CN109139804A - A kind of unmanned plane single stage gear reducer - Google Patents
A kind of unmanned plane single stage gear reducer Download PDFInfo
- Publication number
- CN109139804A CN109139804A CN201710455170.2A CN201710455170A CN109139804A CN 109139804 A CN109139804 A CN 109139804A CN 201710455170 A CN201710455170 A CN 201710455170A CN 109139804 A CN109139804 A CN 109139804A
- Authority
- CN
- China
- Prior art keywords
- unmanned plane
- crank throw
- retarder
- reducer
- 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 16
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims abstract description 9
- 238000009434 installation Methods 0.000 claims description 4
- 230000009467 reduction Effects 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 210000000515 tooth Anatomy 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 208000020442 loss of weight Diseases 0.000 description 1
Classifications
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- 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
- F16H1/00—Toothed gearings for conveying rotary motion
- F16H1/02—Toothed gearings for conveying rotary motion without gears having orbital motion
- F16H1/04—Toothed gearings for conveying rotary motion without gears having orbital motion involving only two intermeshing members
- F16H1/06—Toothed gearings for conveying rotary motion without gears having orbital motion involving only two intermeshing members with parallel axes
-
- 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
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D1/00—Couplings for rigidly connecting two coaxial shafts or other movable machine elements
- F16D1/06—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end
-
- 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
-
- 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
- F16H2057/0203—Gearboxes; Mounting gearing therein the gearbox is associated or combined with a crank case of an engine
-
- 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
- F16H2057/02086—Measures for reducing size of gearbox, e.g. for creating a more compact transmission casing
-
- 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
- F16H2057/02095—Measures for reducing number of parts or components
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention discloses a kind of retarders of unmanned plane, it is desirable to provide a kind of single gear reductions case integrated with diesel engine crankshaft, including crank throw input shaft, rotor output shaft, retarder pedestal, speed reducing gear pair, flat key and reducer shell.The retarder pedestal is integrated with crankcase upper box, and directly from 4 input power of crank throw, by one group of reduction gearing to 2 output power of rotor shaft, while 4 extension of crank throw can be used as the input shaft of unmanned plane generator.This reducer structure is compact, light-weight, high reliablity, while generator for unmanned plane or other equipment provide power input.
Description
Technical field
The present invention realizes a kind of unmanned plane single stage gear reducer.It can be used as rotor wing unmanned aerial vehicle, propeller-parachuting, model plane
Etc. equipment actuating unit, belong to field of power machinery.
Background technique
Current heavy rotor wing unmanned aerial vehicle majority, as power, needs to be reduced revolving speed raising with retarder using internal combustion engine
Torque, common unmanned plane retarder is mostly coaxial speed reducer, is arranged for series of rows star-wheel arrangement or turbine, and is independent zero
Part, structure is complicated, is unfavorable for unmanned plane loss of weight.
Simultaneously as unmanned air vehicle technique develops and the diversification of function, the electrical equipment on unmanned plane is more and more, tradition
The weight and capacity of battery cannot gradually be met the requirements, and need to provide on unmanned plane power-equipment for small generator dynamic
Power input.
Summary of the invention
A kind of unmanned plane single stage gear reducer system is by retarder pedestal 1, rotor output shaft 2, ball bearing 3, crank throw
Input shaft 4, reducer shell 5, driving gear 6, driven gear 7, installation bolt 8 and flat key 9 form.Its retarder pedestal and song
Axle box upper box integrates, and lower part and crankcase lower box cooperate, and reducer shell 5 is fixed on retarder by bolt 8
On pedestal 1 (crankcase upper box).
A kind of unmanned plane single stage gear reducer system, power are inputted by engine crank throw 4, by driving gear 6 and from
Moving gear 7 is driven, and by rotor shaft 2 is that rotor provides power, at the same crank throw 4 stretch out the part of reducer shell 5 for generator or
Other equipment provide power input, are attached between crank throw input shaft 4 and rotor output shaft 2 and gear by flat key 9.
This retarder is small in size, light-weight, high reliablity, while generator for unmanned plane or other equipment are reserved connects
Mouthful.
Detailed description of the invention
Fig. 1 is retarder front view schematic diagram, and Fig. 2 is retarder top view half-section diagram.
1 retarder pedestal, 2 rotor output shafts, 3 ball bearings, 4 crank throw input shafts, 5 reducer shells, 6 driving tooths in figure
Wheel, 7 driven gears, 8 installation bolt groups and 9 flat keys.
Specific embodiment
The present invention will be described with reference to the accompanying drawings and examples.
The retarder pedestal of retarder system of the present invention is integrated on crankcase upper box, and power is inputted from crank shaft 4, is moved
Power output has two lines road, and one is transferred to the driven gear 7 in rotor shaft by the driving gear 6 on crank shaft 4, by driven tooth
Wheel 7 drives rotor shaft 2 to rotate, and by the keyway on rotor shaft top, provides power output for unmanned plane rotor；Another power is defeated
Route is directly transmitted by the part that crank shaft 4 stretches out reduction box casing 5 out, is mentioned for the generator or other components of unmanned plane
It is inputted for power.
Claims (4)
1. a kind of unmanned plane gear reducer system is by retarder pedestal 1, rotor output shaft 2, ball bearing 3, crank throw input shaft
4, reducer shell 5, driving gear 6, driven gear 7, installation bolt 8 and flat key 9 form.
2. retarder system according to claim 1 is single stage gear reducer, the different axis that slows down is realized for unmanned mechanomotive force
Output.
3. retarder pedestal 1 according to claim 1, it is integrated with the function of crankcase upper box, under lower part and crankcase
Cabinet cooperation.
4. reducer shell is stretched out on 4 top of crank throw input shaft according to claim 1, be unmanned plane generator or other
Equipment provides power input and installation site.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710455170.2A CN109139804A (en) | 2017-06-16 | 2017-06-16 | A kind of unmanned plane single stage gear reducer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710455170.2A CN109139804A (en) | 2017-06-16 | 2017-06-16 | A kind of unmanned plane single stage gear reducer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109139804A true CN109139804A (en) | 2019-01-04 |
Family
ID=64830453
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710455170.2A Pending CN109139804A (en) | 2017-06-16 | 2017-06-16 | A kind of unmanned plane single stage gear reducer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109139804A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2527782Y (en) * | 2002-02-02 | 2002-12-25 | 重庆力帆实业（集团）有限公司 | Built-in gear speed reducer |
| CN205278276U (en) * | 2015-12-11 | 2016-06-01 | 陕西法士特齿轮有限责任公司 | Single reduction gear for electric automobile |
| CN206171811U (en) * | 2016-10-14 | 2017-05-17 | 大连宏翼航空科技发展有限公司 | Multistage deceleration system of unmanned helicopter of single rotor and unmanned helicopter of single rotor |
-
2017
- 2017-06-16 CN CN201710455170.2A patent/CN109139804A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2527782Y (en) * | 2002-02-02 | 2002-12-25 | 重庆力帆实业（集团）有限公司 | Built-in gear speed reducer |
| CN205278276U (en) * | 2015-12-11 | 2016-06-01 | 陕西法士特齿轮有限责任公司 | Single reduction gear for electric automobile |
| CN206171811U (en) * | 2016-10-14 | 2017-05-17 | 大连宏翼航空科技发展有限公司 | Multistage deceleration system of unmanned helicopter of single rotor and unmanned helicopter of single rotor |
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Legal Events
| 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 | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190104 |