CN205150232U - Coaxial double wings helicopter core and helicopter - Google Patents
Coaxial double wings helicopter core and helicopter Download PDFInfo
- Publication number
- CN205150232U CN205150232U CN201520951087.0U CN201520951087U CN205150232U CN 205150232 U CN205150232 U CN 205150232U CN 201520951087 U CN201520951087 U CN 201520951087U CN 205150232 U CN205150232 U CN 205150232U
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- rotor
- control panel
- swash plate
- helicopter
- connecting rod
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Abstract
The utility model discloses a coaxial double wings helicopter core and helicopter, include upper rotor and lower rotor through the rotation axis coaxial coupling, lower rotor wobbling server in the control, and the last lower rotor reverse rotation's of control motor, in the rotation axis includes, outer axle, upper rotor and lower rotor are connected respectively with outer axle to interior axle, upper rotor and lower rotor connect through slope dish subassembly, slope dish subassembly includes the updip sloping cam plate and has a down dip the sloping cam plate, the updip sloping cam plate all includes the inside and outside control panel of connecting through joint bearing with the sloping cam plate that has a down dip, the interior control panel of updip sloping cam plate is connected through first connecting rod and upper rotor, and along with the upper rotor antiport, the server is connected to the outer control panel of sloping cam plate of having a down dip, by server control up -down linkage, the interior control panel of sloping cam plate and the outer control panel of updip sloping cam plate of having a down dip passes through the linkage of second connecting rod, and rotate along with outer axle forward. The utility model discloses a go up lower rotor's linkage synchronization regulation, can effectively offset the moment of torsion that produces when two -layer rotor rotates, make the aircraft more stable.
Description
Technical field
The utility model relates to helicopter field, refers more particularly to a kind of coaxial dual-rotor helicopter movement and helicopter.
Background technology
Coaxial unmanned helicopter, due to No Tail Rotor, relies on the coaxial synchronized reversion of upper and lower two rotor, makes the compact conformation of itself, startup layout symmetry and hovering efficiency high, is widely applied to every field.And along with modern times investigation detection and the development of the demand such as video monitoring and multimedia shooting, miniature coaxial unmanned machine, with the advantage of its uniqueness, has captured rapidly one seat.
Although coaxial unmanned helicopter application is more and more extensive, still there are some problems, particularly for the Steering under floating state.As usually arranged trammel beam above upper rotor, when regulating upper and lower rotor to make helicopter turn to, trammel beam is due to Action of Gravity Field, remain horizontality, due to Action of Gravity Field, it pulls upper and lower rotor to playback virgin state, complete rotation direction operation, but the balance leaning on the Action of Gravity Field of trammel beam to maintain upper and lower rotor is completely very passive, and stability is very poor, for the place of some space environment complexity, use very inconvenient, a slightly slow step just may cause the accident generation, and safety is very low.
Existing also exist only regulate lower rotor to overturn the steering operation realized under floating state by tilting frame, upper rotor keeps horizontality, stability is all right, but it is very slow for overturning by means of only the lower rotor of adjustment the speed making whole helicopter turn to, and this just causes the sensitivity of steering operation also not high.
Existing depopulated helicopter cannot accomplish better coordination in stability and sensitivity, and therefore, prior art needs further to be improved.
Utility model content
Problem to be solved in the utility model is, a kind of coaxial dual-rotor helicopter movement and helicopter are provided, under solving existing depopulated helicopter floating state, turning efficiency is not good, to fly jiggly technical matters, realizing smooth flight effect more, aircraft being manipulated when not reducing stability sensitiveer.
The utility model adopts following technical scheme: a kind of coaxial dual-rotor helicopter movement, comprise the upper rotor and lower rotor that are connected by rotating shaft coaxle, the servomechanism that in control, rotor and lower rotor swing, and control the motor of upper rotor and lower rotor contrarotation, in described S. A. comprises, outer shaft, interior axle and outer shaft are connected upper rotor and lower rotor respectively, and rotor and lower rotor wing rotation is driven under motor driving, described upper rotor is connected by tilting frame assembly with lower rotor, described tilting frame assembly comprises updip swash plate and the swash plate that has a down dip, control panel inside and outside described updip swash plate and the swash plate that has a down dip are included and to be connected by oscillating bearing, the interior control panel of updip swash plate is connected with upper rotor by first connecting rod, and rotate backward with upper rotor, the outer control panel of swash plate of having a down dip connects servomechanism, linkage from top to bottom is controlled by servomechanism, the have a down dip interior control panel of swash plate and the outer control panel of updip swash plate is linked by second connecting rod, and rotate forward with outer shaft, lower rotor is arranged on second connecting rod.
Described coaxial dual-rotor helicopter movement, wherein, the interior axle of described S. A. and outer shaft are separately installed with the first gear and the second gear, described motor includes the first motor and the second motor, first motor is provided with the 3rd gear, second motor is provided with the 4th gear, described first gear engages with the 3rd gear, rotates to drive interior axle; Second gear and the engaging of the 4th gear, rotate to drive outer shaft.
Described coaxial dual-rotor helicopter movement, wherein, described first connecting rod and second connecting rod is provided with articulated section, the two by articulated section respectively with upper rotor and lower rotor pivotal joint.
Described coaxial dual-rotor helicopter movement, wherein, in the outer control panel of updip swash plate and interior control panel and the swash plate that has a down dip, control panel is provided with the first bulb, first connecting rod connects the interior control panel of updip swash plate by the first bulb, and described second connecting rod connects the outer control panel of control panel and updip swash plate in the swash plate that has a down dip respectively by the first bulb.
Described coaxial dual-rotor helicopter movement, wherein, on described rotor outer control panel on be symmetrically arranged with two turning cylinders, described S. A. is provided with clamping two rotation shaft supports, two turning cylinders are 90 degree of angles with the first bulb be arranged on the outer control panel of rotor, outer control panel axle upset centered by two turning cylinders of upper rotor.
Described coaxial dual-rotor helicopter movement, wherein, described in the have a down dip outer control panel of swash plate be provided with two the second bulbs, and connect servomechanisms respectively by two third connecting rods.
Described coaxial dual-rotor helicopter movement, wherein, described third connecting rod is elastic link, is provided with spring in it.
Described coaxial dual-rotor helicopter movement, wherein, described two the second bulbs are that 90 degree of angles are arranged, and the outer control panel of wherein one second bulb symmetric position is provided with position-limited lever, described position-limited lever is connected in a strip spacing hole vertically arranged, and when servomechanism drives the outer control panel of the swash plate that has a down dip to overturn, projection swings up and down in spacing hole.
A kind of coaxial dual-rotor helicopter, described helicopter is provided with described movement.
Compared with prior art, coaxial dual-rotor helicopter movement of the present utility model and helicopter, have following technique effect:
1) realize the synchronization regulation of two rotors, and tilted upward dish links the moment of torsion produced when effectively can offset two-layer rotor rotational simultaneously, makes aircraft more stable;
2) synchronization regulation too increases the moment of helicopter direction to control simultaneously, helicopter being manipulated when not reducing stability sensitiveer, turning to more flexible under floating state.
Accompanying drawing explanation
The constructional drawing of the coaxial dual-rotor helicopter movement that Fig. 1 provides for the utility model.
The constructional drawing of the preferred embodiment of the coaxial dual-rotor helicopter movement that Fig. 2 provides for the utility model.
The johning knot composition of motor and gear in the coaxial dual-rotor helicopter movement that Fig. 3 provides for the utility model.
The constructional drawing of the coaxial dual-rotor helicopter movement medium dip dish assembly that Fig. 4 provides for the utility model.
Detailed description of the invention
In order to make technical problem to be solved in the utility model, technical scheme and beneficial effect clearly understand, below in conjunction with drawings and Examples, the utility model is further elaborated.Should be appreciated that specific embodiment described herein only in order to explain the utility model, and be not used in restriction the utility model.
As shown in Figures 1 to 4, the coaxial dual-rotor helicopter movement that the utility model provides, comprise the upper rotor 1111 and lower rotor 12 that are connected by rotating shaft coaxle, the servomechanism 30 that in control, rotor 11 and lower rotor 12 swing, and control the motor of upper rotor 11 and the contrarotation of lower rotor 12, in described S. A. comprises, outer shaft (14, 15), interior axle 14 and outer shaft 15 are connected rotor 11 and lower rotor 12 respectively, and rotor 11 and lower rotor 12 rotate on driving under motor drives, described upper rotor 11 is connected by tilting frame assembly with lower rotor 12, described tilting frame assembly comprises updip swash plate 100 and the swash plate 200 that has a down dip, control panel inside and outside described updip swash plate 100 and the swash plate 200 that has a down dip are included and to be connected by oscillating bearing, the interior control panel 15 of updip swash plate is connected with upper rotor 11 by first connecting rod 19, and rotate backward with upper rotor 11, the outer control panel 18 of swash plate of having a down dip connects servomechanism 30, linkage from top to bottom is controlled by servomechanism 30, the have a down dip interior control panel 17 of swash plate and the outer control panel 16 of updip swash plate is linked by second connecting rod 20, and rotate forward with outer shaft 15, lower rotor 12 is arranged on second connecting rod 20.Therefore, the utility model to be had a down dip swash plate 200 assembly interlock updip swash plate 100 by adjustment, can realize the synchronization regulation of upper and lower two rotors.Owing to being that upper and lower two tilting framees link simultaneously, can the moment of torsion that produces when offsetting two-layer rotor rotational of actv., making aircraft flight more stable, increase the moment of aircraft direction to control simultaneously, aircraft being manipulated when not reducing stability sensitiveer.
Particularly, the interior axle 14 of S. A. and outer shaft 15 drive separately respectively by two motors, be respectively the first motor 31 and the second motor 32, interior axle 14 is driven to rotate by the first motor 31, outer shaft 15 is driven to rotate by the second motor 32, in connection structure, interior axle 14 and outer shaft 15 are separately installed with the first gear 33 and the second gear 34, first gear 33 and the second gear 34 are coaxially installed, and the first motor 31 and the second motor 32 arrange the 3rd gear 35 and the 4th gear 36 respectively, described first gear 33 engages with the 3rd gear 35, rotate to drive interior axle 14, and then drive upper rotor 11 to rotate, second gear 34 and the 4th gear 36 engage, rotate to drive outer shaft 15, and then drive lower rotor 12 to rotate.Control upper and lower rotor respectively by double motor, the independent adjustment manipulation in upper and lower rotor-speed can be accomplished.
In the control of two rotors, the utility model is provided with articulated section 28 respectively on two first connecting rods 19 and second connecting rod 20, the two by articulated section 28 respectively with upper rotor 11 and lower rotor 12 pivotal joint.Like this when first connecting rod 19 and second connecting rod 20 link, upper and lower rotor is synchronously overturn by pivot, more convenient and stable to the manipulation of upper and lower rotor.Further, the outer control panel 16 of described updip swash plate is symmetrically arranged with two turning cylinders 25, at described S. A. (14,15) the U support 26 of clamping two turning cylinders 25 is provided with on, two turning cylinders 25 are 90 degree of angles with the first bulb be arranged on the outer control panel 16 of updip swash plate, outer control panel 16 axle upset centered by two turning cylinders 26 of updip swash plate, to ensure the stability manipulated further.
Further, upper rotor 11 and lower rotor 12 are provided with installation portion 27, installation portion 27 is provided with two parallel mounting rods 28, mounting rod 28 arranges pivot to connect articulated section 28, and shaft (not shown) is also set on installation portion 27, shaft vertically rotor axis arrange, upper and lower rotor overturns along axis.
In the connection of tilting frame, each connecting joint arrange bulb, particularly, in the outer control panel 16 of updip swash plate and interior control panel 17 and the swash plate that has a down dip, control panel 17 is provided with the first bulb 22, first connecting rod 19 connects the interior control panel 15 of updip swash plate by the first bulb 22, and described second connecting rod 20 connects the outer control panel 16 of control panel 17 and updip swash plate in the swash plate that has a down dip respectively by the first bulb 22.The outer control panel 18 of the swash plate that has a down dip is provided with two the second bulbs 23, and connects servomechanism 30 respectively by two third connecting rods 21.The adapter shaft of two the second bulbs 23 is than the length of connection first bulb 22, so that when third connecting rod 21 pulls the outer control panel 18 of the swash plate that has a down dip, second connecting rod 20 pulls the outer control panel 16 of updip swash plate and first connecting rod 19 to pull the operation of the interior control panel 15 of updip swash plate more smooth and easy.Preferably, third connecting rod 21 of the present utility model is elastic link, is provided with spring in it.Third connecting rod 21 is set to elastic link can make the adjustment of servomechanism 30 pairs of tilting frame assemblies more flexible.
Preferably, described two the second bulbs 23 are arranged in 90 degree of angles, and the outer control panel of wherein one second bulb 23 symmetric position is provided with position-limited lever, described position-limited lever is connected in a strip spacing hole vertically arranged, and when servomechanism 30 drives the outer control panel 18 of the swash plate that has a down dip to overturn, projection swings up and down in spacing hole.Third connecting rod 21 effectively can be avoided so excessively to pull the swash plate 200 that has a down dip to make lower rotor 12 overturn excessively, ensure the safety of manipulation.
Based on above-mentioned movement, the utility model additionally provides a kind of coaxial dual-rotor helicopter, and this helicopter is provided with described movement.Coaxial dual-rotor helicopter of the present utility model is when controlling, the outer control panel of the swash plate that has a down dip is pulled to swing by servomechanism by third connecting rod, the outer control panel of swash plate of having a down dip drives the control panel in swash plate that has a down dip to swing by oscillating bearing, the interior control panel of swash plate of having a down dip drives the outer control panel of updip swash plate to swing by second connecting rod, in the process, drive lower rotor upset, and the outer control panel of updip swash plate drives control panel in updip swash plate to swing by oscillating bearing, the interior control panel of updip swash plate drives upper rotor upset by first connecting rod again, whole manipulation process is completed with this.Realize the synchronization regulation of upper and lower rotor.In manipulation process, two servomechanisms can control separately its corresponding third connecting rod connected.
In sum, the coaxial dual-rotor helicopter movement that the utility model provides and helicopter, by tilting frame assembly, achieve the interlock synchronization regulation of upper and lower rotor, the moment of torsion produced when effectively can offset two-layer rotor rotational, makes aircraft more stable; Too increasing the moment of helicopter direction to control simultaneously, helicopter being manipulated when not reducing stability sensitiveer, turn to more flexible under floating state.
Should be understood that; application of the present utility model is not limited to above-mentioned citing; for those of ordinary skills, can be improved according to the above description or convert, all these improve and convert the protection domain that all should belong to the utility model claims.
Claims (9)
1. a coaxial dual-rotor helicopter movement, comprise the upper rotor and lower rotor that are connected by rotating shaft coaxle, the servomechanism that in control, rotor and lower rotor swing, and control the motor of upper rotor and lower rotor contrarotation, it is characterized in that, in described S. A. comprises, outer shaft, interior axle and outer shaft are connected upper rotor and lower rotor respectively, and rotor and lower rotor wing rotation is driven under motor driving, described upper rotor is connected by tilting frame assembly with lower rotor, described tilting frame assembly comprises updip swash plate and the swash plate that has a down dip, control panel inside and outside described updip swash plate and the swash plate that has a down dip are included and to be connected by oscillating bearing, the interior control panel of updip swash plate is connected with upper rotor by first connecting rod, and rotate backward with upper rotor, the outer control panel of swash plate of having a down dip connects servomechanism, linkage from top to bottom is controlled by servomechanism, the have a down dip interior control panel of swash plate and the outer control panel of updip swash plate is linked by second connecting rod, and rotate forward with outer shaft, lower rotor is arranged on second connecting rod.
2. coaxial dual-rotor helicopter movement according to claim 1, it is characterized in that, the interior axle of described S. A. and outer shaft are separately installed with the first gear and the second gear, described motor includes the first motor and the second motor, first motor is provided with the 3rd gear, second motor is provided with the 4th gear, described first gear engages with the 3rd gear, rotates to drive interior axle; Second gear and the engaging of the 4th gear, rotate to drive outer shaft.
3. coaxial dual-rotor helicopter movement according to claim 1, is characterized in that, described first connecting rod and second connecting rod are provided with articulated section, the two by articulated section respectively with upper rotor and lower rotor pivotal joint.
4. coaxial dual-rotor helicopter movement according to claim 1, it is characterized in that, in the outer control panel of updip swash plate and interior control panel and the swash plate that has a down dip, control panel is provided with the first bulb, first connecting rod connects the interior control panel of updip swash plate by the first bulb, and described second connecting rod connects the outer control panel of control panel and updip swash plate in the swash plate that has a down dip respectively by the first bulb.
5. coaxial dual-rotor helicopter movement according to claim 4, it is characterized in that, on described rotor outer control panel on be symmetrically arranged with two turning cylinders, described S. A. is provided with clamping two rotation shaft supports, two turning cylinders and the first bulb are that 90 degree of angles are arranged, outer control panel axle upset centered by two turning cylinders of upper rotor.
6. coaxial dual-rotor helicopter movement according to claim 4, is characterized in that, described in the have a down dip outer control panel of swash plate be provided with two the second bulbs, and connect servomechanisms respectively by two third connecting rods.
7. coaxial dual-rotor helicopter movement according to claim 6, it is characterized in that, described third connecting rod is elastic link, is provided with spring in it.
8. coaxial dual-rotor helicopter movement according to claim 6, it is characterized in that, described two the second bulbs are that 90 degree of angles are arranged, and the outer control panel of wherein one second bulb symmetric position is provided with position-limited lever, described position-limited lever is connected in a strip spacing hole vertically arranged, and when servomechanism drives the outer control panel of the swash plate that has a down dip to overturn, projection swings up and down in spacing hole.
9. a coaxial dual-rotor helicopter, is characterized in that, described helicopter is provided with the movement as described in any one of claim 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520951087.0U CN205150232U (en) | 2015-11-25 | 2015-11-25 | Coaxial double wings helicopter core and helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520951087.0U CN205150232U (en) | 2015-11-25 | 2015-11-25 | Coaxial double wings helicopter core and helicopter |
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| Publication Number | Publication Date |
|---|---|
| CN205150232U true CN205150232U (en) | 2016-04-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520951087.0U Active CN205150232U (en) | 2015-11-25 | 2015-11-25 | Coaxial double wings helicopter core and helicopter |
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| CN (1) | CN205150232U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105480414A (en) * | 2015-11-25 | 2016-04-13 | 深圳市富微科创电子有限公司 | Coaxial double-rotor helicopter core and helicopter |
| EP3415426A1 (en) * | 2017-06-12 | 2018-12-19 | Bell Helicopter Textron Inc. | Uav rotor system |
| WO2020079649A1 (en) * | 2018-10-17 | 2020-04-23 | Jaime Guillermo Sada | A quiet redundant rotorcraft |
| US10717526B2 (en) | 2017-06-12 | 2020-07-21 | Textron Innovations Inc. | UAV with in-flight adjustable wings |
-
2015
- 2015-11-25 CN CN201520951087.0U patent/CN205150232U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105480414A (en) * | 2015-11-25 | 2016-04-13 | 深圳市富微科创电子有限公司 | Coaxial double-rotor helicopter core and helicopter |
| EP3415426A1 (en) * | 2017-06-12 | 2018-12-19 | Bell Helicopter Textron Inc. | Uav rotor system |
| US10435149B2 (en) | 2017-06-12 | 2019-10-08 | Bell Helicopter Textron Inc. | UAV rotor system |
| US10717526B2 (en) | 2017-06-12 | 2020-07-21 | Textron Innovations Inc. | UAV with in-flight adjustable wings |
| WO2020079649A1 (en) * | 2018-10-17 | 2020-04-23 | Jaime Guillermo Sada | A quiet redundant rotorcraft |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |