01 | 2016-08-17 | 湖北省超能超高压电力科技开发有限公司 | Unmanned plane-mounted UV detection system for power transmission and transformation equipment |
| CN106155080A (en) * | 2015-07-28 | 2016-11-23 | 英华达（上海）科技有限公司 | Unmanned plane |
| WO2016192021A1 (en) | 2015-06-01 | 2016-12-08 | SZ DJI Technology Co., Ltd. | Systems and methods for foldable arms |
| JP7115800B1 (en) | 2022-05-16 | 2022-08-09 | アラセ・アイザワ・アエロスパシアル合同会社 | unmanned aerial vehicle |
-
2010
- 2010-09-16 CN CN201020532777XU patent/CN201793017U/en not_active Expired - Fee Related
Cited By (27)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102991663A (en) * | 2012-11-05 | 2013-03-27 | 上海交通大学无锡研究院 | System for mooring stratospheric telecommunication platform with rotor wing |
| CN103625641A (en) * | 2013-11-18 | 2014-03-12 | 北京中科飞鸿科技有限公司 | Transverse folding type four-rotor aircraft |
| CN103625641B (en) * | 2013-11-18 | 2016-01-20 | 北京中科飞鸿科技有限公司 | Laterally folded formula quadrotor |
| TWI508763B (en) * | 2014-01-08 | 2015-11-21 | Univ Nat Formosa | Foldable Shaped six rotorcraft |
| 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 |
| CN104260878A (en) * | 2014-10-16 | 2015-01-07 | 北京理工大学 | Four-rotor aircraft rack with capacity of automatic folding and spreading |
| CN104260605A (en) * | 2014-10-16 | 2015-01-07 | 北京理工大学 | Air-ground amphibious spherical metamorphic robot based on metamorphic principle |
| CN104401484A (en) * | 2014-10-16 | 2015-03-11 | 北京理工大学 | Six-rotor aircraft rack capable of being folded and expanded automatically |
| CN104648667A (en) * | 2015-02-17 | 2015-05-27 | 何春旺 | Aircraft |
| US10202191B2 (en) | 2015-06-01 | 2019-02-12 | SZ DJI Technology Co., Ltd. | Systems and methods for foldable arms |
| US10472063B2 (en) | 2015-06-01 | 2019-11-12 | SZ DJI Technology Co., Ltd. | Systems and methods for foldable arms |
| CN112722239B (en) * | 2015-06-01 | 2023-02-28 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| WO2016192021A1 (en) | 2015-06-01 | 2016-12-08 | SZ DJI Technology Co., Ltd. | Systems and methods for foldable arms |
| EP3206947A4 (en) * | 2015-06-01 | 2017-11-01 | SZ DJI Technology Co., Ltd. | Systems and methods for foldable arms |
| CN107614377A (en) * | 2015-06-01 | 2018-01-19 | 深圳市大疆创新科技有限公司 | System and method for collapsible arm |
| US9914537B2 (en) | 2015-06-01 | 2018-03-13 | SZ DJI Technology Co., Ltd | Systems and methods for foldable arms |
| JP2018516197A (en) * | 2015-06-01 | 2018-06-21 | エスゼット ディージェイアイ テクノロジー カンパニー リミテッドＳｚ Ｄｊｉ Ｔｅｃｈｎｏｌｏｇｙ Ｃｏ．，Ｌｔｄ | Unmanned aerial vehicle |
| US11091262B2 (en) | 2015-06-01 | 2021-08-17 | SZ DJI Technology Co., Ltd. | Systems and methods for foldable arms |
| CN112722239A (en) * | 2015-06-01 | 2021-04-30 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| CN107614377B (en) * | 2015-06-01 | 2021-03-02 | 深圳市大疆创新科技有限公司 | System and method for a foldable arm |
| CN106155080A (en) * | 2015-07-28 | 2016-11-23 | 英华达（上海）科技有限公司 | Unmanned plane |
| CN105460211A (en) * | 2015-12-30 | 2016-04-06 | 联想(北京)有限公司 | Flight device |
| CN105866626A (en) * | 2016-04-01 | 2016-08-17 | 湖北省超能超高压电力科技开发有限公司 | Unmanned plane-mounted UV detection system for power transmission and transformation equipment |
| JP7115800B1 (en) | 2022-05-16 | 2022-08-09 | アラセ・アイザワ・アエロスパシアル合同会社 | unmanned aerial vehicle |
| WO2023224018A1 (en) * | 2022-05-16 | 2023-11-23 | アラセ・アイザワ・アエロスパシアル合同会社 | Unmanned aircraft |
| JP2023169057A (en) * | 2022-05-16 | 2023-11-29 | アラセ・アイザワ・アエロスパシアル合同会社 | Unmanned aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201793017U (en) | Rotary retractable four-rotor flight device | |
| CN201800918U (en) | Rotating telescopic flying device with four rotor wings | |
| EP3181449B1 (en) | Multi-rotor structure applied to unmanned aerial vehicle | |
| EP1794051B1 (en) | Compact pylon actuation system for tiltrotor aircraft | |
| CN101992854B (en) | Foldable six-axis multi-rotor aircraft | |
| US7959104B2 (en) | Flying device with improved movement on the ground | |
| CN101973392A (en) | Four-rotor aircraft with telescopic body | |
| US20100172759A1 (en) | Retractable wind turbines | |
| CN106741912B (en) | Foldable long-endurance multi-rotor unmanned aerial vehicle | |
| CN107672802A (en) | Fluting culvert type plume rotor craft | |
| CN201793018U (en) | Four-rotor-winged aircraft with retractable fuselage | |
| CN103072690A (en) | Single-ducted coaxial rotor/propeller saucer-shaped aircraft | |
| US11634215B2 (en) | Flying object | |
| CN104859852A (en) | Airphibious four-rotor aircraft | |
| CN211417616U (en) | Double-paddle counter-rotating power system of unmanned aerial vehicle | |
| CN207242040U (en) | A kind of ducted fan unmanned plane | |
| CN215436979U (en) | Paddle folding device and unmanned aerial vehicle automatic hangar | |
| CN206466153U (en) | Dirigible and its nacelle device | |
| CN205707351U (en) | Minitype bionic flapping wing robot | |
| CN102923302A (en) | Flexible connection rotating lifting airfoil of helicopter | |
| CN201907653U (en) | Helicopter gear-drive propeller | |
| CN203638099U (en) | Pitch-changeable aircraft | |
| CN102079387B (en) | Gear-driven propeller of helicopter | |
| CN207917148U (en) | A kind of foldable rotor blade | |
| CN203864995U (en) | Double-loop rotor wing used for helicopter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110413 Termination date: 20110916 |