CN109098842A - A kind of unmanned plane petrol engine of different axis output - Google Patents
A kind of unmanned plane petrol engine of different axis output Download PDFInfo
- Publication number
- CN109098842A CN109098842A CN201710474519.7A CN201710474519A CN109098842A CN 109098842 A CN109098842 A CN 109098842A CN 201710474519 A CN201710474519 A CN 201710474519A CN 109098842 A CN109098842 A CN 109098842A
- Authority
- CN
- China
- Prior art keywords
- engine
- exhaust
- retarder
- generator
- rotor
- 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
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B61/00—Adaptations of engines for driving vehicles or for driving propellers; Combinations of engines with gearing
- F02B61/04—Adaptations of engines for driving vehicles or for driving propellers; Combinations of engines with gearing for driving propellers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B63/00—Adaptations of engines for driving pumps, hand-held tools or electric generators; Portable combinations of engines with engine-driven devices
- F02B63/04—Adaptations of engines for driving pumps, hand-held tools or electric generators; Portable combinations of engines with engine-driven devices for electric generators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B67/00—Engines characterised by the arrangement of auxiliary apparatus not being otherwise provided for, e.g. the apparatus having different functions; Driving auxiliary apparatus from engines, not otherwise provided for
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02N—STARTING OF COMBUSTION ENGINES; STARTING AIDS FOR SUCH ENGINES, NOT OTHERWISE PROVIDED FOR
- F02N15/00—Other power-operated starting apparatus; Component parts, details, or accessories, not provided for in, or of interest apart from groups F02N5/00 - F02N13/00
- F02N15/02—Gearing between starting-engines and started engines; Engagement or disengagement thereof
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention discloses a kind of unmanned plane petrol engines of different axis output, including generator, foundation machine, retarder, engine foundation, air inlet system and exhaust system, oil supply system, starting system, electric-control system and rotor system composition.The engine is twin-tub two-cycle engine, carries gear reduction unit, increases the output torque of rotor shaft, improve flying quality；The engine is integrated with generator module simultaneously, and power input can be provided for the electrical equipment of complete machine；In addition, the engine uses ipsilateral exhaust, facilitates arrangement of the engine in multi-rotor unmanned aerial vehicle, solve the problems, such as exhaust gas " sooting " fuselage occurred when reversed exhaust.Structure arrangement aspect, the engine integrates retarder pedestal with crankcase body, while the starting system of engine uses retarding starter, and the two-stage gear drive of traditional startup system is reduced to level-one, therefore engine structure is compact, and weight advantage is obvious.
Description
Technical field
The invention discloses a kind of unmanned plane petrol engine of different axis power output, can as rotor wing unmanned aerial vehicle,
The power resources of the equipment such as propeller-parachuting, model plane, belong to field of power machinery.
Background technique
Current medium and heavy rotor wing unmanned aerial vehicle (100kg or more) is most to use gasoline engine as power, and gasoline engine exports
Torque is lower, needs to install retarder to improve engine output torque, and common unmanned plane retarder is mostly coaxial speed reducer,
For example series of rows star-wheel arrangement or turbine are arranged, and are independent components, structure is complicated, is unfavorable for unmanned plane loss of weight.
Need to provide starting power with starter and deceleration train when gasoline starting, common small-sized starter without
Retarder, output revolving speed is higher, to reach engine start request, needs to install two under engine foundation to three-level ratio wheel
System, leading to starting system, structure is complicated, and weight is larger and inconvenient demolition and maintenance.
Twin-tub gas engine also has application on unmanned plane at present, and majority is using reversed exhaust, in multi-rotor unmanned aerial vehicle
On, this exhaust mode often will lead to the exhaust pipe of side against unmanned plane central side, fuselage occurs by tail pipe exhaust
The problem of " sooting ".
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 install small generator on unmanned plane power-equipment with full
Sufficient electrical equipment demand.
Therefore, in view of the above-mentioned problems, the complete machine arrangement of optimization unmanned plane, simplifies retarder and starting system structure and improve
Serviceability is of great significance.
Summary of the invention
In view of the above-mentioned problems, the invention proposes a kind of compact-sized, small in size, light-weight engine overall design sides
Case.Be the twin-tub unmanned plane petrol engine with retarder described in the invention, by generator system (generator 1 and generator every
Block 2), foundation machine 8, retarder 10, engine foundation 14, air inlet system and exhaust system (air inlet is every cover 5 and exhaust pipe 3), oil supply system (spray
Oily device 6 and carburetor 7), starting system (starter 12 and start train 13), electric-control system (speed probe 4 and electronic control module
9) it is formed with rotor system 11.
The exhaust mode of two cylinders of engine is exhaust in the same direction, and engine in more rotor complete machines when arranging, exhaust
Direction can effectively avoid the fuselage of unmanned plane center by exhaust gas " sooting " both facing to outside.
The retarder of the engine does not need pedestal, and crankcase upper box is integrated with the function of retarder pedestal, retarder
It is directly installed on crankcase upper box.The retarder is single gear transmission, and input shaft is the upper crank throw in crank assemblby, defeated
Shaft is rotor shaft, while the input shaft stretches out reducer shell top, provides installation site for generator system.
The starter of the engine starting system be retarding starter, inside be integrated with primary speed-down mechanism, export
The more common starter of revolving speed is low, therefore gear drive of the starting system from starter gear to crankshaft only needs level-one i.e. reachable
To the starting speed requirement of engine.
The generator and generator spacer block of the generator of engine system are mounted on the upper crank throw of crank assemblby, wherein sending out
Motor provides power resources for each electrical appliance of unmanned plane complete machine, and magnet is equipped on generator spacer block, subtracts for being mounted on
Speed probe on fast device shell reads engine rotational speed signal.
To save complete machine space, the starter and exhaust pipe of the engine are located at the two sides of cylinder centerline.
Detailed description of the invention
Fig. 1 is engine structure schematic diagram 1.1 generator, 2 generator spacer blocks, 3 exhaust pipes, 4 speed probes, 5 in figure
Air inlet is every cover, 6 atomizers, 7 carburetors, 8 engine foundation machines, 9 electronic control modules, 10 retarders and 11 rotor assemblies.
Fig. 2 is engine structure schematic diagram 2.12 retarding starters, 13 starter transmission gears, 14 engine bottoms in figure
Seat.
Fig. 3 is the schematic diagram of engine foundation machine 8.15 cylinders in figure, 16 crankshaft rod assemblies, nowel on 17 crankcases
Body.
Fig. 4 is the structural schematic diagram of retarder 10.
Specific embodiment
The present invention will be described with reference to the accompanying drawings and examples.
The present invention is there are two types of working condition, and when engine start, power is inputted by starter 12, passes through 13 band of transmission gear
Dynamic crankshaft 16 rotates, and completes engine start.After engine start, starter 12 stops operating, and engine power derives from vapour
Oil firing is inputted by crankshaft 16, and power output stretches out reduction box casing by crankshaft by two lines road, a power output route
Part directly transmit, provide power input for the generator 1 of unmanned plane or other components；Another power output route be
By Gear Transmission in Reducer, bent axle power is transferred to rotor output shaft, drives rotor 11 to rotate, is provided for unmanned plane dynamic
Power.
Claims (6)
1. a kind of unmanned plane petrol engine of different axis output is two stroke electric-controlled petrol engine of twin-tub, by generator, basis
Machine, retarder, engine foundation, air inlet system and exhaust system, oil supply system, starting system, electric-control system and rotor system composition.
2. the exhaust mode of air inlet system and exhaust system according to claim 1 is ipsilateral exhaust, exhaust pipe 3 and starter 12 are distinguished
Positioned at the two sides of cylinder centerline.
3. the input shaft of speed reducer assembly 12 according to claim 1 is the upper crank throw of crankshaft rod assembly 16, song on this
Stretching reducer shell is turned, provides installation site for generator 1 and generator spacer block 2, the output shaft of the retarder is rotor shaft,
Installation site is provided for rotor.
4. being equipped with speed probe 4 on reducer shell according to claim 1, rotated together by reading with crankshaft
Generator spacer block 2 on magnet signal measure speed of crankshaft.
5. the starter 12 of starting system according to claim 1 is retarding starter, it is internally integrated primary speed-down knot
Structure, starter gear assembly are one-stage gear transmission.
6. the upper box of crankcase body 17 according to claim 1 is integrated with the function of retarder pedestal, retarder is total
It is directly installed on crankcase upper box at 12.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710474519.7A CN109098842A (en) | 2017-06-21 | 2017-06-21 | A kind of unmanned plane petrol engine of different axis output |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710474519.7A CN109098842A (en) | 2017-06-21 | 2017-06-21 | A kind of unmanned plane petrol engine of different axis output |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109098842A true CN109098842A (en) | 2018-12-28 |
Family
ID=64796061
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710474519.7A Pending CN109098842A (en) | 2017-06-21 | 2017-06-21 | A kind of unmanned plane petrol engine of different axis output |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109098842A (en) |
-
2017
- 2017-06-21 CN CN201710474519.7A patent/CN109098842A/en active Pending
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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: 20181228 |