CN107237652A - A kind of unmanned helicopter piston engine structure - Google Patents
A kind of unmanned helicopter piston engine structure Download PDFInfo
- Publication number
- CN107237652A CN107237652A CN201710314667.2A CN201710314667A CN107237652A CN 107237652 A CN107237652 A CN 107237652A CN 201710314667 A CN201710314667 A CN 201710314667A CN 107237652 A CN107237652 A CN 107237652A
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- power
- piston
- unmanned helicopter
- engine
- piston engine
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
- F01C1/00—Rotary-piston machines or engines
- F01C1/08—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing
- F01C1/10—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of internal-axis type with the outer member having more teeth or tooth-equivalents, e.g. rollers, than the inner member
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pistons, Piston Rings, And Cylinders (AREA)
Abstract
The present invention relates to a kind of unmanned helicopter piston engine structure, belong to unmanned air vehicle technique field；The body is provided with air inlet, exhaust outlet；The air inlet, the inner of exhaust outlet cooperate with working chamber；Cylinder is provided with the working chamber；The cylinder cooperates with main shaft；The little gear is socketed with main shaft；The bull gear cooperates with eccentric spindle nose；The little gear, bull gear cooperate；The rotary-piston cooperates with eccentric spindle nose.With larger power, relatively low oil consumption rate, excellent high-level performance and higher reliability；The dynamic property of engine, especially economy, job stability are improved, and meet the requirement of aviation high reliability, increase the endurance of aircraft, engine working method and control mode flexibility are strong.
Description
Technical field
The present invention relates to a kind of unmanned helicopter piston engine structure, belong to unmanned air vehicle technique field.
Background technology
Aviation power is always one of difficult point and key technology of aeronautical technology, with the development of unmanned air vehicle technique, to small
Type unmanned vehicle engine proposes higher requirement, and this development just for small-sized aviation piston type engine technology provides direction
And target.In recent years, countries in the world put into substantial amounts of manpower and materials, small-sized aviation piston engine strengthen and new technology should
Conducted in-depth research in terms of, the development of unmanned air vehicle technique is adapted to and promoted with this.
China's Development of UAV starts from the fifties, is engaged in the mainly Beijing Institute of Aeronautics of unmanned plane research and design, western work it is big and
Three aviation universities and colleges of South Airways.With the expansion and the increasing of country's input of the demand of unmanned plane, many research institutes have been added to nothing
The ranks of man-machine research, in order to meet following unmanned plane to volume is bigger, quality is heavier, higher, flight time for flying it is longer
Direction is developed, and domestic multiple units are that 60~130 horsepowers of two-stroke or four reciprocating pistons start to power bracket is developed
Machine, wherein Northwestern Polytechnical University had begun to develop the two stroke engine that power is 80 horsepowers from 2003, and existing oneself enters sample
Machine experimental stage.
A series of depopulated helicopter features such as have spot hover, VTOL and low-altitude low-speed good, can perform and detect
Vouch position, war damage assess, communication relaying, resource exploration, electric inspection process, traffic monitoring, forest fire protection and the task such as take photo by plane,
Military, civilian field has a wide range of applications, as current study hotspot both domestic and external.The operation control surface of depopulated helicopter is rotation
Wing system, and the power source of rotor system comes from engine, so engine control is the basis of helicopter control, only surely
Fixed reliable control of engine speed, just can guarantee that the stabilized flight of helicopter.
Traditional engine research method is carried out by the running experience of engine testsand, give it is different just
Beginning condition such as air door and rotating speed etc. obtain the power and moment of torsion of engine, so as to set up the model of engine.And it is current middle-size and small-size
Depopulated helicopter generally uses piston aviation engine, and its rotating speed is not simply to be determined by the power output of engine
, but determined by the matching relationship of engine output and the required horsepower of rotor, thus for depopulated helicopter
Engine, combine the characteristic of rotor system to carry out it on the basis of tradition research method.
The content of the invention
It is reasonable in design, make in view of the defects and deficiencies of the prior art, the present invention intends to provide one kind is simple in construction
With convenient unmanned helicopter piston engine structure.
To achieve the above object, the technical solution adopted by the present invention is：It lives comprising air inlet, exhaust outlet, cylinder, rotation
Plug, working chamber, body, main shaft, little gear, bull gear, eccentric spindle nose；The body is provided with air inlet, exhaust outlet；It is described enter
Gas port, the inner of exhaust outlet cooperate with working chamber；Cylinder is provided with the working chamber；The cylinder and main shaft phase interworking
Close；The little gear is socketed with main shaft；The bull gear cooperates with eccentric spindle nose；The little gear, bull gear phase interworking
Close；The rotary-piston cooperates with eccentric spindle nose.
Preferably, the rotary-piston is equilateral triangle, and three sides are provided with sealing between outer convex arc edge, side
Connector.
Preferably, clamping is fixed in one end of the eccentric spindle nose with main shaft.
Preferably, the exhaust outlet is back taper, and it is inner small and outside big, it is adapted to the aerial work of unmanned plane.
Preferably, provided with power output module, rotation inside unmanned helicopter piston engine of the present invention
Wing load blocks and power modular converter；The power output module is mutually corresponding with rotary-piston；The rotor load module
It is mutually corresponding with bull gear；The power modular converter is mutually corresponding with cylinder；Work(is included in wherein described power output module
Rate correcting module；The power correction module cooperates with atmospheric pressure monitoring modular and atmospheric temperature monitoring modular.
Preferably, the power output module is an inertial element, it is corresponding with tachometer value not according to different air door amounts
Same engine power, interpolation obtains the power of engine in real time, and is modified by power correction module, obtains engine
Moment of torsion；Rotor system is analyzed by rotor load module, so as to obtain the reaction torque of rotor；According to power modular converter
Dynamics obtain engine output speed.
Preferably, the rotor load module and power modular converter cooperate；The rotor load module and dynamic
Power modular converter is connected with power output module, and power output module mutually restricts control power output module.
The present invention uses rotary engine form, and inside can produce larger impulsive force, relatively general hair
Motivation internal pressurization effect is good, the cooperation of especially eccentric spindle nose and bull gear, main shaft and the activity simultaneously of eccentric spindle nose, and internal
Power output module matches with rotary-piston, and rotor load module and power modular converter cooperate, and mutually restrict defeated
Go out the running of power model, it is possible to decrease oil consumption, improve stability, internal electric-control system is that those skilled in the art should grasp
Technology, repeat no more here.
After said structure, the present invention has the beneficial effect that：A kind of unmanned helicopter of the present invention is sent out with piston
Motivation structure, with larger power, relatively low oil consumption rate, excellent high-level performance and higher reliability；Engine it is dynamic
Power, especially economy, job stability are improved, and meet the requirement of aviation high reliability, increase the continuation of the journey energy of aircraft
Power, engine working method and control mode flexibility are strong.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is the accompanying drawing used required in technology description to be briefly described, it should be apparent that, drawings in the following description are only this
Some embodiments of invention, for those of ordinary skill in the art, without having to pay creative labor, may be used also
To obtain other accompanying drawings according to these accompanying drawings.
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the schematic diagram of rotary-piston in the present invention；
Fig. 3 is Fig. 2 side view；
Fig. 4 is the internal module figure of the present invention；
Description of reference numerals：
Air inlet 1, exhaust outlet 2, cylinder 3, rotary-piston 4, working chamber 5, body 6, main shaft 7, little gear 8, bull gear 9,
It is eccentric spindle nose 10, power output module 001, rotor load module 002, power modular converter 003, power correction module 004, big
The strong monitoring modular 005 of air pressure, atmospheric temperature monitoring modular 006.
Embodiment
The present invention is further illustrated below in conjunction with the accompanying drawings.
Referring to such as Fig. 1 -- shown in Fig. 4, present embodiment comprising air inlet 1, exhaust outlet 2, cylinder 3, rotary-piston 4,
Working chamber 5, body 6, main shaft 7, little gear 8, bull gear 9, eccentric spindle nose 10；The body 6 is provided with air inlet 1, exhaust outlet
2；The air inlet 1, the inner of exhaust outlet 2 cooperate with working chamber 5；Cylinder 3 is provided with the working chamber 5；The cylinder 3
Cooperated with main shaft 7；The little gear 8 is socketed with main shaft 7；The bull gear 9 cooperates with eccentric spindle nose 10；It is described small
Gear 8, bull gear 9 cooperate；The rotary-piston 4 cooperates with eccentric spindle nose 10；The rotary-piston 4 is equilateral three
It is angular, and three sides are that sealed connecting component is provided between outer convex arc edge, side；One end of the eccentric spindle nose 10 is consolidated with main shaft 7
Determine clamping；The exhaust outlet 2 is back taper, inner small and outside big, is adapted to the aerial work of unmanned plane.
Power output module 001, rotor load are provided with inside unmanned helicopter piston engine of the present invention
Module 002 and power modular converter 003；The power output module 001 is mutually corresponding with rotary-piston 4；The rotor load
Module 002 is mutually corresponding with bull gear 9；The power modular converter 003 is mutually corresponding with cylinder 3；Wherein described power output
Power correction module 004 is included in module 001；The power correction module 004 and atmospheric pressure monitoring modular 005 and big temperature
Degree monitoring modular 006 cooperates；The power output module 001 is an inertial element, according to different air door amounts and rotating speed
The different engine power of value correspondence, interpolation obtains the power of engine in real time, and is repaiied by power correction module 004
Just, the moment of torsion of engine is obtained；Rotor system is analyzed by rotor load module 002, so as to obtain the reaction torque of rotor；
Engine output speed is obtained according to the dynamics of power modular converter 003；The rotor load module 002 and power turn
Mold changing block 003 cooperates；The rotor load module 002 and power modular converter 003 connect with power output module 001
Connect, and the mutually restriction control power output module 001 of power output module 001.
Present embodiment uses rotary engine form, and inside can produce larger impulsive force, relatively
General engine interior pressurized effect is good, and the cooperation of especially eccentric spindle nose and bull gear, main shaft is simultaneously living with eccentric spindle nose
Move, and internal power output module matches with rotary-piston, rotor load module and power modular converter cooperate, and phase
The mutually running of restriction power output module, it is possible to decrease oil consumption, improves stability, internal electric-control system is those skilled in the art
The technology that should be grasped, is repeated no more here.
A kind of unmanned helicopter piston engine structure described in present embodiment, with larger power,
Relatively low oil consumption rate, excellent high-level performance and higher reliability；The dynamic property of engine, economy, especially work steady
It is qualitative to be improved, the requirement of aviation high reliability is met, increases the endurance of aircraft, engine working method and manipulation side
Formula flexibility is strong.
It is described above, it is merely illustrative of the technical solution of the present invention and unrestricted, those of ordinary skill in the art are to this hair
Other modifications or equivalent substitution that bright technical scheme is made, without departing from the spirit and scope of technical solution of the present invention,
It all should cover among scope of the presently claimed invention.
Claims (8)
1. a kind of unmanned helicopter piston engine structure, it is characterised in that：It includes air inlet, exhaust outlet, cylinder, rotation
Turn a work plug, working chamber, body, main shaft, little gear, bull gear, eccentric spindle nose；The body is provided with air inlet, exhaust outlet；Institute
Air inlet, the inner of exhaust outlet is stated to cooperate with working chamber；Cylinder is provided with the working chamber；The cylinder and main shaft are mutual
Coordinate；The little gear is socketed with main shaft；The bull gear cooperates with eccentric spindle nose；The little gear, bull gear are mutual
Coordinate；The rotary-piston cooperates with eccentric spindle nose.
2. a kind of unmanned helicopter piston engine structure according to claim 1, it is characterised in that：The rotation
Piston is equilateral triangle, and three sides are that sealed connecting component is provided between outer convex arc edge, side.
3. a kind of unmanned helicopter piston engine structure according to claim 1, it is characterised in that：The bias
Clamping is fixed in one end of spindle nose with main shaft.
4. a kind of unmanned helicopter piston engine structure according to claim 1, it is characterised in that：The exhaust
Mouth is back taper, inner small and outside big, is adapted to the aerial work of unmanned plane.
5. a kind of unmanned helicopter piston engine structure according to claim 1, it is characterised in that：Institute of the present invention
Power output module, rotor load module and power modular converter are provided with inside the unmanned helicopter piston engine stated；
The power output module is mutually corresponding with rotary-piston；The rotor load module is mutually corresponding with bull gear；The power
Modular converter is mutually corresponding with cylinder；Power correction module is included in wherein described power output module；The power correction mould
Block cooperates with atmospheric pressure monitoring modular and atmospheric temperature monitoring modular.
6. a kind of unmanned helicopter piston engine structure according to claim 1, it is characterised in that：The output
Power model is inertial element, according to different air door amounts different engine power corresponding with tachometer value, in real time interpolation
The power of engine is obtained, and is modified by power correction module, the moment of torsion of engine is obtained；By rotor load module to rotation
Wing system is analyzed, so as to obtain the reaction torque of rotor；Engine is obtained according to the dynamics of power modular converter defeated
Go out rotating speed.
7. a kind of unmanned helicopter piston engine structure according to claim 1, it is characterised in that：The rotor
Load blocks and power modular converter cooperate；The rotor load module and power modular converter with power output module
Connection, and power output module mutually restricts control power output module.
8. a kind of unmanned helicopter piston engine structure according to claim 1, it is characterised in that：It is using rotation
Rotating piston engine form, inside can produce larger impulsive force, and relatively general engine interior pressurized effect is good, especially
It is the cooperation of eccentric spindle nose and bull gear, and main shaft is lived with the activity simultaneously of eccentric spindle nose, and internal power output module with rotation
Plug matches, and rotor load module and power modular converter cooperate, and the mutually running of restriction power output module, can drop
Low oil consumption, improves stability.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710314667.2A CN107237652A (en) | 2017-05-06 | 2017-05-06 | A kind of unmanned helicopter piston engine structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710314667.2A CN107237652A (en) | 2017-05-06 | 2017-05-06 | A kind of unmanned helicopter piston engine structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107237652A true CN107237652A (en) | 2017-10-10 |
Family
ID=59984521
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710314667.2A Pending CN107237652A (en) | 2017-05-06 | 2017-05-06 | A kind of unmanned helicopter piston engine structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN107237652A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB951813A (en) * | 1960-06-29 | 1964-03-11 | Nsu Motorenwerke Ag | Improvements in or relating to gearings for rotary internal combustion engines |
| CN201486647U (en) * | 2009-08-20 | 2010-05-26 | 宁波贝斯特航空技术工程有限公司 | Electric control spraying type triangle rotor engine |
| CN104405447A (en) * | 2013-09-22 | 2015-03-11 | 摩尔动力(北京)技术股份有限公司 | Multi-angle rotor fluid mechanism and engine using the same |
| CN205064087U (en) * | 2015-10-11 | 2016-03-02 | 上海工程技术大学 | Roller piston for rotary engine |
-
2017
- 2017-05-06 CN CN201710314667.2A patent/CN107237652A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB951813A (en) * | 1960-06-29 | 1964-03-11 | Nsu Motorenwerke Ag | Improvements in or relating to gearings for rotary internal combustion engines |
| CN201486647U (en) * | 2009-08-20 | 2010-05-26 | 宁波贝斯特航空技术工程有限公司 | Electric control spraying type triangle rotor engine |
| CN104405447A (en) * | 2013-09-22 | 2015-03-11 | 摩尔动力(北京)技术股份有限公司 | Multi-angle rotor fluid mechanism and engine using the same |
| CN205064087U (en) * | 2015-10-11 | 2016-03-02 | 上海工程技术大学 | Roller piston for rotary engine |
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Application publication date: 20171010 |