CN205418096U - First structure of unmanned helicopter rotor - Google Patents
First structure of unmanned helicopter rotor Download PDFInfo
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- CN205418096U CN205418096U CN201620228571.5U CN201620228571U CN205418096U CN 205418096 U CN205418096 U CN 205418096U CN 201620228571 U CN201620228571 U CN 201620228571U CN 205418096 U CN205418096 U CN 205418096U
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- main shaft
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- middle connection
- groove
- transverse axis
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Abstract
The utility model relates to an unmanned air vehicle technique field, concretely relates to first structure of unmanned helicopter rotor, include that the well connection of being connected with the power unit main shaft constructs, the rotary type was connected and axis of rotation heart yearn level between the upper end of main shaft and well connection constructed, the rotor and the well antithetical couplet structural connection of unmanned helicopter, the axle body of well connection structure and main shaft constitutes the cooperation of pegging graft, is provided with the damping piece between well connection structure and the main shaft, the structural cross axle that is provided with of well antithetical couplet, and the one end of cross axle is planted in the recess that the one end that the oar pressed from both sides was offered, is provided with the bearing between cross axle and the recess, lie in still to be provided with plugging block between notch and the cross axle of recess, plugging block communicates with cross axle constitution rotary type cooperation, the vallecular cavity that is provided with oil filler point and recess on the oar presss from both sides. Above -mentioned rotor head structure has prolonged the life of main shaft and well connection structure, has reduced the whole mechanical oscillation of unmanned helicopter rotor head, can avoid lubricating grease to throw away the oar moreover and press from both sides, still ensures the lubricated effect of bearing.
Description
Technical field
The utility model relates to unmanned air vehicle technique field, is specifically related to a kind of depopulated helicopter rotor head structure.
Background technology
Multiaxis depopulated helicopter is a kind of by radio robot or the airborne vehicle driven by programme-control autopilot facility, is also widely used at civil area in recent years.Conventional multi-axis depopulated helicopter includes the multiple rotors arranged on body and body, each rotor is connected with the drive shaft of the drive mechanism each arranged on body, drive mechanism drives rotor High Rotation Speed in atmosphere, constantly air is pushed to lower section, thus produce lift upwards, drive aircraft upwards to fly.Simultaneously by the drive shaft speed of flight controller regulation drive mechanism, thus the Indirect method propulsive force of each drive shaft.The thrust difference of each drive shaft just can control the skyborne incline direction of aircraft and angle, and after aircraft inclination, rotor just can allow aircraft fly to front and indirectly control the speed flown after producing horizontal component.
nullThe rotor of tradition depopulated helicopter typically realizes being connected by middle connection structure with the main shaft of drive mechanism，Middle connection structure is connected with oar folder，Oar folder is connected with rotor，Oar sandwiched of the prior art is set to tubular structure，The transverse axis being connected with middle connection structure is placed through in the tube chamber of oar folder，It is provided with bearing between the tube chamber of transverse axis and oar folder，Lubricant grease it is passed through in pipe，One pipe end of oar folder with middle connection structure is arranged to closing in shape structure，Thus can avoid rotor during rotating，Bearing throws away the tube chamber of oar folder，The other end at oar folder is provided with opening，The plate of rotor is positioned at this opening，Bolt is utilized to realize rotor and being connected that oar presss from both sides，Above-mentioned oar folder is logical tubular structure，Rotor is during rotating，Owing to the lubricant grease in siphunculus is easily thrown away by the effect of centrifugal force，Cause bearing lubrication inadequate，Bearing is easy to damage.And existing middle construction weight is big and structure is complicated, it is not easy to safeguard very much, the connected mode of the main shaft of middle connection structure and depopulated helicopter drive mechanism mostly is the socket connection in hole and axle, and the big oar installed on rotor head often revolves to turn around and all can swing up and down in the cycle once, main shaft understands direct collision below middle, thus middle will soon connect in damaging structure be easy to abrasion, service life is short.
Utility model content
The purpose of this utility model is: provide a kind of depopulated helicopter rotor head structure, it is possible to while connecting the abrasion between structure and main shaft in minimizing, it is to avoid lubricant grease throws away oar folder.
For achieving the above object, the technical solution adopted in the utility model is: depopulated helicopter rotor head structure, including the middle connection structure being connected with actuating unit main shaft, between the upper end of described main shaft with middle connection structure, rotary type is connected and rotary shaft cord horizontal, the rotor of depopulated helicopter is connected with middle connection structure, described middle connection structure constitutes grafting with the axle body of main shaft and coordinates, it is provided with damping block between middle connection structure and main shaft, it is provided with transverse axis on middle connection structure, one end of transverse axis is plugged in the groove offered of one end of oar folder, bearing it is provided with between transverse axis and groove, it is additionally provided with plugging block between the notch and transverse axis of groove, described plugging block constitutes rotary type with transverse axis and coordinates, it is provided with oil filler point on oar folder to connect with the vallecular cavity of groove.
nullCompared with prior art，The technique effect that the utility model possesses is: the main shaft of drive mechanism constitutes rotary type with middle connection structure and is connected，And middle connection structure and main axis formula position are as the fulcrum of seesaw，Damping block below International Liaison Department of the CPC Central Committee's part bears the swing impact of middle connection structure，The lower step avoiding middle connection structure is directly collided with depopulated helicopter main shaft，Effectively extend depopulated helicopter main shaft and the service life of middle connection structure，The cushioning effect of damping block also reduces the overall mechanical oscillation of depopulated helicopter rotor head simultaneously，Oar is pressed from both sides and offers groove，One end of transverse axis is plugged in groove，Bearing is set between transverse axis and groove，It is fast that notch at groove arranges closure，Material is thus formed the shoe cream room more closed，Oar folder is provided with oil filler point，Thus facilitate injection lubricant grease in the vallecular cavity of groove，After in the vallecular cavity of lubricant grease injection groove，Rotor is during rotating，Lubricant grease can be avoided to throw away oar folder，Also assure that the lubricant effect of bearing.
Accompanying drawing explanation
Fig. 1 is the structural representation that depopulated helicopter rotor head is taken apart；
Fig. 2 is the structural representation at another visual angle that depopulated helicopter rotor head is taken apart；
Fig. 3 is the structural representation of depopulated helicopter rotor head；
Fig. 4 is depopulated helicopter rotor clamping structure cut-away illustration.
Detailed description of the invention
In conjunction with Fig. 1 to Fig. 4, the utility model is further described:
nullDepopulated helicopter rotor head structure，Including the middle connection structure 20 being connected with actuating unit main shaft 10，Between the upper end of described main shaft 10 with middle connection structure 20, rotary type is connected and rotary shaft cord horizontal，The rotor 80 of depopulated helicopter is connected with middle connection structure 20，Described middle connection structure 20 constitutes grafting with the axle body of main shaft 10 and coordinates，It is provided with damping block 30 between middle connection structure 20 and main shaft 10，It is provided with transverse axis 40 on middle connection structure 20，One end of transverse axis 40 is plugged in the groove 51 offered of one end of oar folder 50，Bearing 60 it is provided with between transverse axis 40 and groove 51，It is additionally provided with plugging block 70 between the notch and transverse axis 40 of groove 51，Described plugging block 70 constitutes rotary type with transverse axis 40 and coordinates，It is provided with oil filler point 52 on oar folder 50 to connect with the vallecular cavity of groove 51.
In conjunction with Fig. 1 and Fig. 4, abandon in prior art, the drawback of the easy abrasion that middle connection structure 20 and the connected mode of main shaft 10 empty set are brought, the rotary type that the upper end of main shaft 10 is constituted with middle connection structure 20 is connected, make middle connection structure 20 and main shaft 10 rotary type position as the fulcrum of seesaw, damping block 30 below International Liaison Department of the CPC Central Committee's part 20 bears the swing impact of middle connection structure 20, avoid middle connection structure 20 bottom directly to collide with depopulated helicopter main shaft 10, effectively extend depopulated helicopter main shaft 10 and the service life of middle connection structure 20, the cushioning effect of damping block 30 also reduces the overall mechanical oscillation of depopulated helicopter rotor head simultaneously.And groove 51 will be offered on oar folder 50, one end of transverse axis 40 is plugged in groove 51, arranging bearing 60 between transverse axis 40 and groove 51, the notch at groove 51 arranges closure fast 70, material is thus formed the shoe cream room more closed, oar folder is provided with oil filler point 52, thus facilitating in the vallecular cavity of groove 51 injection lubricant grease, after lubricant grease injects in the vallecular cavity of groove 51, rotor 80 is during rotating, lubricant grease can be avoided to throw away oar folder 50, and then guarantee the lubricant effect of bearing 60.
As preferred version of the present utility model, described middle connection structure 20 is mutually to be fastened by two lobe body formula structures to constitute, described main shaft 10 is between two lobe body formula structures, the upper end of main shaft 10 is provided with bearing pin 11, the bar length direction of described bearing pin 11 is vertical with main shaft 10 length direction and stretches out the two ends of main shaft 10, the two ends of bearing pin 11 are respectively arranged with rolling bearing 111, and rolling bearing 111 constitutes rotary type with two lobe body formula structures of middle connection structure 20 and coordinates.Middle connection structure 20 is used two lobe body formula structures, the installation of structure 20 is connect in Fang Bian, utilize the rolling bearing 111 that bearing pin 11 and two ends thereof are arranged, the abrasion causing main shaft 10 and middle connection structure 20 when depopulated helicopter rotor floats can be reduced further, further increasing the service life of middle connection structure 20.
Further, it is provided with the draw-in groove 21 for accommodating damping block 30 between two lobe body formula structures of described middle connection structure 20, described draw-in groove 21 is provided with two between two lobe body formula structures of middle connection structure 20, and relative and along main shaft 10 the shaft core of the notch of draw-in groove 21 is arranged symmetrically with.Main shaft 10 is held tightly by the damping block 30 arranged in two draw-in grooves 21, and the torsion that main shaft 10 bears is applied to damping block 30, thus further reduces the abrasion of main shaft 10.
Described damping block 30 is made up of elastomeric material, and the rubber at this can use elastic caoutchouc, so that damping block 30 can absorb enough impact energys, reduces abrasion.
It is connected and being fastenedly connected of draw-in groove 50 for connecting two lobe body formula structures of structure 20 in implementing, the flute length direction of described draw-in groove 21 is vertical with the length direction of main shaft 10, it is provided with installing hole 211 on the groove arm of draw-in groove 21, bolt is installed connected with two lobe body formula structures of middle connection structure 20 through installing hole 211 and two ends.Install bolt realize in connect structure 20 two lobe body formula structures be connected and draw-in groove 21 be fastenedly connected both be fastenedly connected.After infringement occurs in above-mentioned damping block 30, unload installation bolt can complete to change and safeguard.
As further preferred scheme of the present utility model, shown in Fig. 4, the axle head of described transverse axis 40 arranges T-shaped structure, described bearing 60 be set on the axle body of transverse axis 40 and outer ring and groove 51 vallecular cavity against.Owing to T-shaped transverse axis 40 is that solid forging machine-shaping can bear bigger big oar rotary centrifugal force, and tradition depopulated helicopter transverse axis 40 uses cap nut to fix oar folder 50 and bearing 60, because thread contact lifting surface area Limited Phase is relatively limited to the centrifugal force also ratio that can bear oar folder 50 rotation.
For implementing plugging block 50 Fast Installation, described plugging block 70 is circulus, and described oar folder 50 is provided with installing hole, is provided with installation bolt 71 in installing hole, installs bolt 71 and is connected with plugging block 70 through installing hole.
For improving the effect of rotational support, described bearing 60 is positioned on transverse axis 40 and is provided with two.
The other end of oar folder 50 is provided with opening 53, and rotor 80 is positioned at this opening 53, and the oar folder 50 at opening 53 place is provided with bolt 81, and bolt 81 passes oar folder 50 and rotor 80 and external part is provided with nut.
Transverse axis 40 and a side lobe body formula structure laminating of middle connection structure 20, transverse axis 40 is provided with fixed block 90, fixed block 90 is provided with bolt connected with a side lobe body formula structure of middle connection structure 20.
Claims (10)
- null1. depopulated helicopter rotor head structure，It is characterized in that: include the middle connection structure (20) being connected with actuating unit main shaft (10)，Between the upper end of described main shaft (10) with middle connection structure (20), rotary type is connected and rotary shaft cord horizontal，The rotor (80) of depopulated helicopter is connected with middle connection structure (20)，Described middle connection structure (20) constitutes grafting with the axle body of main shaft (10) and coordinates，It is provided with damping block (30) between middle connection structure (20) and main shaft (10)，It is provided with transverse axis (40) on middle connection structure (20)，One end of transverse axis (40) is plugged in the groove (51) offered of one end of oar folder (50)，Bearing (60) it is provided with between transverse axis (40) and groove (51)，It is positioned between the notch of groove (51) and transverse axis (40) and is additionally provided with plugging block (70)，Described plugging block (70) constitutes rotary type with transverse axis (40) and coordinates，It is provided with oil filler point (52) on oar folder (50) to connect with the vallecular cavity of groove (51).
- Depopulated helicopter rotor head structure the most according to claim 1, it is characterized in that: described middle connection structure (20) is mutually to be fastened by two lobe body formula structures to constitute, described main shaft (10) is between two lobe body formula structures, the upper end of main shaft (10) is provided with bearing pin (11), the bar length direction of described bearing pin (11) is vertical with main shaft (10) length direction and stretches out the two ends of main shaft (10), the two ends of bearing pin (11) are respectively arranged with rolling bearing (111), rolling bearing (111) constitutes rotary type with two lobe body formula structures of middle connection structure (20) and coordinates.
- Depopulated helicopter rotor head structure the most according to claim 2, it is characterized in that: between two lobe body formula structures of described middle connection structure (20), be provided with the draw-in groove (21) for accommodating damping block (30), described draw-in groove (21) is positioned between two lobe body formula structures of middle connection structure (20) and is provided with two, and the notch of draw-in groove (21) relatively and is arranged symmetrically with along the shaft core of main shaft (10).
- Depopulated helicopter rotor head structure the most according to claim 3, it is characterised in that: described damping block (30) is made up of elastomeric material.
- Depopulated helicopter rotor head structure the most according to claim 3, it is characterized in that: the flute length direction of described draw-in groove (21) is vertical with the length direction of main shaft (10), it is provided with installing hole (211) on the groove arm of draw-in groove (21), bolt is installed connected with two lobe body formula structures of middle connection structure (20) through installing hole (211) and two ends.
- Depopulated helicopter rotor head structure the most according to claim 2, it is characterized in that: the axle head of described transverse axis (40) arranges T-shaped structure, described bearing (60) be set on the axle body of transverse axis (40) and outer ring and groove (51) vallecular cavity against.
- Depopulated helicopter rotor head structure the most according to claim 6, it is characterized in that: described plugging block (70) is circulus, it is provided with installing hole on described oar folder (50), it is provided with installation bolt (71) in installing hole, bolt (71) is installed and is connected with plugging block (70) through installing hole.
- Depopulated helicopter rotor head structure the most according to claim 6, it is characterised in that: described bearing (60) is positioned on transverse axis (40) and is provided with two.
- Depopulated helicopter rotor head structure the most according to claim 6, it is characterized in that: the other end of oar folder (50) is provided with opening (53), rotor (80) is positioned at this opening (53), being provided with bolt (81) on oar folder (50) at opening (53) place, bolt (81) presss from both sides (50) and rotor (80) through oar and external part is provided with nut.
- Depopulated helicopter rotor head structure the most according to claim 6, it is characterized in that: transverse axis (40) and a side lobe body formula structure laminating of middle connection structure (20), it is provided with fixed block (90) on transverse axis (40), fixed block (90) is provided with bolt connected with a side lobe body formula structure of middle connection structure (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620228571.5U CN205418096U (en) | 2016-03-21 | 2016-03-21 | First structure of unmanned helicopter rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620228571.5U CN205418096U (en) | 2016-03-21 | 2016-03-21 | First structure of unmanned helicopter rotor |
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| Publication Number | Publication Date |
|---|---|
| CN205418096U true CN205418096U (en) | 2016-08-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620228571.5U Expired - Fee Related CN205418096U (en) | 2016-03-21 | 2016-03-21 | First structure of unmanned helicopter rotor |
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| Country | Link |
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| CN (1) | CN205418096U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106438664A (en) * | 2016-11-08 | 2017-02-22 | 芜湖万户航空航天科技有限公司 | Tail shaft component of unmanned aerial vehicle |
| CN106516107A (en) * | 2016-11-08 | 2017-03-22 | 芜湖万户航空航天科技有限公司 | Tail slurry clamp shaft |
| CN107140202A (en) * | 2017-05-12 | 2017-09-08 | 上海寅翅智能科技有限公司 | A kind of centrifugal flapping hinge rotor head |
| CN107140185A (en) * | 2017-05-22 | 2017-09-08 | 程伯儒 | A kind of intelligent multi-rotor unmanned aerial vehicle |
| CN107310721A (en) * | 2017-07-17 | 2017-11-03 | 飞瑞航空科技（江苏）有限公司 | A kind of depopulated helicopter rotor oar clamp mechanism |
| CN107662704A (en) * | 2017-10-23 | 2018-02-06 | 郑州方达电子技术有限公司 | Depopulated helicopter main rotor propeller hub mechanism |
-
2016
- 2016-03-21 CN CN201620228571.5U patent/CN205418096U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106438664A (en) * | 2016-11-08 | 2017-02-22 | 芜湖万户航空航天科技有限公司 | Tail shaft component of unmanned aerial vehicle |
| CN106516107A (en) * | 2016-11-08 | 2017-03-22 | 芜湖万户航空航天科技有限公司 | Tail slurry clamp shaft |
| CN107140202A (en) * | 2017-05-12 | 2017-09-08 | 上海寅翅智能科技有限公司 | A kind of centrifugal flapping hinge rotor head |
| CN107140202B (en) * | 2017-05-12 | 2023-06-20 | 郑可为 | Centrifugal swing hinge rotor head |
| CN107140185A (en) * | 2017-05-22 | 2017-09-08 | 程伯儒 | A kind of intelligent multi-rotor unmanned aerial vehicle |
| CN107140185B (en) * | 2017-05-22 | 2018-12-28 | 广东利美隆文化股份有限公司 | A kind of intelligence multi-rotor unmanned aerial vehicle |
| CN107310721A (en) * | 2017-07-17 | 2017-11-03 | 飞瑞航空科技（江苏）有限公司 | A kind of depopulated helicopter rotor oar clamp mechanism |
| CN107662704A (en) * | 2017-10-23 | 2018-02-06 | 郑州方达电子技术有限公司 | Depopulated helicopter main rotor propeller hub mechanism |
| CN107662704B (en) * | 2017-10-23 | 2023-11-03 | 河南方达空间信息技术有限公司 | Unmanned helicopter main rotor hub mechanism |
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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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160803 Termination date: 20190321 |