CN106838268A - A kind of reducer arrangement - Google Patents
A kind of reducer arrangement Download PDFInfo
- Publication number
- CN106838268A CN106838268A CN201710148446.2A CN201710148446A CN106838268A CN 106838268 A CN106838268 A CN 106838268A CN 201710148446 A CN201710148446 A CN 201710148446A CN 106838268 A CN106838268 A CN 106838268A
- Authority
- CN
- China
- Prior art keywords
- reducer arrangement
- casing
- arrangement according
- ribs
- output shaft
- 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
- 239000003638 chemical reducing agent Substances 0.000 title claims abstract description 37
- 230000002787 reinforcement Effects 0.000 claims description 13
- 238000000034 method Methods 0.000 claims description 3
- 238000012545 processing Methods 0.000 claims description 2
- 210000003205 muscle Anatomy 0.000 claims 1
- 238000005728 strengthening Methods 0.000 abstract description 3
- 239000003921 oil Substances 0.000 description 7
- 238000010586 diagram Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 208000020442 loss of weight Diseases 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
- 208000016261 weight loss Diseases 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Classifications
-
- 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
- F16H57/03—Gearboxes; Mounting gearing therein characterised by means for reinforcing gearboxes, e.g. ribs
-
- 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
- F16H57/04—Features relating to lubrication or cooling or heating
- F16H57/0412—Cooling or heating; Control of temperature
- F16H57/0415—Air cooling or ventilation; Heat exchangers; Thermal insulations
- F16H57/0416—Air cooling or ventilation
-
- 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
- F16H2057/02039—Gearboxes for particular applications
-
- 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
- F16H2057/02091—Measures for reducing weight of gearbox
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Details Of Gearings (AREA)
- Gear Transmission (AREA)
Abstract
The invention provides a kind of reducer arrangement, the potentiality of the dynamic engine of oil and large scale rotor in terms of endurance and load-carrying ability is increased can be given full play to, coordinate the rotating speed and moment of torsion of large scale rotor and the dynamic engine of oil, improve delivery efficiency.By increasing appropriate strengthening rib strip and ribs on casing, reducer arrangement weight can be effectively reduced, increased heat-sinking capability, improved reliability in the case where casing rigidity requirement is met, meet decelerator long-time, the job requirement of high capacity.
Description
Technical field
The present invention relates to vehicle technology field, the more particularly to deceleration device of the dynamic multi-rotor aerocraft of oil.
Background technology
Rotor class aircraft, due to good mobility and maneuverability, suffering from widely should in every field
With.Current rotor class aircraft controls attitude by the change of rotor lift, it is possessed good stability.Current many rotations
The motion of the wing depends on the change of revolution speed of propeller, dynamic many in larger sized many rotors or oil to adjust lift and torque
Larger limitation is subject in rotor craft.
The content of the invention
In order to overcome the above-mentioned deficiencies of the prior art, the unfavorable shadow that large scale rotor and the dynamic engine of oil bring is reduced
Ring, it is necessary to increase deceleration device between power set and rotor, meet the rotating speed and torque demand of rotor.The present invention is proposed
A kind of reducer arrangement, to give full play to the dynamic engine of oil and large scale rotor in terms of endurance and load-carrying ability is increased
Potentiality, there is provided necessary technology ensures.
To realize technical purpose of the invention, the present invention provides following technical scheme：
A kind of reducer arrangement for multi-rotor aerocraft rotor power system, including input shaft, input shaft gear, case
Body, output shaft and output shaft gear, the input shaft gear and output shaft gear are respectively positioned within casing and are intermeshed, the former
Diameter is less than the latter's diameter, it is characterised in that each self-contained n bars reinforcement of inner surface and/or institute above and/or under the casing
The outer surface for stating casing includes m bar ribs.
Reducer arrangement according to above-mentioned any one technical scheme, it is characterised in that n is the natural number of 6-10,
And the n bars reinforcement is in center radial arrangement around the axle center of the output shaft.
Reducer arrangement according to above-mentioned any one technical scheme, it is characterised in that the ribs is equidistant
It is arranged on the outer surface.
Reducer arrangement according to above-mentioned any one technical scheme, it is characterised in that m is even number and the reinforcement
One group of spaced set of rib two is on the outer surface.
Reducer arrangement according to above-mentioned any one technical scheme, it is characterised in that the bottom of the casing is thick
Degree is for about 3mm, and the thickness of side wall is for about 2mm.
Reducer arrangement according to above-mentioned any one technical scheme, it is characterised in that the thickness of the reinforcement
For about 8mm.
Reducer arrangement according to above-mentioned any one technical scheme, it is characterised in that the thickness of the ribs
For about 2mm.
Reducer arrangement according to above-mentioned any one technical scheme, it is characterised in that the ribs is in wing
Shape, width is gradually increased to opposite side from side.
Reducer arrangement according to above-mentioned any one technical scheme, it is characterised in that the reinforcement and reinforcement
Rib uses integral forming technique processing and fabricating with the casing.
In one more specifically technical scheme, the present invention provides a kind of decelerator dress of the dynamic multi-rotor aerocraft of oil
Put, including, input shaft, input shaft gear, casing, Box Cover, output shaft gear and output shaft.Power set input rotating speed and
Moment of torsion, by the input shaft being connected with power set, on the input shaft gear in incoming casing, by between output shaft gear
Deceleration transmission, be changed into meeting the rotating speed and moment of torsion of rotor work, exported to rotor system by output shaft.
Increase appropriate strengthening rib strip in box house and Box Cover bottom, the wall thickness of casing and Box Cover can be reduced,
Making the weight of decelerator is significantly reduced.Appropriate ribs is increased by outside the enclosure portion, can effectively be increased
Casing rigidity and heat-sinking capability, improve the reliability of decelerator, meet decelerator long-time, the job requirement of high capacity.
Beneficial effects of the present invention include following any one：
1st, the weight of decelerator is effectively reduced；
2nd, ensure that the rigidity of casing；
3rd, increased heat-sinking capability；
4th, improve the reliability of decelerator；
5th, decelerator long-time, the job requirement of high capacity are met.
Brief description of the drawings
The present invention is described in further detail with reference to the accompanying drawings and detailed description.
Fig. 1 represents the schematic diagram of embodiment of the present invention reducer arrangement
Fig. 2 represents the detailed maps of embodiment of the present invention reducer arrangement
Fig. 3 represents embodiment of the present invention reducer arrangement schematic internal view
Fig. 4 represents embodiment of the present invention reducer arrangement outside schematic diagram
Fig. 5 represents the half-section diagram of embodiment of the present invention reducer arrangement
Fig. 6 represents the half-section diagram of conventional reducer arrangement
In figure：1st, input shaft, 2, input shaft gear, 3, casing, 4, Box Cover, 5, output shaft, 6, output shaft gear, 7, plus
Strong rib, 8, reinforcement.
Specific embodiment
The present invention will be described below in conjunction with the accompanying drawings, and described preferred embodiment is merely to illustrate and explains this hair
It is bright, it is not intended to limit the present invention.
Embodiment 1：
As shown in Figure 1 and Figure 2, the present embodiment is by input shaft 1, input shaft gear 2, casing 3, Box Cover 4, output shaft gear 5
Constituted with output shaft 6.
Above-mentioned input shaft 1 is used for connecting power device, and input shaft gear 2 is located in casing 3 with output shaft gear 5, will
The rotating speed and moment of torsion of input are changed into meeting the rotating speed and moment of torsion of rotor job requirement by deceleration transmission, are exported by output shaft 6
To rotor driver.Need Box Cover 6 to be installed on the upper opening of casing 5 in casing, be connected by screw with casing 5, for will be defeated
Enter shaft gear 2 to be sealed in casing 5 with output shaft gear 5.
As shown in Figure 3, Figure 4, increase appropriate strengthening rib strip 9 by the inside of casing 3 and the bottom of Box Cover 4, can drop
The wall thickness of low casing 3 and Box Cover 4, making the weight of whole reducer arrangement is significantly reduced.By outside casing 3
Increase appropriate ribs 7, can simultaneously increase the rigidity and heat-sinking capability of casing 3.
Embodiment 2：
As shown in figure 5, the bottom wall thickness of reducer arrangement is 3mm, sidewall thickness is 2mm, and the thickness of 8 reinforcements 8 is equal
It is 8mm, reinforcement region area accounts for the 70% of whole base area, and 18 thickness of ribs 7 are 2mm, strengthen wall rib area and account for
The 6% of whole lateralarea.
Embodiment 3：
Inventor is designed into Late Stage Verification experiment and has carried out substantial amounts of creative work from the initial scheme of decelerator.Preceding
In the trial-manufacturing process of phase, as shown in fig. 6, the reducer arrangement designed to traditional design method is by after preliminary loss of weight, obtaining
Bottom wall thickness is 6mm, and sidewall thickness is the scheme of 3mm.Find that the reducer arrangement weight is larger in use, and continue
Temperature is high during work, is unfavorable for playing the dynamic advantage that aircraft cruising time is long, load-carrying ability is big of oil.
By related experiment work, reducer arrangement of the present invention shown in following table is obtained with traditional reducer arrangement in weight
And under continuous firing state lubricating oil temperature contrast.
As can be seen from the above table, using reducer arrangement of the present invention, by reducing overall wall thickness, and in appropriate position
After putting increase ribs and reinforcement, it is possible to achieve weight reduction 27.6%, fan heat energy power improves 16.7%, be conducive to oil dynamic winged
Row device cruising time and the lifting of load-carrying ability, with more preferable performance.
Claims (10)
1. a kind of reducer arrangement for multi-rotor aerocraft rotor power system, including input shaft (1), input shaft gear
(2), casing (3), output shaft (5) and output shaft gear (6), the input shaft gear (2) and output shaft gear (6) are respectively positioned on case
Within body (3) and it is intermeshed, diameter is less than the latter's diameter, it is characterised in that interior above and/or under the casing (3)
The outer surface of each self-contained n bars reinforcement (8) in surface and/or the casing (3) includes m bars ribs (7).
2. reducer arrangement according to claim 1, it is characterised in that n is the natural number of 6-10, and the n bars are strengthened
Muscle (8) is in center radial arrangement around the axle center of the output shaft.
3. reducer arrangement according to claim 1, it is characterised in that m is the natural number of 6-20, and the m bars are strengthened
Rib (7) is parallel to each other.
4. reducer arrangement according to claim 3, it is characterised in that ribs (7) spaced set is in described
On outer surface.
5. reducer arrangement according to claim 3, it is characterised in that m is (7) two group of even number and the ribs
Spaced set is on the outer surface.
6. reducer arrangement according to claim 1, it is characterised in that the bottom thickness of the casing (3) is for about 3mm,
The thickness of side wall is for about 2mm.
7. reducer arrangement according to claim 6, it is characterised in that the thickness of the reinforcement (8) is for about 8mm.
8. reducer arrangement according to claim 6, it is characterised in that the thickness of the ribs (7) is for about 2mm.
9. reducer arrangement according to claim 1, it is characterised in that in wing shape, width is from for the ribs (7)
Side is gradually increased to opposite side.
10. reducer arrangement according to claim 1, it is characterised in that the reinforcement (8) and ribs (7) and institute
Casing is stated using integral forming technique processing and fabricating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710148446.2A CN106838268A (en) | 2017-03-14 | 2017-03-14 | A kind of reducer arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710148446.2A CN106838268A (en) | 2017-03-14 | 2017-03-14 | A kind of reducer arrangement |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106838268A true CN106838268A (en) | 2017-06-13 |
Family
ID=59143525
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710148446.2A Pending CN106838268A (en) | 2017-03-14 | 2017-03-14 | A kind of reducer arrangement |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106838268A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002005270A (en) * | 2000-06-23 | 2002-01-09 | Isuzu Motors Ltd | Transmission case structure |
| CN202629029U (en) * | 2012-05-22 | 2012-12-26 | 湖北航天技术研究院特种车辆技术中心 | Shell of main reducing gear |
| CN202927010U (en) * | 2012-11-19 | 2013-05-08 | 宁波中大力德传动设备有限公司 | Box of right-angle output speed reducer with quasi-hyperbolic gears |
| CN204900753U (en) * | 2015-07-15 | 2015-12-23 | 沈阳闪宁科技有限公司 | Coaxial rotor unmanned aerial vehicle reduction gear |
| CN206555411U (en) * | 2017-03-14 | 2017-10-13 | 北京天宇新超航空科技有限公司 | A kind of reducer arrangement |
-
2017
- 2017-03-14 CN CN201710148446.2A patent/CN106838268A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002005270A (en) * | 2000-06-23 | 2002-01-09 | Isuzu Motors Ltd | Transmission case structure |
| CN202629029U (en) * | 2012-05-22 | 2012-12-26 | 湖北航天技术研究院特种车辆技术中心 | Shell of main reducing gear |
| CN202927010U (en) * | 2012-11-19 | 2013-05-08 | 宁波中大力德传动设备有限公司 | Box of right-angle output speed reducer with quasi-hyperbolic gears |
| CN204900753U (en) * | 2015-07-15 | 2015-12-23 | 沈阳闪宁科技有限公司 | Coaxial rotor unmanned aerial vehicle reduction gear |
| CN206555411U (en) * | 2017-03-14 | 2017-10-13 | 北京天宇新超航空科技有限公司 | A kind of reducer arrangement |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170613 |