CN203854860U - Engine and pilotless helicopter - Google Patents
Engine and pilotless helicopter Download PDFInfo
- Publication number
- CN203854860U CN203854860U CN201420092166.6U CN201420092166U CN203854860U CN 203854860 U CN203854860 U CN 203854860U CN 201420092166 U CN201420092166 U CN 201420092166U CN 203854860 U CN203854860 U CN 203854860U
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- China
- Prior art keywords
- driving engine
- pilotless helicopter
- engine
- power output
- output face
- 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.)
- Expired - Fee Related
Links
- 238000009434 installation Methods 0.000 claims abstract description 8
- 230000006978 adaptation Effects 0.000 claims description 6
- 238000010586 diagram Methods 0.000 description 4
- 238000000354 decomposition reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000037452 priming Effects 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000012188 paraffin wax Substances 0.000 description 1
- 239000000575 pesticide Substances 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
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- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The utility model provides an engine and a pilotless helicopter. The engine is arranged in a helicopter body of the pilotless helicopter; the power output face of the engine is towards the top of the pilotless helicopter; the power output face of the engine is provided with a magnetic motor rotor and a magnetic motor stator; and the magnetic motor stator is fixed at one side of the power output face of the engine, which is closer to the front end of the pilotless helicopter. According to the engine provided by the utility model, by optimizing the installation position of the magnetic motor stator and fixing the magnetic motor stator at one side of the power output face of the engine, which is closer to the front end of the pilotless helicopter, a space between the engine and other structures in the helicopter body of the pilotless helicopter can be more compact, and thus, the internal space of the pilotless helicopter can be better utilized, so that the integral volume of the pilotless helicopter is reduced.
Description
Technical field
The utility model relates to transportation apparatus technical field, the pilotless helicopter that relates in particular to a kind of driving engine and comprise this driving engine.
Background technology
The advantages such as adaptive capacity to environment is strong, volume is small and exquisite owing to having for pilotless helicopter, flexible operation, accuracy is high and cost of manufacture is low, thereby obtained gradually increasing concern.For example, pilotless helicopter has obtained application very widely in a plurality of fields such as pesticide spraying, customs and border patrols, forest fire protection patrol, high-altitude explorations at present.
In pilotless helicopter, mainly by electrical motor or driving engine, for it, provide power; In prior art, the driving engine adopting in pilotless helicopter mostly is engine petrol.Magneto generator is to utilize permanent magnet to produce the small-sized alternating current generator in magnetic field, can be used as the priming supply in gasoline engine ignition system.As shown in fig. 1, be petrolic structural representation of the prior art, wherein gasoline engine power output face is provided with magneto rotor and Magnetor stator; It should be noted that after actual installation completes, engine power output face is towards pilotless helicopter top, and Magnetor stator is positioned at engine power output face away from a side of pilotless helicopter front end.
Due to the requirement of pilotless helicopter lightweight and Miniaturization Design, it is very limited that its inside is used for installing petrolic space.Yet, in prior art, the inner structure of pilotless helicopter is still compact not, for example, the parts on engine petrol cause position to conflict with pilotless helicopter internal body existing structure, need to vacate more space engine petrol is installed.
Utility model content
The purpose of this utility model is, for the subproblem in background technology or whole issue, to provide a kind of driving engine, thereby can better utilize pilotless helicopter inner space, and then reduces the overall volume of pilotless helicopter; Further, the utility model also provides a kind of pilotless helicopter that comprises this driving engine.
Concrete, described driving engine, is placed in pilotless helicopter body; Described engine power output face is towards described pilotless helicopter top; Described engine power output face is provided with magneto rotor and Magnetor stator; Described Magnetor stator is fixed on a side of the more close described pilotless helicopter front end of described engine power output face.
Described pilotless helicopter, comprises above-mentioned driving engine.
From above technical scheme, in driving engine provided by the utility model, pass through to optimize the installation site of Magnetor stator, Magnetor stator is fixed on to a side of the more close described pilotless helicopter front end of engine power output face, thereby can make in driving engine and pilotless helicopter body compacter between other structures, thereby can better utilize pilotless helicopter inner space, and then reduce the overall volume of pilotless helicopter.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model embodiment or technical scheme of the prior art, to the accompanying drawing of required use in embodiment or description of the Prior Art be briefly described below, apparently, accompanying drawing in the following describes is embodiment more of the present utility model, for those of ordinary skills, do not paying under the prerequisite of creative work, can also obtain according to these accompanying drawings other accompanying drawing.
Fig. 1 is a kind of petrolic structural representation in prior art;
Fig. 2 is the structural representation of pilotless helicopter in a kind of embodiment of the utility model;
Fig. 3 is the integral structure schematic diagram of driving engine in a kind of embodiment of the utility model;
Fig. 4 is the decomposition texture schematic diagram of driving engine in a kind of embodiment of the utility model;
Fig. 5 is the structural representation of mounting bracket in a kind of embodiment of the utility model;
Fig. 6 is the structural representation of magneto rotor in a kind of embodiment of the utility model.
In figure: 1: driving engine fuselage; 2: magneto rotor; 21: centre hole; 22: keyway; 3: Magnetor stator; 31: assembly opening; 4: mounting bracket; 41: plate body; 42: joint pin; 43: tapped bore; 44: hollow-out parts; 45: screw is installed; 46: mounting hole; 5: screw propeller; 6: alighting gear; 7: empennage.
The specific embodiment
For making object, technical scheme and the advantage of the utility model embodiment clearer, below in conjunction with the accompanying drawing in the utility model embodiment, technical scheme in the utility model embodiment is clearly described, obviously, described embodiment is the utility model part embodiment, rather than whole embodiment.Embodiment based in the utility model, those of ordinary skills are not making the every other embodiment obtaining under creative work prerequisite, all belong to the scope of the utility model protection.
A kind of driving engine is provided in the present embodiment, and according to the difference of used fuel, this driving engine can be engine petrol, can be also the driving engine of the other types such as paraffin engine, at this, does not do particular determination.As shown in Figure 2, this driving engine is placed in pilotless helicopter body; The front portion of driving engine integral body in pilotless helicopter.Described engine power output face is towards described pilotless helicopter top, and other parts that are pilotless helicopter by gear cluster and other transmission devices provide propulsive effort.Described engine power output face is provided with magneto rotor 2 and Magnetor stator 3, and the magneto rotor 2 that utilization cooperatively interacts and Magnetor stator 3 are as the priming supply in engine igniting system.The installation site of described magneto rotor 2 is identical with installation site of the prior art, one of main improvement of the present utility model is, described Magnetor stator 3 is arranged on to a side of the more close described pilotless helicopter front end of described engine power output face.
For driving engine of the prior art (as shown in Figure 1 driving engine), while being arranged in pilotless helicopter, can obviously find out, for fear of Magnetor stator 3, conflict with the structure location of a-quadrant in pilotless helicopter, need to strengthen the distance between driving engine integral structure and a-quadrant structure, be that pilotless helicopter inner structure is compact not, need to vacate more space driving engine is installed.And when the driving engine providing in the present embodiment is arranged in pilotless helicopter, Magnetor stator 3 is fixed on a side of the more close described pilotless helicopter front end of described engine power output face, and this position does not have other to produce the structure of conflicting in position with Magnetor stator 3; In addition, a part for driving engine is positioned at structure below, pilotless helicopter a-quadrant, one side can make between driving engine and the structure of the interior a-quadrant of pilotless helicopter body compacter like this, can make pilotless helicopter inner space obtain on the other hand multiplexing, thereby can better utilize the space of pilotless helicopter inside, and then reduce the overall volume of pilotless helicopter.
As shown in Figure 3, for described driving engine is overturn and postrotational structural representation, comparison diagram 1 can be found out, than prior art, is the equal of that Magnetor stator 3 has been moved to 180 degree to existing position by original position in the present embodiment; It should be noted that when actual installation, this engine power output face is towards pilotless helicopter top, and the bottom of this driving engine is towards pilotless helicopter top.As shown in Figure 4, be the decomposition texture schematic diagram of described driving engine.Wherein, on described driving engine fuselage 1, be provided with mounting bracket 4, described Magnetor stator 3 is fixed on described mounting bracket 4.
As shown in Figure 5, be the structural representation of described mounting bracket 4.Described mounting bracket 4 comprises plate body 41; Described plate body 41 first sides are for being fixed on a side of the more close described pilotless helicopter front end of described engine power output face, on first side, be provided with two mounting holes 46, on driving engine, starting has the tapped bore 43 corresponding with these two mounting holes 46, screw be installed through described mounting hole 46 and screwed in after corresponding tapped bore 43, mounting bracket 4 is fixed on driving engine fuselage 1.On the Second Edge relative with described first side, being provided with in joint pin 42(the present embodiment that some and described plate body 41 is vertical is 2, can certainly be according to the more multi-link post 42 of actual conditions setting); Described Magnetor stator 3 is fixed on described joint pin 42.Further, in the present embodiment, also provide the fixed form between a kind of described Magnetor stator 3 and joint pin 42: described joint pin 42 axially offers tapped bore 43, on described Magnetor stator 3, be provided with the assembly opening 31 corresponding with described tapped bore 43, screw 45 be installed through described assembly opening 31 and screwed in corresponding tapped bore 43, described Magnetor stator 3 is fixed on described joint pin 42.Further, in the situation that trying one's best not lower mounting bracket semi-finals degree, reduce the weight of described mounting bracket 4, on the plate body 41 of mounting bracket described in the present embodiment 4, offer some hollow-out parts 44.
In addition, iff mobile Magnetor stator 3, and do not do other improvement, can be due to the change of Magnetor stator 3 positions, cause engine ignition reverse-phase 180 degree, thereby cannot, in orthochronous ignition operation, may cause and cannot to pilotless helicopter, control accurately like this.Therefore, in order, in orthochronous ignition operation, also the installation site that makes magneto rotor 2 in Fig. 1 have been rotated to 180 degree in the driving engine in the present embodiment simultaneously.Further, in the present embodiment, also provide a kind of concrete implementation:
The power output face of available engine is provided with rotating shaft, and on described magneto rotor 2, offers the centre hole 21 with described rotating shaft adaptation, thereby magneto rotor 2 can be set in described rotating shaft.In described rotating shaft, be conventionally provided with a card key, and on the circumference of described centre hole 21, offer accordingly a keyway 22 with described card key adaptation, when magneto rotor 2 is set in rotating shaft, by card key and coordinating of keyway 22 magneto rotor 2 and rotating shaft being fixed.The keyway that offers a plurality of and described card key adaptation 22 in the present embodiment on the circumference of magneto rotor centre hole 21, thus can, according to the difference of Magnetor stator 3 positions, select corresponding keyway 22 to carry out adaptation.For example, as shown in Figure 6, can on existing magneto rotor 2, newly drive 22, two keyways 22 of a keyway and just relatively distribute.Hold intelligiblely, also can provide separately new magneto rotor 2, make driving engine in orthochronous ignition operation, at this, not do particular determination.
Finally, in the present embodiment, also provide a kind of pilotless helicopter, as shown in Figure 2.This pilotless helicopter comprises above-mentioned driving engine.Certainly, in addition, this pilotless helicopter can also comprise screw propeller 5, alighting gear 6, empennage 7 etc., substantially similar in these parts and prior art, does not repeat them here.
Comprehensive above-described embodiment is known, in driving engine provided by the utility model and pilotless helicopter, by optimizing the mounting means of magneto generator, make between the structure of other parts in driving engine and pilotless helicopter body compacter, thereby better utilize the space of pilotless helicopter inside, and then reduce the overall volume of pilotless helicopter.In addition, in driving engine provided by the utility model, substantially do not need to destroy the integral structure of available engine, therefore realize cost extremely low, there is very strong practicality.
The foregoing is only preferred embodiment of the present utility model; not in order to limit the utility model; all within spirit of the present utility model and principle, any modification of making, be equal to replacement, improvement etc., within all should being included in the scope of the utility model protection.
Claims (8)
1. a driving engine, is placed in pilotless helicopter body; Described engine power output face is towards described pilotless helicopter top; Described engine power output face is provided with magneto rotor and Magnetor stator; It is characterized in that, described Magnetor stator is fixed on a side of the more close described pilotless helicopter front end of described engine power output face.
2. driving engine according to claim 1, is characterized in that, a side of the more close described pilotless helicopter front end of described engine power output face is provided with mounting bracket, and described Magnetor stator is fixed on described mounting bracket.
3. driving engine according to claim 2, is characterized in that, described mounting bracket comprises plate body; Described plate body first side is fixed on described driving engine fuselage, is provided with the vertical joint pin of some and described plate body on the Second Edge relative with described first side; Described Magnetor stator is fixed on described joint pin.
4. driving engine according to claim 3, is characterized in that, described joint pin axially offers tapped bore, is provided with the assembly opening corresponding with described tapped bore on described Magnetor stator; Described Magnetor stator is through the installation screw that screws in described tapped bore after described assembly opening and is fixed on described joint pin.
5. driving engine according to claim 3, is characterized in that, offers some hollow-out parts on described plate body.
6. driving engine according to claim 1, is characterized in that, described power output face is provided with rotating shaft, in described rotating shaft, is provided with card key; On described magneto rotor, offer the centre hole with described rotating shaft adaptation, on described centre hole circumference, offer the keyway of a plurality of and described card key adaptation.
7. driving engine according to claim 6, is characterized in that, offers two just relative keyways on described centre hole circumference.
8. a pilotless helicopter, is characterized in that, comprises according to the driving engine described in claim 1-7 any one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420092166.6U CN203854860U (en) | 2014-02-28 | 2014-02-28 | Engine and pilotless helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420092166.6U CN203854860U (en) | 2014-02-28 | 2014-02-28 | Engine and pilotless helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203854860U true CN203854860U (en) | 2014-10-01 |
Family
ID=51604730
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420092166.6U Expired - Fee Related CN203854860U (en) | 2014-02-28 | 2014-02-28 | Engine and pilotless helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203854860U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691766A (en) * | 2014-12-31 | 2015-06-10 | 湖北易瓦特科技有限公司 | UAV (unmanned aerial vehicle) |
-
2014
- 2014-02-28 CN CN201420092166.6U patent/CN203854860U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691766A (en) * | 2014-12-31 | 2015-06-10 | 湖北易瓦特科技有限公司 | UAV (unmanned aerial vehicle) |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Engine and pilotless helicopter Effective date of registration: 20150601 Granted publication date: 20141001 Pledgee: Wuxi New District Chuang friends financing Company limited by guarantee Pledgor: WUXI HANHE AVIATION TECHNOLOGY Co.,Ltd. Registration number: 2015320000005 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20160711 Granted publication date: 20141001 Pledgee: Wuxi New District Chuang friends financing Company limited by guarantee Pledgor: WUXI HANHE AVIATION TECHNOLOGY Co.,Ltd. Registration number: 2015320000005 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141001 |