CN203743312U - Transmission system for unmanned rotor wing helicopter - Google Patents
Transmission system for unmanned rotor wing helicopter Download PDFInfo
- Publication number
- CN203743312U CN203743312U CN201420093835.1U CN201420093835U CN203743312U CN 203743312 U CN203743312 U CN 203743312U CN 201420093835 U CN201420093835 U CN 201420093835U CN 203743312 U CN203743312 U CN 203743312U
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- Prior art keywords
- gear
- main shaft
- driving
- driven
- transmission system
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- Expired - Fee Related
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Abstract
The utility model relates to a transmission system applied to an unmanned rotor wing helicopter. The transmission system comprises a driving shaft, a concentric driving gear fixedly arranged at the output end of the driving shaft, a driven shaft, a concentric driven gear fixedly arranged at the input end of the driven shaft, a concentric main shaft gear A and a concentric main shaft gear B, wherein the concentric main shaft gear A penetrates through a main shaft and is fixedly connected with the main shaft, and the concentric main shaft gear B is located below the main shaft gear A, penetrates through the main shaft and is movably connected with the main shaft. The unmanned rotor wing helicopter comprises a rotor wing head and a main shaft fixedly connected with the rotor wing head. The main shaft gear A, the main shaft gear B, the driving gear and the driven gear are spiral bevel gears. The driving gear and the driven gear are concentrically and symmetrically arranged. The main shaft gear A is respectively meshed with the driving gear and the driven gear. The main shaft gear B is respectively meshed with the driving gear and the driven gear. According to the transmission system, force offset is achieved, abrasion to the gears is reduced, stability of the transmission system is improved, the service life of the unmanned rotor wing helicopter is prolonged, and the production cost is reduced.
Description
Technical field
The utility model belongs to the transmission system technical field of aircraft, specifically, relates to a kind of transmission system that is applied to unmanned rotary wing helicopter.
Background technique
The transmission system of existing unmanned rotary wing helicopter is to adopt the mode of ratchet transmission to carry out transmission of power, and it is relatively simple for structure.The driving force of unmanned rotary wing lifting airscrew is larger, during gear engagement simultaneously, also can produce larger torsion and stress, the time one is long, very easily occurs the situation of gear shifting quadrant texturing, the even tired broken teeth of wearing and tearing, in the working life that has greatly shortened unmanned rotary wing helicopter, even cause the generation of security incident.
Model utility content
For solving the problems of the technologies described above, the utility model proposes a kind of elimination gear engagement torsion and stress, reduce gear wear, reduce gear tooth breakage risk, be applied to the transmission system of unmanned rotary wing helicopter.
The technical solution of the utility model is: a kind of transmission system of unmanned rotary wing helicopter, described unmanned rotary wing helicopter comprise rotor head, with the affixed main shaft of rotor head.Described transmission system comprises driving shaft, be fixedly installed on the concentric driving gear of driving shaft output terminal, driven shaft, be fixedly installed on the concentric driven gear of driven shaft input end, on described main shaft and the concentric mainshaft gear A being fixedly connected with main shaft and be positioned at described mainshaft gear A below, on described main shaft and the concentric mainshaft gear B being flexibly connected with main shaft.Described mainshaft gear A, mainshaft gear B, driving gear and driven gear are spiral bevel gear.Described driving gear and driven gear are symmetrical arranged with one heart, and described mainshaft gear A meshes with described driving gear and driven gear respectively, and described mainshaft gear B meshes with described driving gear and driven gear respectively.Described driving gear, mainshaft gear A, driven gear, mainshaft gear B between two engaging become symmetrical closed-system, this structure is dispersed to torsion and stress equilibrium that in prior art, gear bears during ratchet transmission on driving gear and driven gear, cancelling out each other of realizable force, reduce gear wear, increased the stability of transmission system.
Described mainshaft gear B is connected with described main shaft by bearing.
Described mainshaft gear A, mainshaft gear B, driving gear and driven gear outer cladding arrange lock case.
Described lock case above and below is respectively equipped with dividing plate, and dividing plate is the positioning device of mast, and effect is that main shaft is fixed and is supported.
The beneficial effects of the utility model are: the torsion technical problem of concentrating the gear wear that cause relative to stress that while having solved ratchet transmission in prior art, gear bears, the utility model is dispersed to this part torsion and stress equilibrium on driving gear and driven gear, cancelling out each other of realizable force, reduced gear wear, increased the stability of transmission system, extend the working life of device, reduced cost of production.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Wherein, 1, rotor head; 2, main shaft; 3, mainshaft gear A; 4, driving gear; 5, driving shaft; 6, lock case; 7, mainshaft gear B; 8, driven shaft; 9, driven gear; 10, bearing.
Embodiment
Below in conjunction with drawings and Examples, illustrate the utility model.
As shown in Figure 1: the utility model is the transmission system that is applied to unmanned rotary wing helicopter, unmanned rotary wing helicopter comprises rotor head 1, the main shaft 2 affixed with rotor head 1, transmission system comprises driving shaft 5, be fixedly installed on the concentric driving gear 4 of driving shaft 5 output terminals, driven shaft 8, be fixedly installed on the concentric driven gear 9 of driven shaft 8 input ends, on main shaft 2, and the concentric mainshaft gear A3 being fixedly connected with main shaft 2, be positioned at mainshaft gear A3 below, on main shaft 2, and the concentric mainshaft gear B7 being flexibly connected with main shaft 2, mainshaft gear A3, mainshaft gear B7, driving gear 4 and driven gear 9 are spiral bevel gear, driving gear 4 and driven gear 9 are symmetrical arranged with one heart, and mainshaft gear A3 meshes with driving gear 4 and driven gear 9 respectively, and mainshaft gear B7 meshes with driving gear 4 and driven gear 9 respectively.Driving gear 4, mainshaft gear A3, driven gear 9, mainshaft gear B7 between two engaging become symmetrical closed-system, this structure is dispersed to torsion and stress equilibrium that in prior art, gear bears during ratchet transmission on driving gear 4 and driven gear 9, cancelling out each other of realizable force, reduce gear wear, increased the stability of transmission system.
Mainshaft gear B7 is connected with main shaft 2 by bearing 10.
Mainshaft gear A3, mainshaft gear B7, driving gear 4 and driven gear 9 outer claddings arrange lock case 6.
Lock case 6 above and belows are respectively equipped with dividing plate 11.Dividing plate is the positioning device of mast 2, and effect is that main shaft 2 is fixed and is supported.
Working procedure of the present utility model is as follows:
During the operation aloft of unmanned rotary wing helicopter, the motor of driving shaft 5 provides power, driving shaft 5 High Rotation Speeds, and driving gear 4 rotates with mainshaft gear A3 and mainshaft gear B7 interlock respectively, drives driven gear 9 rotations simultaneously.As shown in Figure 1, suppose that driving shaft rotates along the diagram direction of arrow, drive driving gear 4 rotating Vortexes simultaneously, mainshaft gear A3 rotates from left to right, drives rotor head 1 rotating Vortex, drives driven gear 9 by the direction rotation with driving shaft 5 switched in opposite simultaneously.
Claims (4)
1. the transmission system of a unmanned rotary wing helicopter, described unmanned rotary wing helicopter comprises rotor head (1), the main shaft (2) affixed with rotor head (1), it is characterized in that: described transmission system comprises driving shaft (5), be fixedly installed on the concentric driving gear (4) of driving shaft (5) output terminal, driven shaft (8), be fixedly installed on the concentric driven gear (9) of driven shaft (8) input end, on main shaft (2), and the concentric mainshaft gear A (3) being fixedly connected with main shaft (2), and be positioned at below mainshaft gear A (3), on main shaft (2), and the concentric mainshaft gear B (7) being flexibly connected with main shaft (2), described mainshaft gear A (3), mainshaft gear B (7), driving gear (4) and driven gear (9) are spiral bevel gear, driving gear (4) and driven gear (9) are symmetrical arranged with one heart, mainshaft gear A (3) meshes with driving gear (4) and driven gear (9) respectively, and mainshaft gear B (7) meshes with driving gear (4) and driven gear (9) respectively.
2. the transmission system of unmanned rotary wing helicopter according to claim 1, is characterized in that, the mainshaft gear B of institute (7) is connected with main shaft (2) by bearing (10).
3. the transmission system of unmanned rotary wing helicopter according to claim 1, is characterized in that, the mainshaft gear A of institute (3), mainshaft gear B (7), driving gear (4) and driven gear (9) outer cladding arrange lock case (6).
4. the transmission system of unmanned rotary wing helicopter according to claim 3, is characterized in that, described lock case (6) above and below is respectively equipped with dividing plate (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420093835.1U CN203743312U (en) | 2014-03-03 | 2014-03-03 | Transmission system for unmanned rotor wing helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420093835.1U CN203743312U (en) | 2014-03-03 | 2014-03-03 | Transmission system for unmanned rotor wing helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203743312U true CN203743312U (en) | 2014-07-30 |
Family
ID=51343115
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420093835.1U Expired - Fee Related CN203743312U (en) | 2014-03-03 | 2014-03-03 | Transmission system for unmanned rotor wing helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203743312U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103791029A (en) * | 2014-03-03 | 2014-05-14 | 青岛宏百川金属精密制品有限公司 | Transmission system of unmanned rotor wing helicopter |
-
2014
- 2014-03-03 CN CN201420093835.1U patent/CN203743312U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103791029A (en) * | 2014-03-03 | 2014-05-14 | 青岛宏百川金属精密制品有限公司 | Transmission system of unmanned rotor wing helicopter |
| CN103791029B (en) * | 2014-03-03 | 2017-01-18 | 青岛宏百川金属精密制品有限公司 | Transmission system of unmanned rotor wing helicopter |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PP01 | Preservation of patent right |
Effective date of registration: 20160128 Granted publication date: 20140730 |
|
| RINS | Preservation of patent right or utility model and its discharge | ||
| PD01 | Discharge of preservation of patent |
Date of cancellation: 20160728 Granted publication date: 20140730 |
|
| RINS | Preservation of patent right or utility model and its discharge | ||
| 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: 20140730 Termination date: 20160303 |