CN203921185U - The bending mechanism of remote control multi-rotor aerocraft support arm - Google Patents
The bending mechanism of remote control multi-rotor aerocraft support arm Download PDFInfo
- Publication number
- CN203921185U CN203921185U CN201420368236.6U CN201420368236U CN203921185U CN 203921185 U CN203921185 U CN 203921185U CN 201420368236 U CN201420368236 U CN 201420368236U CN 203921185 U CN203921185 U CN 203921185U
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- support arm
- remote control
- rotor aerocraft
- control multi
- bending mechanism
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Abstract
The utility model discloses a kind of bending mechanism of remote control multi-rotor aerocraft support arm, this mechanism has dual latching function, while making support arm connect fuselage, when support arm is in level attitude, locked more firmly, support arm does not produce vibrations in-flight remote control multi-rotor aerocraft, improves its airworthiness.Electricity is installed in pipe simultaneously and is adjusted, make the cleaner letter of overall appearance of remote control multi-rotor aerocraft attractive in appearance, in the fine plate of carbon of fuselage, more equipment and instrument are installed.The bending mechanism of remote control multi-rotor aerocraft support arm is simple in structure, easy to manufacture, easy to use.
Description
Technical field
The utility model relates to remotely-piloted vehicle, particularly the bending mechanism of the support arm of remote control multi-rotor aerocraft.
Background technology
Remote control multi-rotor aerocraft has four support arms (being axle), and six support arms are down to more branched arm, and remote control multi-rotor aerocraft comprises fuselage, support arm, motor, screw propeller, the formations such as controller.The use of remote control multi-rotor aerocraft is now more and more universal, and performance and appearance requirement to these aircraft are also more and more higher.Support arm in remote control multi-rotor aerocraft is in the past fixing can not bending, and the expansion of support arm seems greatly the volume of remote control multi-rotor aerocraft like this, makes it in transport and carries middle inconvenience.So people have improved this fixing support arm that can not bend, in one end of support arm and the junction of fuselage, a mechanism that can bend is installed, bending mechanism is made up of permanent seat and joint and snap close, permanent seat and joint are flexibly connected by bearing pin, make the below bending of support arm to fuselage, the volume of remote control multi-rotor aerocraft has just diminished like this, is convenient to transport and carries.The mechanism that can make support arm bending has all been installed in existing most of remote control multi-rotor aerocraft.This bending mechanism contacts with the face of joint one side by the face of permanent seat one side, make support arm become horizontality, pin by snap close, the permanent seat in bending mechanism is arranged on the edge of the fine plate of carbon of fuselage, the place of bending is in again on the edge of the fine plate of carbon, although fasten fixing by snap close, but support arm has certain length, under the weight effect of the other end motor of support arm, support arm just easily produces and prizes the fine plate of carbon and produce vibrations in the upward flight of remote control multi-rotor aerocraft, this vibration influence the airworthiness of remote control multi-rotor aerocraft.What the joint in bending mechanism connected simultaneously is all pipe, electricity that can not mounted motor is adjusted (being the controller of motor), the electricity of motor is adjusted in the fine plate of carbon that is just all arranged on fuselage like this, especially more than four support arms (axle), as six, eight, 12, when 14 support arms (axle) etc., the position that the electricity of the motor in the fine plate of carbon of fuselage adjusts installation to occupy is just many, has affected other equipment that need to install in remote control multi-rotor aerocraft.Or electricity is adjusted and tied up on support arm, and electric capacity transfer is vulnerable to collision and damages, the outward appearance of the multi-rotor aerocraft of remote control is simultaneously not attractive in appearance yet.
Summary of the invention
Technical problem to be solved in the utility model is to provide a kind of electricity simple in structure, easy to use, motor and adjusts the bending mechanism that is placed in the remote control multi-rotor aerocraft support arm in support arm.In order to solve the problems of the technologies described above, the technical scheme that the utility model adopts is such: the bending mechanism of remotely-piloted vehicle support arm, described bending mechanism, comprise permanent seat, joint, snap close, bearing pin, the paired ground separated by a distance of described permanent seat distributing installation is in the centre of the fine panel area of carbon of fuselage, described joint is flexibly connected permanent seat by bearing pin, described snap close is arranged on the rear side of permanent seat, described joint is connected to the centre of permanent seat, one side of this joint is fixedly connected with pipe, the upside position, short transverse center of its opposite side is provided with salient, its top is provided with convex tendon, described snap close, comprise locking wrench, locking board, described locking wrench and locking board are flexibly connected by screw.Salient top surface in described joint is provided with circular groove.The lower surface of the locking board in described snap close is provided with fitfull circular arc protruding rail, set circular groove in this irregular roundness arc protruding rail corresponding joints, and an end surfaces of described locking wrench is supported the surface of set convex tendon one end, the top of joint.One side of described joint is fixedly connected with oval pipe, settles the electricity of DC motor to adjust in the middle of the internal diameter of described oval pipe.
The beneficial effect of support arm bending mechanism of the present utility model is: with the symmetrical installation separated by a distance in pairs of same permanent seat, the space that permanent seat is separated by holds support arm joint and is flexibly connected, so only with a permanent seat of processing, processing is simple, support arm joint stretches in the middle of two permanent seats, makes bending place in the inside position, edge of the fine plate of carbon of fuselage.Support arm prizes the fine plate of carbon of fuselage with regard to the power that is not easy to produce at remote control multi-rotor aerocraft awing, reduced this vibrations that brought to remote control multi-rotor aerocraft that prize awing.The groove of the salient in joint is pinned by the set fitfull circular arc protruding rail of the locking board in snap close, convex rib on top one side surface in joint is withstood by locking wrench one side surface in snap close again, bending part is fixed on two-bolt lock, top like this, has increased the intensity of support arm bending junction.
Brief description of the drawings
Fig. 1 is the scheme of installation of the support arm bending mechanism of the utility model remote controlled rotary-wing aircraft.
Fig. 2 is the overall structure schematic diagram of the support arm bending mechanism of the utility model remote controlled rotary-wing aircraft.
Fig. 3 is the schematic top plan view of Fig. 2.
Fig. 4 is the overall structure schematic diagram of snap close.
Fig. 5 is that the master of locking board looks schematic diagram.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the utility model will be further described.
Wherein: 1; Bending mechanism, 2:; The fine plate of carbon of fuselage,, A; Permanent seat, B; Joint, C; Snap close, D; Bearing pin, G; Oval pipe, K; Electricity is adjusted.
As shown in Figures 1 to 5, the bending mechanism of a kind of remote control multi-rotor aerocraft that the utility model provides, described bending mechanism 1, comprise permanent seat A, joint B, snap close C, bearing pin D, described permanent seat A is the centre of symmetrical distributing installation separated by a distance around the fine plate 2 of carbon of fuselage in pairs, and described joint B is flexibly connected permanent seat A by bearing pin D.Described snap close C is arranged on the rear side of permanent seat A.Described joint is movably connected in the centre of permanent seat A, a side of this joint B is fixedly connected with oval pipe G, the upside position, short transverse center of its opposite side is provided with salient B-1, and described salient B-1 upper surface is provided with the groove B-2 of circular arc, and the top of described joint B is provided with convex tendon B-3.Described snap close C; Comprise locking wrench C-1, locking board C-2, described locking wrench C-1 and locking board C-2 are flexibly connected by screw.The lower surface of locking board C-1 in described snap close C is provided with fitfull circular arc lock rail C-3, set circular groove B-2 in this fitfull circular arc lock rail C-3 corresponding joints B, rotating locking wrench C-2 makes fitfull circular arc lock rail C-3 be locked into and exit in circular groove B-2, adopt fitfull circular arc lock rail C-3, more lock is tighter in circular groove B-2 to make fitfull circular arc lock rail C-3, and also has the effect of placing restrictions on of the position of lock.The surface of set convex tendon B-3 one end, the top of joint B is supported in surface C-4, one end of described locking wrench C-2.
Joint B in the bending mechanism of remote control multi-rotor aerocraft of the present utility model extend into the centre of fixing group A, snap close C is arranged on again the rear side of permanent seat A, snap close C has in the dual-use function corresponding joints B locking and push up and also has the function of being locked and pushing up, while making support arm be in level attitude, bending place is not more firmly produced vibration by snap close, remote control multi-rotor aerocraft is just more stable awing, has improved airworthiness.
Support arm adopts oval pipe G, makes the electricity of DC machine adjust K to be arranged in the middle of the internal diameter of oval pipe G.Special in those small-sized and miniature remote control multi-rotor aerocrafts, the electricity that they must be joined is adjusted K just need not tie up on the support arm of these aircraft again or is arranged in the fine plate of carbon of fuselage, make the overall appearance of these aircraft more succinctly attractive in appearance, in the fine plate of carbon of the fuselage of these aircraft, more equipment and instrument also can be installed, increase their use function.
Claims (4)
1. the bending mechanism of remote control multi-rotor aerocraft support arm, described bending mechanism (1), comprise permanent seat (A), joint (B), snap close (C), bearing pin (D), the paired ground separated by a distance of described permanent seat (A) distributing installation is in the middle of the fine panel area of carbon of fuselage, described joint (B) is flexibly connected by bearing pin (D), described snap close (C) is arranged on the rear side of permanent seat (A), it is characterized in that: described joint (B) is connected to the centre of permanent seat (A), a side of this joint B is fixedly connected with pipe (G), the upside position, short transverse center of its opposite side is provided with salient (B-1), its top is provided with convex tendon (B-3), described snap close (C), comprise locking wrench (C-1), locking board (C-2), described locking wrench and locking board are flexibly connected by screw.
2. the bending mechanism of remote control multi-rotor aerocraft support arm according to claim 1, is characterized in that: salient (B-1) top surface in described joint (B) is provided with circular groove (B-2).
3. the bending mechanism of remote control multi-rotor aerocraft support arm according to claim 1, it is characterized in that: the lower surface of the locking board (C-1) in described snap close (C) is provided with the fitfull circular arc lock rail (C-3) of circular groove set in corresponding joints B (B-2), an end surfaces (C-4) of described locking wrench (C-2) is supported the surface of set convex tendon (B-3) one end, the top of joint (B).
4. the bending mechanism of remote control multi-rotor aerocraft support arm according to claim 1, is characterized in that; One side of described joint (B) is fixedly connected with oval pipe (G), settles the electricity of DC motor to adjust (K) in the middle of the internal diameter of described oval pipe (G).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420368236.6U CN203921185U (en) | 2014-07-06 | 2014-07-06 | The bending mechanism of remote control multi-rotor aerocraft support arm |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420368236.6U CN203921185U (en) | 2014-07-06 | 2014-07-06 | The bending mechanism of remote control multi-rotor aerocraft support arm |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203921185U true CN203921185U (en) | 2014-11-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420368236.6U Expired - Fee Related CN203921185U (en) | 2014-07-06 | 2014-07-06 | The bending mechanism of remote control multi-rotor aerocraft support arm |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104802979A (en) * | 2015-05-08 | 2015-07-29 | 重庆大学 | Multi-connecting-rod auxiliary folding mechanism with fixed sub-angle for shipborne helicopter |
| CN105752332A (en) * | 2016-04-11 | 2016-07-13 | 徐州蓝翼航空科技有限公司 | Portable foldable four-rotor aircraft |
| CN106081056A (en) * | 2016-06-21 | 2016-11-09 | 广州市红鹏直升机遥感科技有限公司 | A kind of unmanned plane horn fold mechanism |
| CN106218858A (en) * | 2016-08-04 | 2016-12-14 | 厦门南羽科技有限公司 | Horn closed block and unmanned plane for unmanned plane |
| WO2017107752A1 (en) * | 2015-12-25 | 2017-06-29 | 广州亿航智能技术有限公司 | Multirotor manned aerial vehicle having foldable arms |
| WO2017132803A1 (en) * | 2016-02-01 | 2017-08-10 | 张琬彬 | Unmanned aerial vehicle folding structure |
| WO2017132808A1 (en) * | 2016-02-01 | 2017-08-10 | 张琬彬 | Unmanned aerial vehicle irregular-shaped arm folding device |
| CN107521658A (en) * | 2016-06-22 | 2017-12-29 | 北京臻迪机器人有限公司 | A kind of unmanned plane horn fixed seat |
-
2014
- 2014-07-06 CN CN201420368236.6U patent/CN203921185U/en not_active Expired - Fee Related
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104802979A (en) * | 2015-05-08 | 2015-07-29 | 重庆大学 | Multi-connecting-rod auxiliary folding mechanism with fixed sub-angle for shipborne helicopter |
| CN104802979B (en) * | 2015-05-08 | 2017-04-19 | 重庆大学 | Multi-connecting-rod auxiliary folding mechanism with fixed sub-angle for shipborne helicopter |
| WO2017107752A1 (en) * | 2015-12-25 | 2017-06-29 | 广州亿航智能技术有限公司 | Multirotor manned aerial vehicle having foldable arms |
| WO2017132803A1 (en) * | 2016-02-01 | 2017-08-10 | 张琬彬 | Unmanned aerial vehicle folding structure |
| WO2017132808A1 (en) * | 2016-02-01 | 2017-08-10 | 张琬彬 | Unmanned aerial vehicle irregular-shaped arm folding device |
| CN105752332A (en) * | 2016-04-11 | 2016-07-13 | 徐州蓝翼航空科技有限公司 | Portable foldable four-rotor aircraft |
| CN105752332B (en) * | 2016-04-11 | 2018-05-22 | 徐州蓝翼航空科技有限公司 | A kind of portable and collapsible quadrotor |
| CN106081056A (en) * | 2016-06-21 | 2016-11-09 | 广州市红鹏直升机遥感科技有限公司 | A kind of unmanned plane horn fold mechanism |
| CN107521658A (en) * | 2016-06-22 | 2017-12-29 | 北京臻迪机器人有限公司 | A kind of unmanned plane horn fixed seat |
| CN107521658B (en) * | 2016-06-22 | 2021-09-14 | 北京臻迪机器人有限公司 | Unmanned aerial vehicle horn fixing base |
| CN106218858A (en) * | 2016-08-04 | 2016-12-14 | 厦门南羽科技有限公司 | Horn closed block and unmanned plane for unmanned plane |
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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 |
Granted publication date: 20141105 Termination date: 20170706 |
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| CF01 | Termination of patent right due to non-payment of annual fee |