CN107200122A - DCB Specimen bypass system based on Bevel Gear Transmission - Google Patents
DCB Specimen bypass system based on Bevel Gear Transmission Download PDFInfo
- Publication number
- CN107200122A CN107200122A CN201710423778.7A CN201710423778A CN107200122A CN 107200122 A CN107200122 A CN 107200122A CN 201710423778 A CN201710423778 A CN 201710423778A CN 107200122 A CN107200122 A CN 107200122A
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- CN
- China
- Prior art keywords
- rotor
- gear
- bevel gear
- bypass system
- dcb specimen
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000005540 biological transmission Effects 0.000 title claims abstract description 17
- 230000007246 mechanism Effects 0.000 claims abstract description 38
- 230000000694 effects Effects 0.000 abstract description 7
- 230000001360 synchronised effect Effects 0.000 abstract description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000001151 other effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 230000003319 supportive effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
- B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/02—Gearboxes; Mounting gearing therein
- F16H57/038—Gearboxes for accommodating bevel gears
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gear Transmission (AREA)
- Retarders (AREA)
Abstract
The present invention, which is disclosed, is related to culvert type rotor wing unmanned aerial vehicle technical field, specifically related to a kind of DCB Specimen bypass system based on Bevel Gear Transmission, it includes the first rotor mechanism, second rotor mechanism, duct, bevel gear, motor input shaft, multiple support equipment gears, many Auxiliary support axles, first rotor mechanism includes first gear and the first rotor in the middle of first gear, second rotor mechanism includes second gear and the second rotor in the middle of second gear, the DCB Specimen bypass system is rotated by motor belt motor dynamic bevel gear, bevel gear drives first gear simultaneously, second gear rotates, it that is to say the in opposite direction of the first rotor and the second rotor wing rotation and both rotations, the first rotor is linked together with the second rotor by connecting shaft simultaneously, first rotor and the second rotor realize synchronized reversion, the moment of torsion of the first rotor and the second rotor can effectively be eliminated, the more convenient gesture stability realized to unmanned plane, improve using effect.
Description
Technical field
The present invention relates to culvert type rotor wing unmanned aerial vehicle technical field, more particularly to a kind of bispin based on Bevel Gear Transmission
Wing bypass system.
Background technology
Culvert type rotor wing unmanned aerial vehicle is a kind of device with high lift-drag ratio, and built-in paddle blade structure is protected as rotor structure
Rotor mechanism has been protected from external object collision or the influence of gas shock, the security and anti-interference energy of unmanned plane is improved
Power.The mechanism of the offer power of culvert type rotor wing unmanned aerial vehicle is rotor structure, and rotor structure is generally DCB Specimen, and bispin wing structure is set
Put in the inside of duct, DCB Specimen is arranged in parallel, it is possible to achieve VTOL and hovering, moment of torsion of cancelling out each other effect, no
Special landing site is needed, is also convenient for realizing the control to unmanned plane aerial statue.At present, two rotors in bispin wing structure
For upper rotor and lower rotor, upper rotor is connected by connecting shaft motor corresponding with its, and its corresponding motor is arranged on rotation
The top of the wing.Lower rotor is connected by connecting shaft motor corresponding with its, and its corresponding motor is arranged on the lower section of lower rotor,
Two motors for providing power are arranged at outside, are easily damaged, and the heavier-weight of two motors, and there is also by mistake for synchronism
Difference, aerodynamic arrangement's structure is bad, so as to influence the control to unmanned plane, using effect is poor.
The content of the invention
The technical problems to be solved by the invention are to provide a kind of simple in construction, using effect and preferably passed based on bevel gear
Dynamic DCB Specimen bypass system.
The present invention solves the DCB Specimen bypass system based on Bevel Gear Transmission that its technical problem is used, including the first rotation
Wing mechanism, the second rotor mechanism, duct, bevel gear, motor input shaft, multiple support equipment gears, many Auxiliary support axles；
First rotor mechanism is identical and arranged in parallel with the second rotor mechanism structure, and the first rotor mechanism is arranged on
The top of second rotor mechanism, the first rotor mechanism includes first gear and the first rotor in the middle of first gear, the
Two rotor mechanisms include second gear and the second rotor in the middle of second gear, and the first rotor and the second rotor pass through even
Spindle links together；
Motor input shaft one end is connected with bevel gear, and a support equipment gear is set by an Auxiliary support axle connection
Between first gear, second gear, Auxiliary support axle is arranged on duct, and bevel gear, support equipment gear are respectively with first
Gear, second gear, which match, engages connection, and bevel gear and first gear, second gear are perpendicular, the first rotor and second
Rotor can rotate around connecting shaft, and a support equipment gear can rotate around its corresponding Auxiliary support axle；
Duct, which includes being provided with inwall, the circular ring structure of outer wall, inwall on the first circumferential weld, the second circumferential weld, outer wall, to be set
There is axis hole, the matching of motor input shaft is arranged on duct through axis hole, bevel gear, first gear, second gear, support equipment gear
Inwall, between outer wall, the first rotor is located at the first circumferential weld with first gear connection, the second rotor and second gear phase
Junction is located at the second circumferential weld.
It is further that first gear, second gear are shaped as circle, support equipment gear, the number of Auxiliary support axle
Measure as 2.
It is further that bevel gear, 2 support equipment gears are the distance between adjacent equal.
It is further to be provided with 3rd bearing between a support equipment gear and an Auxiliary support axle.
It is further that clutch shaft bearing is provided between the first rotor and connecting shaft, is set between the second rotor and connecting shaft
It is equipped with second bearing.
It is further that connecting shaft is provided at both ends with locking cap.
The beneficial effects of the invention are as follows：
1st, the input shaft of motor is connected with motor, and band dynamic bevel gear rotation, bevel gear drives first gear, second simultaneously
Gear rotates, that is to say the first rotor and the second rotor wing rotation and both rotate it is in opposite direction, while the first rotor and second
Rotor is linked together by connecting shaft, and the first rotor and the second rotor realize synchronized reversion, can effectively eliminate the first rotation
The moment of torsion of the wing and the second rotor, is more convenient to realize the gesture stability to unmanned plane, improves using effect.
2nd, motor is arranged on the sidepiece of the first rotor and the second rotor, and motor is arranged on to the inside of unmanned plane body, electricity
Machine and the first rotor mechanism and the second rotor mechanism are relatively independent, are effectively protected motor, improve the service life of motor,
Its fault rate is reduced, while motor is no longer arranged on the top or bottom of the first rotor and the second rotor, it is to avoid motor pair
Gas flow-disturbing is produced when the first rotor and the work of the second rotor, its delivery efficiency and using effect is improved.
3rd, realize that the first rotor is inverted at the same speed with the second rotor by a motor, reduce the quantity of motor, improve
The utilization rate of motor, using gear drive come transfer motion power, optimizes transmission mechanism layout, simplifies whole DCB Specimen duct system
System, reduces the overall weight of unmanned plane, improves the performance of unmanned plane, is more convenient to realize the gesture stability to unmanned plane.
4th, bevel gear, first gear, second gear, support equipment gear are arranged between the inwall of duct, outer wall, and first
Rotor is located at the first circumferential weld with first gear connection, and the second rotor is located at the second circumferential weld with second gear connection
Place, it is seen then that except the first rotor with the second rotor is naked is exposed on the external, remaining part is arranged in duct, to all parts
Protected, improve its service life, reduce fault rate.
Brief description of the drawings
Fig. 1 is the main structure diagram of the present invention；
Fig. 2 is the structural representation of the invention without duct；
Fig. 3 is the structural representation that the present invention has duct；
Parts, position and numbering in figure：Duct 1, bevel gear 2, motor input shaft 3, support equipment gear 4, auxiliary branch
Support axle 5, first gear 61, the first rotor 62, second gear 71, the second rotor 72, connecting shaft 8, locking cap 9.
Embodiment
The invention will be further described below in conjunction with the accompanying drawings.
As shown in Figure 1, Figure 2, Figure 3 shows, the DCB Specimen bypass system of the invention based on Bevel Gear Transmission, including the first gyroplane
Structure, the second rotor mechanism, duct 1, bevel gear 2, motor input shaft 3, multiple support equipment gears 4, many Auxiliary support axles 5；
First rotor mechanism is identical and arranged in parallel with the second rotor mechanism structure, the first rotor mechanism and second
The shapes and sizes all same of rotor mechanism, the first rotor mechanism (upper rotor) is arranged on the upper of the second rotor mechanism (lower rotor)
Side.Wherein the first rotor mechanism includes first gear 61 and the first rotor 62 in the middle of first gear 61, the second rotor
Mechanism includes second gear 71 and the second rotor 72 in the middle of second gear 71, and the first rotor 62 and the second rotor 72 are logical
Connecting shaft 8 is crossed to link together；
The one end of motor input shaft 3 is connected with bevel gear 2, and the other end of motor input shaft 3 is connected with motor, and motor is set
In the first rotor mechanism and the sidepiece of the second rotor mechanism, in the body of unmanned plane.One support equipment gear 4 passes through one
The connection of root Auxiliary support axle 5 is arranged between first gear 61, second gear 71, and Auxiliary support axle 5 is arranged on duct 1, cone
Gear 2, support equipment gear 4 match to engage respectively with first gear 61, second gear 71 to be connected, and bevel gear 2 and first
Gear 61, second gear 71 are perpendicular, and transmission efficiency is high, and stability in use is good, and the first rotor 62 and the second rotor 72 can be around
Connecting shaft 8 rotates, and a support equipment gear 4 can rotate around its corresponding Auxiliary support axle 5；
Duct 1, which includes being provided with inwall, the circular ring structure of outer wall, inwall on the first circumferential weld, the second circumferential weld, outer wall, to be set
There is axis hole, motor input shaft 3 is matched through axis hole, and bevel gear 2, first gear 61, second gear 71, support equipment gear 4 are set
Put between the inwall, outer wall of duct 1, the first rotor 62 is located at the first circumferential weld with the connection of first gear 61, the second rotation
The wing 72 is located at the second circumferential weld with the connection of second gear 71.It can be seen that, except the first rotor 62 and the second rotor 72 it is exposed
Outside, remaining part is arranged in duct 1, and all parts are protected, and improves its service life, reduces fault rate.
Specifically, because duct 1 includes the circular ring structure of inwall, outer wall, first gear 61, second gear 71 are arranged on culvert
Between the inwall in road 1, outer wall, so first gear 61, second gear 71 is conveniently of circular shape, as shown in Figure 1 and Figure 2.Branch
Support equipment gear 4, Auxiliary support axle 5 play a supportive role, and auxiliary bevel gear 2 completes the transmission of power, support equipment gear 4, auxiliary
The quantity for helping support shaft 5 is preferably 2, and between bevel gear 2 and 2 support threes of equipment gear 4, the distance between adjacent phase
Deng.
In transmission dynamic process, the first rotor 62 need to rotate with the second rotor 72 around connecting shaft 8, a support assist tooth
Wheel 4 need to rotate around its corresponding Auxiliary support axle 5, for the ease of the first rotor 62, the second rotor 72, support equipment gear
4 rotation, 3rd bearing, the first rotor and connecting shaft are provided between a support equipment gear 4 and an Auxiliary support axle 5
Clutch shaft bearing is provided between 8, second bearing is provided between the second rotor 72 and connecting shaft 8.Used to be further ensured that
Security, connecting shaft 8 is provided at both ends with locking cap 9.
In summary, the present invention has good beneficial effect, specific as follows：
1st, motor input shaft 3 is connected with motor, band dynamic bevel gear 2 rotate, bevel gear 2 simultaneously drive first gear 61,
Second gear 71 rotates, that is to say the first rotor 62 rotated with the second rotor 72 and both rotation it is in opposite direction, while first
Rotor 62 is linked together with the second rotor 72 by connecting shaft 8, and the first rotor 62 and the second rotor 72 realize synchronized reversion, energy
Enough moments of torsion for effectively eliminating the first rotor 62 and the second rotor 72, are more convenient to realize the gesture stability to unmanned plane, improve
Using effect.
2nd, motor is arranged on the sidepiece of the first rotor 62 and the second rotor 72, and motor is arranged in unmanned plane body
Portion, motor and the first rotor mechanism and the second rotor mechanism are relatively independent, are effectively protected motor, improve the use of motor
In the life-span, its fault rate is reduced, while motor is no longer arranged on the top or bottom of the first rotor 62 and the second rotor 72, it is to avoid
Motor produces gas flow-disturbing when working the first rotor 62 and the second rotor 72, improves its delivery efficiency and using effect.
3rd, the first rotor 62 and the second reversion at the same speed of rotor 72 are realized by a motor, reduces the quantity of motor, carry
The high utilization rate of motor, using gear drive come transfer motion power, optimizes transmission mechanism layout, simplifies whole DCB Specimen and contain
Road system, reduces the overall weight of unmanned plane, improves the performance of unmanned plane, is more convenient to realize the posture control to unmanned plane
System.
Claims (6)
1. the DCB Specimen bypass system based on Bevel Gear Transmission, it is characterised in that：Including the first rotor mechanism, the second gyroplane
Structure, duct (1), bevel gear (2), motor input shaft (3), multiple support equipment gears (4), many Auxiliary support axles (5)；
First rotor mechanism is identical and arranged in parallel with the second rotor mechanism structure, and the first rotor mechanism is arranged on second
The top of rotor mechanism, the first rotor mechanism includes first gear (61) and the first rotor in the middle of first gear (61)
(62), the second rotor mechanism includes second gear (71) and the second rotor (72) in the middle of second gear (71), first
Rotor (62) is linked together with the second rotor (72) by connecting shaft (8)；
Motor input shaft (3) one end is connected with bevel gear (2), and a support equipment gear (4) passes through an Auxiliary support axle (5)
Connection is arranged between first gear (61), second gear (71), and Auxiliary support axle (5) is arranged on duct (1), bevel gear
(2), support equipment gear (4) matches to engage respectively with first gear (61), second gear (71) and is connected, and bevel gear (2)
Perpendicular with first gear (61), second gear (71), the first rotor (62) can revolve with the second rotor (72) around connecting shaft (8)
Turn, a support equipment gear (4) can rotate around its corresponding Auxiliary support axle (5)；
Duct (1), which includes being provided with the first circumferential weld, the second circumferential weld, outer wall on inwall, the circular ring structure of outer wall, inwall, to be provided with
Axis hole, motor input shaft (3) is matched through axis hole, bevel gear (2), first gear (61), second gear (71), support assist tooth
Wheel (4) is arranged between the inwall of duct (1), outer wall, and the first rotor (62) is located at first with first gear (61) connection
At circumferential weld, the second rotor (72) is located at the second circumferential weld with second gear (71) connection.
2. the DCB Specimen bypass system as claimed in claim 1 based on Bevel Gear Transmission, it is characterised in that：First gear
(61), second gear (71) is shaped as circle, and support equipment gear (4), the quantity of Auxiliary support axle (5) is 2.
3. the DCB Specimen bypass system as claimed in claim 2 based on Bevel Gear Transmission, it is characterised in that：Bevel gear (2), 2
Individual support equipment gear (4) is the distance between adjacent equal.
4. the DCB Specimen bypass system as claimed in claim 1 based on Bevel Gear Transmission, it is characterised in that：One support auxiliary
3rd bearing is provided between gear (4) and an Auxiliary support axle (5).
5. the DCB Specimen bypass system based on Bevel Gear Transmission as described in Claims 1-4 any one, it is characterised in that：
Clutch shaft bearing is provided between first rotor and connecting shaft (8), the second axle is provided between the second rotor (72) and connecting shaft (8)
Hold.
6. the DCB Specimen bypass system as claimed in claim 5 based on Bevel Gear Transmission, it is characterised in that：Connecting shaft (8) two
End is provided with locking cap (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710423778.7A CN107200122A (en) | 2017-06-07 | 2017-06-07 | DCB Specimen bypass system based on Bevel Gear Transmission |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710423778.7A CN107200122A (en) | 2017-06-07 | 2017-06-07 | DCB Specimen bypass system based on Bevel Gear Transmission |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107200122A true CN107200122A (en) | 2017-09-26 |
Family
ID=59907250
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710423778.7A Pending CN107200122A (en) | 2017-06-07 | 2017-06-07 | DCB Specimen bypass system based on Bevel Gear Transmission |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107200122A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109334970A (en) * | 2018-11-13 | 2019-02-15 | 四川大学 | DCB Specimen bypass system |
| CN111483594A (en) * | 2019-02-03 | 2020-08-04 | 罗琮贵 | Low-energy-consumption high-speed flight method and wing ring aircraft thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5340279A (en) * | 1992-06-22 | 1994-08-23 | United Technologies Corporation | Snubber assembly for a rotor assembly having ducted, coaxial counter-rotating rotors |
| CN101934858A (en) * | 2010-07-08 | 2011-01-05 | 王泽峰 | Miniature electric ducted propeller type intelligent unmanned aerial vehicle |
| CN102910285A (en) * | 2011-08-02 | 2013-02-06 | 深圳市联讯创新工场科技开发有限公司 | Rotor aircraft |
| CN103072690A (en) * | 2013-01-23 | 2013-05-01 | 中国航空工业空气动力研究院 | Single-ducted coaxial rotor/propeller saucer-shaped aircraft |
| CN106184780A (en) * | 2016-07-20 | 2016-12-07 | 南昌华梦达航空科技发展有限公司 | A kind of culvert type coaxial double-oar unmanned vehicle |
-
2017
- 2017-06-07 CN CN201710423778.7A patent/CN107200122A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5340279A (en) * | 1992-06-22 | 1994-08-23 | United Technologies Corporation | Snubber assembly for a rotor assembly having ducted, coaxial counter-rotating rotors |
| CN101934858A (en) * | 2010-07-08 | 2011-01-05 | 王泽峰 | Miniature electric ducted propeller type intelligent unmanned aerial vehicle |
| CN102910285A (en) * | 2011-08-02 | 2013-02-06 | 深圳市联讯创新工场科技开发有限公司 | Rotor aircraft |
| CN103072690A (en) * | 2013-01-23 | 2013-05-01 | 中国航空工业空气动力研究院 | Single-ducted coaxial rotor/propeller saucer-shaped aircraft |
| CN106184780A (en) * | 2016-07-20 | 2016-12-07 | 南昌华梦达航空科技发展有限公司 | A kind of culvert type coaxial double-oar unmanned vehicle |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109334970A (en) * | 2018-11-13 | 2019-02-15 | 四川大学 | DCB Specimen bypass system |
| CN109334970B (en) * | 2018-11-13 | 2021-11-30 | 四川大学 | Dual rotor ducted system |
| CN111483594A (en) * | 2019-02-03 | 2020-08-04 | 罗琮贵 | Low-energy-consumption high-speed flight method and wing ring aircraft thereof |
| CN111483594B (en) * | 2019-02-03 | 2024-05-24 | 罗琮贵 | Low-energy-consumption high-speed flight method and wing ring machine thereof |
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| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170926 |
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| RJ01 | Rejection of invention patent application after publication |