CN103925118A - Unmanned aerial vehicle suitable for emergency surveying and mapping protection in plateau area - Google Patents
Unmanned aerial vehicle suitable for emergency surveying and mapping protection in plateau area Download PDFInfo
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- CN103925118A CN103925118A CN201410168525.6A CN201410168525A CN103925118A CN 103925118 A CN103925118 A CN 103925118A CN 201410168525 A CN201410168525 A CN 201410168525A CN 103925118 A CN103925118 A CN 103925118A
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- unmanned plane
- catapult
- bracket
- carburetor
- fuselage
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Abstract
The invention discloses an unmanned aerial vehicle suitable for emergency surveying and mapping protection in a plateau area. The unmanned aerial vehicle comprises a fuselage, an engine is installed at the front end of the fuselage, and a carburetor is connected to the engine. An exhaust pipe of the engine is externally connected with a gas guide pipe. The free end of the gas guide pipe faces a gas inlet of the carburetor and is close to the gas inlet. According to the unmanned aerial vehicle for emergency surveying and mapping protection in the plateau area, the exhaust pipe of the engine is externally connected with the gas guide pipe, heat generated by tail gas of the engine can be fed to the carburetor through the gas guide pipe, the gas inlet of the carburetor is heated through the heat, as a result, the gas inlet is effectively prevented from icing up, safe and stale operation of the engine is guaranteed, and flight performance is improved.
Description
Technical field
The present invention relates to SUAV field, relate in particular to the unmanned plane of the emergent topographic support in a kind of applicable plateau section.
Background technique
The motor that on market, unmanned plane uses is mainly large-scale model plane exploitation, there is certain limitation, as poor to the adaptive capacity of the conditions such as temperature, humidity, air pressure, when occurring contingency tasks environment, need to be in the time of the severe operating condition of the high height above sea level in mountain area, common engine can not be in this highly stable running.Because high altitude localities rarefaction of air, temperature is low, and under this environment, motor carburetor air mouth easily freezes, and gently reduces engine speed, heavy cause stopping working, and has a strong impact on the normal work of unmanned plane.
Summary of the invention
For this reason, the invention provides a kind of unmanned plane of the emergent topographic support in new applicable plateau section of at least a portion that at least can address the above problem, this unmanned plane can normally be worked in high altitude localities.
The unmanned plane that the invention provides the emergent topographic support in a kind of applicable plateau section, comprises fuselage, and front fuselage is provided with motor, is connected with Carburetor on motor; Wherein, on described engine exhaust pipe, be circumscribed with air pipe, the free end of described air pipe is towards the suction port of also close described Carburetor.
Alternatively, according to unmanned plane of the present invention, described air pipe is soft state copper tube.
Alternatively, according to unmanned plane of the present invention, the diameter of described air pipe is 5mm.
Alternatively, according to unmanned plane of the present invention, described external engine is provided with the catch that can shelter from Carburetor.
Alternatively, unmanned plane of the present invention, described unmanned plane further comprises undercarriage, described undercarriage and described fuselage removably connect.
Alternatively, according to unmanned plane of the present invention, described fuselage bottom belly is provided with two metal tubes that cross fuselage, and described undercarriage is bundled on described metal tube.
Alternatively, according to unmanned plane of the present invention, described unmanned plane further comprises ejection system, and described undercarriage is placed on described ejection system.
Alternatively, according to unmanned plane of the present invention, described ejection system comprises launching cradle, catapult bracket and power system, wherein, described launching cradle is obliquely installed, and described catapult bracket is connected on launching cradle and can slides along described launching cradle, and described catapult bracket is connected with described power system.
Alternatively, according to unmanned plane of the present invention, described catapult bracket comprises two dunnages that be arranged in parallel and is vertically connected on first crossbeam and the second cross beam in dunnage; The two ends of described first crossbeam and the two ends of second cross beam are all connected with vertical plate, on described vertical plate, are provided with restraining groove.
Alternatively, according to unmanned plane of the present invention, on described catapult bracket, be provided with locking mechanism.
Unmanned plane of the present invention is by external air pipe on waste pipe, the heat that can motor exhaust be produced by air pipe is fed to Carburetor, suction port to Carburetor heats, thereby effectively prevent that freezing from appearring in suction port, ensure engine health stable operation, improve flight performance.
Brief description of the drawings
By reading below detailed description of the preferred embodiment, various other advantage and benefits will become cheer and bright for those of ordinary skill in the art.Accompanying drawing is only for the object of preferred implementation is shown, and do not think limitation of the present invention.In the accompanying drawings:
Fig. 1 is the connection diagram of motor and Carburetor in unmanned plane of the present invention;
Fig. 2 is the connection diagram of unmanned plane of the present invention motor and Carburetor during with catch;
Fig. 3 is the structural representation of catapult bracket in unmanned plane of the present invention;
Fig. 4 be in unmanned plane of the present invention catapult cradle in locking state schematic diagram; And
Fig. 5 be in unmanned plane of the present invention catapult cradle in released state schematic diagram.
Embodiment
Below in conjunction with accompanying drawing and concrete mode of execution, the invention will be further described.
The invention provides a kind of mapping unmanned plane, this unmanned plane, by motor is improved with the structure that is connected of Carburetor, can normally work unmanned plane in the rugged environment of high height above sea level.
Unmanned plane of the present invention comprises fuselage, at front fuselage, motor is installed, and is connected with Carburetor on motor, and Fig. 1 illustrates the connection diagram of motor and Carburetor in unmanned plane of the present invention.As shown in Figure 1, on the outlet pipe 10 of described motor 1, be circumscribed with air pipe 3, the free end of described air pipe 3 towards and near the suction port of described Carburetor 2 (waste pipe can be many, in Fig. 1 only a schematically illustrated outlet pipe).Thus, the partial tail gas in engine exhaust pipe is delivered to the suction port of Carburetor through air pipe, thereby utilizes the heat that tail gas produces to heat carburetor air mouth, effectively prevents that freezing from appearring in suction port.This improvement structure, without existing unmanned plane and miscellaneous part are changed on a large scale, only need be bored one or more holes on waste pipe, then in hole, inserts air pipe, and operational sequence is simple, successful after improving.For the improvement that improves rear engine performance is described, claimant is to having carried out comparative trial with a motor at intake temperature and other parameter indexs before and after structure of modification, and experimental enviroment is: 5 DEG C of outdoor temperatures, humidity of the air 70%.Concrete test result is as shown in table 1 below:
Table 1 is with the working state contrast when the same throttle position of a motor
Can be found out by above-mentioned contrast form, improved motor compared to improve before intake temperature be significantly improved, under low-temp low-pressure with respect to transformation before more stable, power is higher.
In unmanned plane of the present invention, described air pipe 3 is soft state copper tube.Because the weight of copper tube is lighter, thermal conductivity is good, and low temperature intensity is high, again than flexible, the easy torsion of common metal, be difficult for crack, non-frangibility, and there is certain frost heaving resistant and impact resistance.And soft state copper tube is except occurring with straight tube, and form that also can coil pipe exists, and the benefit of coil pipe is that length is longer, when be used in that tie point grows local time, can freely intercept according to length, thus the appearance of the small opening of appearance while having avoided copper pipe to weld.Set it as air pipe, can adapt to various severe working environments, the heat in motor exhaust is sent to carburetor air mouth to greatest extent, and substantially do not increase the weight of unmanned plane entirety.The diameter of described air pipe 3 can be adjusted according to the type of unmanned plane, and in one embodiment of the present of invention, the diameter of described air pipe is 5mm.Adopt the soft state copper tube of general commercially available caliber 5mm.
In unmanned plane of the present invention, also have catch 4 in described motor 1 outer installment, as shown in Figure 2, described catch 4 wraps motor 1 and Carburetor 2, thereby can directly blow to Carburetor by barrier air, and Carburetor inclusion is formed to a closed area to keep Carburetor temperature.The aluminium alloy sheet that the preferred service property (quality) of described catch is light, intensity is high.
Unmanned plane of the present invention also comprises undercarriage, and described undercarriage and described fuselage removably connect.For example, at described fuselage bottom belly, two metal tubes that cross fuselage are set, by such as the link such as belt or rope, described undercarriage being bundled on described metal tube, binding is all very convenient with dismounting.
Further, unmanned plane of the present invention also comprises ejection system, and described undercarriage is placed on described ejection system, by ejection system, unmanned plane is carried out to catapult-assisted take-off.In one embodiment of the present of invention, described ejection system comprises launching cradle, catapult bracket and power system, and wherein, described launching cradle is obliquely installed, and its one end fixes on the ground, and the other end is made device by such as support etc. and is become certain altitude with ground.Launching cradle is positioned at one end starting point on ground, and its relative the other end is as end.Described catapult bracket is connected on launching cradle and can slides along described launching cradle, and described catapult bracket is connected with described power system.Before launching, described catapult bracket is positioned at the starting point of described launching cradle, when catapult-assisted take-off, under the power that catapult bracket applies by described power system, drive the unmanned plane on undercarriage to slide to launching cradle tail end, arrive after tail end, undercarriage departs from catapult bracket, and realization is taken off.Be understandable that, described ejection system and undercarriage can adopt existing product in prior art, as long as both are used in conjunction with the catapult-assisted take-off that can realize aircraft.
Participate in Fig. 3, in one embodiment of the invention, described catapult bracket comprises two dunnages 5 that be arranged in parallel and is vertically connected on first crossbeam 6 and the second cross beam 7 in dunnage.Spacing between two dunnages 5 is slightly larger than the width of launching cradle, to ensure that catapult bracket can slide along launching cradle.The two ends of the two ends of described first crossbeam 6 and second cross beam 7 are all connected with the first vertical plate 8, on described the first vertical plate 8, are provided with restraining groove 9.On undercarriage, be provided with 4 extensions can including in described restraining groove, these 4 extensions are placed in above-mentioned restraining groove, undercarriage can be limited on catapult bracket.
Further, in order to prevent that the unexpected landing of undercarriage extension from going out restraining groove, is also provided with locking mechanism on described catapult bracket.By this locking mechanism, can guarantee that unmanned plane under static state with after engine start is limited on catapult bracket, avoid occurring accidental and the danger situation that causes.Fig. 4 and Fig. 5 show respectively the schematic diagram of the locking mechanism adopting in one embodiment of the present invention under locking and released state.
Referring to Fig. 4 and Fig. 5, on second cross beam 7, be also connected with the second vertical plate 11 keeping at a certain distance away with described the first vertical plate 8, in the groove of described the first vertical plate 8 and the second vertical plate 14 spaces formation, be placed with slide block 12, on described slide block 12, there is aperture 15, ropy or ribbon, through this aperture, are then connected to ropy or ribbon to the starting point of launching cradle.The length of ropy or ribbon is generally 1 meter of left and right.On described the first vertical plate 8, pivotable is connected with hook sheet 11.All right linking springs 13 on described hook sheet 11, one end of described spring 13 is fixed on second cross beam.By spring 13 is set, can control direction and speed that hook sheet 11 rotates, prevent that hook sheet from acutely rotating and catapult bracket is caused to damage (not shown spring in Fig. 3).
When taking off, when taking off, the extension with undercarriage 16 is placed in the restraining groove 9 of catapult bracket, use slide block extruded hook sheet that undercarriage is fixed on bracket, make locking mechanism in locking state as shown in Figure 4.In the time that unmanned aerial vehicle ejecting takes off, under the power that catapult bracket provides in power system, slide to launching cradle tail end.In the time that catapult bracket advances 1 meter of left and right with undercarriage and unmanned plane, ribbon or ropy, in tensioning state, apply pulling force to slide block, and slide block is subject to pulling the groove skidding off between the first vertical plate 8 and the second vertical plate 14.Lose the squeezing action of slide block, hook sheet 11 moves downward under the effect of spring tension, as shown in Figure 5.Now, hook sheet disappears for the barrier effect of undercarriage, undercarriage release.Offer in power system under the powerful thrust of catapult bracket, unmanned plane undercarriage is limited on catapult bracket all the time, and drives unmanned plane to accelerate.When catapult movement of bracket is during to launching cradle end, unmanned plane accelerates to the speed of 80km left and right per hour, and undercarriage relies on the inertia bracket that flies out, and realizes unmanned aerial vehicle ejecting and takes off.
Unmanned plane of the present invention, by engine structure is carried out to small adjustment, has improved motor power at low temperatures, and unmanned plane can normally be worked under the higher severe working environment of height above sea level, completes the emergent mapping task of plateau section.
It should be noted, the present invention will be described instead of limit the invention for above-described embodiment, and those skilled in the art can design alternative embodiment in the case of not departing from the scope of claims.In the claims, any reference symbol between bracket should be configured to limitations on claims.Word " comprises " not to be got rid of existence and is not listed as element or step in the claims.The use of word first, second and C grade does not represent any order, can be title by these word explanations.
Claims (10)
1. a unmanned plane for the emergent topographic support in applicable plateau section, comprises fuselage, and front fuselage is provided with motor (1), is connected with Carburetor (2) on motor; Wherein,
On described engine exhaust pipe, be circumscribed with air pipe (3), the free end of described air pipe (3) is towards the suction port of also close described Carburetor (2).
2. unmanned plane according to claim 1, is characterized in that: described air pipe (3) is soft state copper tube.
3. unmanned plane according to claim 2, is characterized in that: the diameter of described air pipe (3) is 5mm.
4. unmanned plane according to claim 1, is characterized in that: described motor (1) outer installment has the catch (4) that can shelter from Carburetor (2).
5. according to the unmanned plane described in any one in claim 1-4, it is characterized in that: described unmanned plane further comprises undercarriage, described undercarriage and described fuselage removably connect.
6. unmanned plane according to claim 5, is characterized in that: described fuselage bottom belly is provided with two metal tubes that cross fuselage, and described undercarriage is bundled on described metal tube.
7. unmanned plane according to claim 5, is characterized in that: described unmanned plane further comprises ejection system, and described undercarriage is placed on described ejection system.
8. unmanned plane according to claim 7, is characterized in that: described ejection system comprises launching cradle, catapult bracket and power system, wherein,
Described launching cradle is obliquely installed, and described catapult bracket is connected on launching cradle and can slides along described launching cradle, and described catapult bracket is connected with described power system.
9. unmanned plane according to claim 8, is characterized in that: described catapult bracket comprises two dunnages (5) that be arranged in parallel and is vertically connected on first crossbeam (6) and the second cross beam (7) in dunnage; The two ends of the two ends of described first crossbeam (6) and second cross beam (7) are all connected with the first vertical plate (8), are provided with restraining groove (9) on described the first vertical plate (8).
10. unmanned plane according to claim 9, is characterized in that: on described catapult bracket, be provided with locking mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410168525.6A CN103925118A (en) | 2014-04-24 | 2014-04-24 | Unmanned aerial vehicle suitable for emergency surveying and mapping protection in plateau area |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410168525.6A CN103925118A (en) | 2014-04-24 | 2014-04-24 | Unmanned aerial vehicle suitable for emergency surveying and mapping protection in plateau area |
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| Publication Number | Publication Date |
|---|---|
| CN103925118A true CN103925118A (en) | 2014-07-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410168525.6A Pending CN103925118A (en) | 2014-04-24 | 2014-04-24 | Unmanned aerial vehicle suitable for emergency surveying and mapping protection in plateau area |
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| CN (1) | CN103925118A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105840360A (en) * | 2016-05-31 | 2016-08-10 | 四川鸿鑫空间测绘有限公司 | Surveying and mapping unmanned aerial vehicle for plateau region |
| CN112758312A (en) * | 2020-12-30 | 2021-05-07 | 阿坝师范学院 | Plateau is with many rotor unmanned aerial vehicle |
Citations (6)
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|---|---|---|---|---|
| CN2600337Y (en) * | 2002-11-18 | 2004-01-21 | 雷良榆 | Propeller helicopter driven by air injection |
| CN2665384Y (en) * | 2003-09-28 | 2004-12-22 | 光阳工业股份有限公司 | Engine carburetor anti-icing equipment |
| JP2007127095A (en) * | 2005-11-07 | 2007-05-24 | Nikki Co Ltd | Icing preventing device for carburetor |
| CN202429355U (en) * | 2011-12-19 | 2012-09-12 | 天津全华时代航天科技发展有限公司 | Engine cooling channel |
| CN103693207A (en) * | 2013-12-12 | 2014-04-02 | 桂林航龙科讯电子技术有限公司 | Small-sized unmanned aerial vehicle ejector |
| CN203892066U (en) * | 2014-04-24 | 2014-10-22 | 四川测绘地理信息局测绘技术服务中心 | Unmanned aerial vehicle suitable for emergency surveying-mapping guarantee in plateau areas |
-
2014
- 2014-04-24 CN CN201410168525.6A patent/CN103925118A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2600337Y (en) * | 2002-11-18 | 2004-01-21 | 雷良榆 | Propeller helicopter driven by air injection |
| CN2665384Y (en) * | 2003-09-28 | 2004-12-22 | 光阳工业股份有限公司 | Engine carburetor anti-icing equipment |
| JP2007127095A (en) * | 2005-11-07 | 2007-05-24 | Nikki Co Ltd | Icing preventing device for carburetor |
| CN202429355U (en) * | 2011-12-19 | 2012-09-12 | 天津全华时代航天科技发展有限公司 | Engine cooling channel |
| CN103693207A (en) * | 2013-12-12 | 2014-04-02 | 桂林航龙科讯电子技术有限公司 | Small-sized unmanned aerial vehicle ejector |
| CN203892066U (en) * | 2014-04-24 | 2014-10-22 | 四川测绘地理信息局测绘技术服务中心 | Unmanned aerial vehicle suitable for emergency surveying-mapping guarantee in plateau areas |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105840360A (en) * | 2016-05-31 | 2016-08-10 | 四川鸿鑫空间测绘有限公司 | Surveying and mapping unmanned aerial vehicle for plateau region |
| CN112758312A (en) * | 2020-12-30 | 2021-05-07 | 阿坝师范学院 | Plateau is with many rotor unmanned aerial vehicle |
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Application publication date: 20140716 |
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