CN201793018U - Four-rotor-winged aircraft with retractable fuselage - Google Patents
Four-rotor-winged aircraft with retractable fuselage Download PDFInfo
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- CN201793018U CN201793018U CN2010205327816U CN201020532781U CN201793018U CN 201793018 U CN201793018 U CN 201793018U CN 2010205327816 U CN2010205327816 U CN 2010205327816U CN 201020532781 U CN201020532781 U CN 201020532781U CN 201793018 U CN201793018 U CN 201793018U
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Abstract
The utility model relates to a four-rotor-winged aircraft with a retractable fuselage. The four-rotor-winged aircraft at least comprises a body frame (9), a rotation shaft (7), a one-way snap spring device (4), a two-way snap spring device (6) and a rotor wing mechanism, wherein the one-way snap spring device (4) consists of a blocking sheet (41), a spring (42), a front positioning bayonet (43) and a rear positioning bayonet (44); the two-way snap spring device (6) consists of a left blocking sheet (41), a right blocking sheet (65), a left spring (66), a right spring (67), a horizontal positioning bayonet (61), an upward turned positioning bayonet (62) and a downward turned positioning bayonet (63); the rotor wing mechanism consists of a propeller (1), a driving motor (2), a retractable connection rod (3), a rotary connection rod (5) and a U-shaped fixed support (8); and four rotor wing mechanisms are arranged on the sides of the body frame (9) respectively.
Description
Technical field:
The present invention relates to telescopic four rotor crafts of a kind of fuselage.
Background technology:
Multi-rotor aerocraft is the motor-driven that is evenly distributed by 3～16, the topology layout novelty, and the flying method uniqueness, total arrangement belongs to the non co axial dish, can vertical takeoff and landing and remote control/autonomous flight device of independently hovering.But compare with the fixed-wing aircraft with the butterfly of routine, multi-rotor aerocraft compact conformation, 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, therefore, can the work of efficient quick ground.In addition, its novel profile, simple structure, cheap cost, remarkable performance and easy flicon mode have determined it to have broad application prospects.
In the multi-rotor aerocraft, if one of them rotor of three rotary wind type aircraft damages, then can't continue flight, 5～16 rotary wind type aircraft must make its complex structure along with the increase of rotor number.Thereby four the rotor craft cost performance the highest, use the most generally.But present four rotor crafts are mostly fixed screw propeller by cross bracket, and it is big to take up room, and exist problems such as storage and transportation inconvenience.
Summary of the invention:
The present invention's purpose is:
Propose the four rotary wind type aircraft that a kind of fuselage can shrink freely, make it simple in structure, little, convenient storage and transportation take up room.
In order to realize the present invention's purpose, intend by the following technical solutions:
The present invention comprises at least: frame, rotating shaft, by catch, spring, the prelocalization bayonet socket, the unidirectional jump ring device that back limited bayonet is formed, by left catch, right catch, left spring, right spring, the horizontal location bayonet socket, on turn over limited bayonet and turn over down the two-way jump ring device that limited bayonet is formed, and by screw propeller, drive motor, shrinking connecting-rod, the rotor mechanism that rotation connecting rod and U type fixed mount are formed, it is characterized in that: screw propeller is fixed on the output shaft of drive motor, drive motor is fixed on an end of shrinking connecting-rod, the other end of shrinking connecting-rod is provided with the catch and the spring of unidirectional jump ring device, the prelocalization bayonet socket of unidirectional jump ring device and back limited bayonet are arranged on the top of rotation connecting rod, the rotation connecting rod is connected with U type fixed mount by rotating shaft, the left catch and the left spring of two-way jump ring device, right catch and right spring are separately positioned on the both sides of rotation connecting rod afterbody, the horizontal location bayonet socket of two-way jump ring device, on turn over limited bayonet and under turn over limited bayonet and be arranged on the U type fixed mount, simultaneously, U type fixed mount is fixed on the side of frame.---the side of above-mentioned frame is respectively arranged with four rotor mechanisms.
Characteristics of the present invention are:
The stirring of the contraction of the present invention by shrinking connecting-rod, rotation connecting rod (four rotors upwards stir simultaneously or stir downwards) for whole device under off working state overall volume dwindle the condition created, be convenient to storage and transportation.If a rotor mechanism among the present invention suffers to damage and can't work on, the present invention still can continue flight by the lift of other three rotors.
Description of drawings:
Fig. 1 has illustrated state of flight structure of the present invention.
Fig. 2 has illustrated the present invention upwards to fold contraction state.
Fig. 3 has illustrated the present invention to fold contraction state downwards.
Fig. 4 has illustrated the state of rotation connecting rod horizontal location of the present invention when U type fixed mount.
Fig. 5 is the top plan view (wherein right spring 67 is in compressive state) of Fig. 4.
1, screw propeller; 2, drive motor; 3, shrinking connecting-rod; 4, unidirectional jump ring device; 5, rotation connecting rod; 6, two-way jump ring device; 7, rotating shaft; 8, U type fixed mount; 9, frame; 41, catch; 42, spring; 43, prelocalization bayonet socket; 44, back limited bayonet; 61, horizontal location bayonet socket; 62, turn over limited bayonet on; 63, turn over limited bayonet down; 64, left catch; 65, right catch; 66, left spring; 67, right spring; The direction of N, power.
The specific embodiment:
The present invention is provided with four rotor mechanisms respectively in four different sides of the frame 9 of rectangular build, wherein the structure of rotor mechanism is: screw propeller 1 is fixed on the output shaft of drive motor 2, drive motor 2 is fixed on an end of shrinking connecting-rod 3, the other end of shrinking connecting-rod 3 is provided with the catch 41 and the spring 42 of unidirectional jump ring device 4, the prelocalization bayonet socket 43 of unidirectional jump ring device 4 and back limited bayonet 44 are arranged on the top of rotation connecting rod 5, rotation connecting rod 5 is connected with U type fixed mount 8 by rotating shaft 7, the left catch 64 of two-way jump ring device 6 and left spring 66, right catch 65 and right spring 67 are separately positioned on the both sides of rotation connecting rod 5 afterbodys, the horizontal location bayonet socket 61 of two-way jump ring device 6, on turn over limited bayonet 62 and under turn over limited bayonet 63 and be arranged on the U type fixed mount 8, simultaneously, U type fixed mount 8 is fixed on the side of frame 9.
When the present invention need carry out aerial mission, the present invention is launched to become state of flight illustrated in Figure 1 from upwards contraction state illustrated in Figure 2 or downward contraction state illustrated in Figure 3:
Make left catch 64 and right catch 65 be in right catch 65 illustrated in Figure 5 state simultaneously by left catch 64 and the right catch 65 of pressing the two-way jump ring device 6 of the present invention simultaneously at the right spring 67 of effect lower compression of application force N, simultaneously, with rotation connecting rod 5 to level attitude upset up to the left catch 64 of two-way jump ring device 6 and right catch 65 respectively on the horizontal location bayonet socket 61 that is positioned under the effect of left spring 66 and right spring 67 on the U type fixed mount 8, relative displacement does not just take place and has created condition for the present invention rotate connecting rod 5 and U type fixed mount 8 when state of flight in this.And, with rotor mechanism elongation of the present invention, as shown in Figure 4, make spring 42 compress by the catch 41 of pressing unidirectional jump ring device 4, simultaneously, pulling shrinking connecting-rod 3 is made away from 8 motions of U type fixed mount shrinking connecting-rod 3, rotor mechanism elongation of the present invention is being positioned under the effect of spring 42 on the prelocalization bayonet socket 43 that rotates on the connecting rod 5 up to the catch 41 of unidirectional jump ring device 4, this has not just created condition for the present invention's shrinking connecting-rod 3 when state of flight with rotation connecting rod 5 relative displacement does not take place, has created condition for the stabilized flight of aircraft again.
When needs storages or transportation are of the present invention, the present invention is deformed into upwards contraction state or downward contraction state as schematically shown in Figure 3 illustrated in Figure 2 from state of flight illustrated in Figure 1:
Make spring 42 compress by the catch 41 of pressing unidirectional jump ring device 4, simultaneously, promoting shrinking connecting-rod 3 makes shrinking connecting-rod 3 do be positioned at the back limited bayonet 44 that rotates on the connecting rod 5 near 8 motions of U type fixed mount under the effect of spring 42 up to the catch 41 of unidirectional jump ring device 4, this has not just created condition for the present invention's shrinking connecting-rod 3 under off working states such as storage or transportation with rotation connecting rod 5 relative displacement does not take place, and, make left catch 64 and right catch 65 be in the state of the right catch 65 shown in Fig. 5 simultaneously by left catch 64 and the right catch 65 of pressing two-way jump ring device 6 of the present invention simultaneously at the right spring 67 of effect lower compression of application force N, simultaneously, to rotate connecting rod 5 upwards (or to) down upset up to the left catch 64 of two-way jump ring device 6 and right catch 65 be positioned under the effect of left spring 66 and right spring 67 respectively on the U type fixed mount 8 on turn on the limited bayonet 62 (or under turn over limited bayonet 63), relative displacement does not just take place with U type fixed mount 8 and has created condition for the present invention rotate connecting rod 5 when off working state in this, is the convenient storage or the condition of having transported the invention.
Claims (2)
1. telescopic four rotor crafts of fuselage, at least comprise: frame (9), rotating shaft (7), by catch (41), spring (42), prelocalization bayonet socket (43), the unidirectional jump ring device (4) that back limited bayonet (44) is formed, by left catch (64), right catch (65), left spring (66), right spring (67), horizontal location bayonet socket (61), on turn over limited bayonet (62) and turn over down the two-way jump ring device (6) that limited bayonet (63) is formed, and by screw propeller (1), drive motor (2), shrinking connecting-rod (3), the rotor mechanism that rotation connecting rod (5) and U type fixed mount (8) are formed, it is characterized in that: screw propeller (1) is fixed on the output shaft of drive motor (2), drive motor (2) is fixed on an end of shrinking connecting-rod (3), the other end of shrinking connecting-rod (3) is provided with the catch (41) and the spring (42) of unidirectional jump ring device (4), the prelocalization bayonet socket (43) of unidirectional jump ring device (4) and back limited bayonet (44) are arranged on the top of rotation connecting rod (5), rotation connecting rod (5) is connected with U type fixed mount (8) by rotating shaft (7), the left catch (64) of two-way jump ring device (6) and left spring (66), right catch (65) and right spring (67) are separately positioned on the both sides of rotation connecting rod (5) afterbody, the horizontal location bayonet socket (61) of two-way jump ring device (6), on turn over limited bayonet (62) and under turn over limited bayonet (63) and be arranged on the U type fixed mount (8), simultaneously, U type fixed mount (8) is fixed on the side of frame (9).
2. a kind of fuselage telescoping four rotor crafts according to claim 1, it is characterized in that: the side of described frame (9) is respectively arranged with four rotor mechanisms.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010205327816U CN201793018U (en) | 2010-09-16 | 2010-09-16 | Four-rotor-winged aircraft with retractable fuselage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010205327816U CN201793018U (en) | 2010-09-16 | 2010-09-16 | Four-rotor-winged aircraft with retractable fuselage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201793018U true CN201793018U (en) | 2011-04-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010205327816U Expired - Fee Related CN201793018U (en) | 2010-09-16 | 2010-09-16 | Four-rotor-winged aircraft with retractable fuselage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201793018U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101973392A (en) * | 2010-09-16 | 2011-02-16 | 中国计量学院 | Four-rotor aircraft with telescopic body |
| CN104648664A (en) * | 2014-12-18 | 2015-05-27 | 合肥工业大学 | Retractable folding quad rotor |
| TWI508763B (en) * | 2014-01-08 | 2015-11-21 | Univ Nat Formosa | Foldable Shaped six rotorcraft |
| WO2015196436A1 (en) * | 2014-06-26 | 2015-12-30 | 深圳市大疆创新科技有限公司 | Deforming aircraft |
| CN105292467A (en) * | 2015-11-06 | 2016-02-03 | 中国航空工业经济技术研究院 | Horizontal speed-raising system of rotorcraft |
| EP3241741A4 (en) * | 2015-01-04 | 2018-01-24 | Beijing Zero Zero Infinity Technology Co. Ltd. | Foldable unmanned aerial vehicle |
| CN113193800A (en) * | 2021-04-13 | 2021-07-30 | 南昌三瑞智能科技有限公司 | Rotation direction conversion method of direct-current brushless electronic speed regulator |
-
2010
- 2010-09-16 CN CN2010205327816U patent/CN201793018U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101973392A (en) * | 2010-09-16 | 2011-02-16 | 中国计量学院 | Four-rotor aircraft with telescopic body |
| TWI508763B (en) * | 2014-01-08 | 2015-11-21 | Univ Nat Formosa | Foldable Shaped six rotorcraft |
| WO2015196436A1 (en) * | 2014-06-26 | 2015-12-30 | 深圳市大疆创新科技有限公司 | Deforming aircraft |
| US10287004B2 (en) | 2014-06-26 | 2019-05-14 | SZ DJI Technology Co., Ltd. | Transformable aerial vehicle |
| CN104648664A (en) * | 2014-12-18 | 2015-05-27 | 合肥工业大学 | Retractable folding quad rotor |
| CN104648664B (en) * | 2014-12-18 | 2017-02-22 | 合肥工业大学 | Retractable folding quad rotor |
| EP3241741A4 (en) * | 2015-01-04 | 2018-01-24 | Beijing Zero Zero Infinity Technology Co. Ltd. | Foldable unmanned aerial vehicle |
| CN105292467A (en) * | 2015-11-06 | 2016-02-03 | 中国航空工业经济技术研究院 | Horizontal speed-raising system of rotorcraft |
| CN113193800A (en) * | 2021-04-13 | 2021-07-30 | 南昌三瑞智能科技有限公司 | Rotation direction conversion method of direct-current brushless electronic speed regulator |
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Legal Events
| Date | Code | Title | Description |
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| 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 |