CN203655479U - Low-temperature ignition security device of small gas engine of unmanned aerial vehicle - Google Patents
Low-temperature ignition security device of small gas engine of unmanned aerial vehicle Download PDFInfo
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- CN203655479U CN203655479U CN201420033669.6U CN201420033669U CN203655479U CN 203655479 U CN203655479 U CN 203655479U CN 201420033669 U CN201420033669 U CN 201420033669U CN 203655479 U CN203655479 U CN 203655479U
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Abstract
The utility model discloses a low-temperature ignition security device of a small gas engine of an unmanned aerial vehicle. The low-temperature ignition security device comprises a shell, heat conducting fins, cold air inlet pipes, a hot air discharge pipe, a waste gas inlet and a waste gas exhaust hole; there are a plurality of heat conducting fins which are uniformly arrayed in the shell at intervals; there are two cold air inlet pipes which pass through the shell, both ends of each cold air inlet pipe extend to the outside of the shell, and both the cold air inlet pipes pass through all the heat conducting fins in the shell; the hot air discharge pipe is located at the outside of the shell, air outlets of the two cold air inlet pipes at the same side of the outside of the shell are communicated with the hot air discharge pipe; the shell is further formed with the waste gas inlet and the waste gas exhaust hole, and both the waste gas inlet and the waste gas exhaust hole are communicated with the inside of the shell. The low-temperature ignition security device of the small gas engine of the unmanned aerial vehicle solves the difficulties of working under a subzero temperature and a high altitude.
Description
Technical field
The utility model relates to unmanned plane gasoline piston type power system inlet air heating technology, is specifically related to a kind of unmanned plane put-put low-temperature ignition ensuring equipment.
Background technique
Due to unmanned plane have motor-driven fast, user cost is low, safeguard and use the features such as simple, therefore at home and abroad extensively used, but that current unmanned aerial vehicle remote sensing platform technology also has is a lot of not enough.Wherein, sub-zero temperature and high height above sea level are exactly its difficult problem of hanging back.Due to sub-zero temperature and high height above sea level, in the working procedure of conventional reciprocating engine gasoline, air gas mixture is more difficult is lighted, and often there will be flame-out phenomenon therefore engine operation is unstable in flight course.And in order to keep low this technical characterstic of unmanned plane user cost, it must be unpractical using jet engine instead.
Model utility content
The heat of unmanned plane small-sized piston formula motor fuel burning is except being converted into useful mechanical energy, and all the other most heats are all lost in cooling, friction, transmission and the tail gas of mechanism, and wherein tail gas has been taken away the overwhelming majority.The thermal efficiency that how to improve unmanned plane small-sized piston formula motor is the focus of paying close attention to always, and is also one of energy-conservation important channel to the exploitation of tail gas energy.Technical problem to be solved in the utility model is to provide a kind of unmanned plane put-put low-temperature ignition ensuring equipment, recovered energy being used from the tail gas of unmanned plane small-sized piston formula motor fuel burning, improve capacity usage ratio, not only save the energy but also operating cost is reduced, under equal oil mass, can promote unmanned plane cruising range.The present invention has used for reference the anti-icing system of jet engine, the Btu utilization that engine operation is produced, air inlet to motor is heated, and after hotter air being entered combine with fuel oil in cylinder, is easier to burn, and guarantees motor reliably working under low temperature environment.
The technological scheme that the utility model solves the problems of the technologies described above is as follows: a kind of unmanned plane put-put low-temperature ignition ensuring equipment, comprises housing, heat-conducting plate, cool air suction tude, hot air steam outlet pipe, waste gas inlet and exhaust vent; Described heat-conducting plate has multi-disc, and all described heat-conducting plates are equidistant is arranged in described enclosure interior; Described cool air suction tude has two; two described cool air suction tude are all passed described housing; the two ends of two described cool air suction tude all extend to the outside of described housing, and two described cool air suction tude are all passed in all described heat-conducting plate of described enclosure interior; Described hot air steam outlet pipe is in described outside, is communicated with described hot air steam outlet pipe at the mouth of pipe of giving vent to anger of two described cool air suction tude of described outside the same side; On described housing, be also provided with waste gas inlet and exhaust vent, described waste gas inlet and exhaust vent are all communicated with described enclosure interior.
Further, described exhaust vent has two.
Further, the sealing of described hot air steam outlet pipe one end, one end is not sealed in addition, and one end that described hot air steam outlet pipe does not seal is communicated with unmanned plane small-sized piston formula engine intake.
Wherein, small-sized piston petrol engine is a kind of call of regular price gasoline motor of comparing.The main distinction of it and regular price gasoline motor has the following aspects: power capacity is little, and volume of cylinder is also less, is generally less than 1000ml, there is no perfect water-cooling heat radiating system, and weight is lighter, and motor adopts wind-cooling heat dissipating.Be used in the general two-stroke put-put that adopts on aviation aircraft, it has, and volume is little, lightweight, power ratio is large.Deficiency is that fuel efficiency is low, and temperature accommodation is narrow.According to SUAV practical application experience for many years, working stability is with regard to variation below 0 ℃ for small-sized piston petrol engine, and as easy as rolling off a log generation is flame-out in the air.For capturing this difficult problem, a kind of unmanned plane put-put low-temperature ignition ensuring equipment that the utility model provides just can reliably effectively be worked within the scope of 0 ℃ to-20 ℃.
The beneficial effects of the utility model are: a kind of unmanned plane put-put low-temperature ignition ensuring equipment that the utility model provides, be that the air that enters unmanned plane small-sized piston formula motor is heated with unmanned plane small-sized piston formula engine exhaust, can improve reciprocating engine cylinder temperature, fuel gasification rate is improved, sufficient combustion promotes SUAV engine efficiency, reaches the object of energy-saving and emission-reduction.Promote unmanned plane small-sized piston formula motor in sub-zero temperature and high height above sea level working efficiency simultaneously, solved unmanned plane small-sized piston formula motor operation difficult problem under the climate condition of sub-zero temperature and high height above sea level.
Accompanying drawing explanation
Fig. 1 is the utility model overall structure schematic diagram;
Fig. 2 is the utility model sectional view;
Fig. 3 is the utility model partial sectional view.
In accompanying drawing, the list of parts of each label representative is as follows:
1, housing, 2, heat-conducting plate, 3, cool air suction tude, 4, hot air steam outlet pipe, 5, waste gas inlet, 6, exhaust vent.
Embodiment
Below in conjunction with accompanying drawing, principle of the present utility model and feature are described, example, only for explaining the utility model, is not intended to limit scope of the present utility model.
As shown in Figure 1,2 and 3, a kind of unmanned plane put-put low-temperature ignition ensuring equipment, comprises housing 1, heat-conducting plate 2, cool air suction tude 3, hot air steam outlet pipe 4, waste gas inlet 5 and exhaust vent 6; Described heat-conducting plate 2 has multi-disc, equidistant described housing 1 inside that is arranged in of all described heat-conducting plates 2; Described cool air suction tude 3 has two; two described cool air suction tude 3 are all passed described housing 1; the two ends of two described cool air suction tude 3 all extend to the outside of described housing 1, and two described cool air suction tude 3 are all passed in all described heat-conducting plate 2 of described housing 1 inside; Described hot air steam outlet pipe 4 is in described housing 1 outside, is communicated with described hot air steam outlet pipe 4 at the mouth of pipe of giving vent to anger of two described cool air suction tude 3 of described housing 1 outside the same side; On described housing 1, be also provided with waste gas inlet 5 and exhaust vent 6, described waste gas inlet 5 and exhaust vent 6 are all communicated with described housing 1 inside.After unmanned plane small-sized piston formula engine start, the waste gas that motor operation produces enters housing 1 inside from waste gas inlet 5, in the inside of housing 1, flow in the space of air-flow between heat-conducting plate 2, when air-flow is during through the outer wall of supercooled air suction tude 3, the cool air heat exchange entering in cool air suction tude 3 is heated, extruding by heat-conducting plate 2 to air-flow, make the area of contact of air-flow and cool air suction tude 3 outer walls larger, improve the cool air heat transfer rate in air-flow and cool air suction tude 3, described waste gas inlet 5 has two, after air-flow cooling after heat exchange, discharged by two exhaust vents 6, cold empty heat exchange in cool air suction tude 3 enters into hot air steam outlet pipe 4 after heating, described hot air steam outlet pipe 4 one end sealings, one end is not sealed in addition.One end that hot air steam outlet pipe 4 does not seal is communicated with unmanned plane small-sized piston formula engine intake.
When the operation of unmanned plane small-sized piston formula motor, cool air enters into unmanned plane put-put low-temperature ignition ensuring equipment by hot air steam outlet pipe 4, by moving after the waste gas heat exchange producing with unmanned plane small-sized piston formula motor, cool air is heated and is become hot air gradually, hot air is entered in unmanned plane small-sized piston formula motor by hot air steam outlet pipe 4 again, after hot air accelerates by engine and carburetor " trunnion ", after mixing with atomization gas, form inflammable gas by piston inhaling air cylinder body, compressing inflammable gas is to spark plug discharge igniting blast acting.Can improve reciprocating engine cylinder temperature, fuel gasification rate is improved, sufficient combustion promotes SUAV engine efficiency, reaches the object of energy-saving and emission-reduction.The Btu utilization that engine operation is produced, heats the air inlet of motor, after hotter air being entered combine with fuel oil in cylinder, is easier to burn, and guarantees motor reliably working under low temperature environment.Promote the working efficiency of unmanned plane small-sized piston formula motor under the climate condition of sub-zero temperature and in high altitude environment, solved the operation difficult problem of unmanned plane small-sized piston formula motor in sub-zero temperature and high altitude environment.
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 doing, be equal to replacement, improvement etc., within all should being included in protection domain of the present utility model.
Claims (3)
1. a unmanned plane put-put low-temperature ignition ensuring equipment, is characterized in that: comprise housing (1), heat-conducting plate (2), cool air suction tude (3), hot air steam outlet pipe (4), waste gas inlet (5) and exhaust vent (6); Described heat-conducting plate (2) has multi-disc, equidistant described housing (1) inside that is arranged in of all described heat-conducting plates (2); Described cool air suction tude (3) has two; two described cool air suction tude (3) are all passed described housing (1); the two ends of two described cool air suction tude (3) all extend to the outside of described housing (1), and two described cool air suction tude (3) are all passed in the inner all described heat-conducting plate (2) of described housing (1); Described hot air steam outlet pipe (4) is in described housing (1) outside, is communicated with described hot air steam outlet pipe (4) at the mouth of pipe of giving vent to anger of two described cool air suction tude (3) of the outside the same side of described housing (1); On described housing (1), be also provided with waste gas inlet (5) and exhaust vent (6), described waste gas inlet (5) and exhaust vent (6) are all communicated with described housing (1) inside.
2. a kind of unmanned plane put-put low-temperature ignition ensuring equipment according to claim 1, is characterized in that: described exhaust vent (5) has two.
3. a kind of unmanned plane put-put low-temperature ignition ensuring equipment according to claim 1 and 2, it is characterized in that: the sealing of described hot air steam outlet pipe (4) one end, one end is not sealed in addition, and one end that described hot air steam outlet pipe (4) does not seal is communicated with unmanned plane small-sized piston formula engine intake.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420033669.6U CN203655479U (en) | 2014-01-20 | 2014-01-20 | Low-temperature ignition security device of small gas engine of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420033669.6U CN203655479U (en) | 2014-01-20 | 2014-01-20 | Low-temperature ignition security device of small gas engine of unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203655479U true CN203655479U (en) | 2014-06-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420033669.6U Expired - Fee Related CN203655479U (en) | 2014-01-20 | 2014-01-20 | Low-temperature ignition security device of small gas engine of unmanned aerial vehicle |
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| CN (1) | CN203655479U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103790739A (en) * | 2014-01-20 | 2014-05-14 | 桂林航龙科讯电子技术有限公司 | Low temperature ignition guaranteeing device of small gasoline engine of unmanned aerial vehicle |
| CN110242449A (en) * | 2019-06-24 | 2019-09-17 | 淮安信息职业技术学院 | Charge heating and the united loading machine engine of water circulation cooling |
-
2014
- 2014-01-20 CN CN201420033669.6U patent/CN203655479U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103790739A (en) * | 2014-01-20 | 2014-05-14 | 桂林航龙科讯电子技术有限公司 | Low temperature ignition guaranteeing device of small gasoline engine of unmanned aerial vehicle |
| CN103790739B (en) * | 2014-01-20 | 2016-01-13 | 桂林航龙科讯电子技术有限公司 | A kind of unmanned plane put-put low-temperature ignition ensuring equipment |
| CN110242449A (en) * | 2019-06-24 | 2019-09-17 | 淮安信息职业技术学院 | Charge heating and the united loading machine engine of water circulation cooling |
| CN110242449B (en) * | 2019-06-24 | 2021-03-30 | 淮安信息职业技术学院 | Loader engine combining air inlet preheating and water circulation heat dissipation |
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| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140618 Termination date: 20170120 |
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| CF01 | Termination of patent right due to non-payment of annual fee |