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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- carburetor
- ejection
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- 238000013507 mapping Methods 0.000 title claims abstract description 10
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 7
- 229910052802 copper Inorganic materials 0.000 claims description 7
- 239000010949 copper Substances 0.000 claims description 7
- 229910052751 metal Inorganic materials 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 7
- 230000007246 mechanism Effects 0.000 claims description 6
- 210000001015 abdomen Anatomy 0.000 claims description 3
- 230000008901 benefit Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
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- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
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 invention relates to the field of small unmanned aerial vehicles, in particular to an unmanned aerial vehicle suitable for emergency surveying and mapping guarantee in plateau areas.
Background
The engine that unmanned aerial vehicle used in the market mainly is large-scale model aeroplane and model ship development, has certain limitation, and is relatively poor like the adaptability to conditions such as temperature, humidity, atmospheric pressure, when emergent task environment appears, when needing the abominable operating condition at mountain area high altitude, ordinary engine can not be in this highly stable operation. Because the air in the high-altitude area is thin and the air temperature is low, the air inlet of the engine carburetor in the environment is easy to freeze, the rotating speed of the engine is reduced if the air inlet is light, and flameout is caused if the air inlet is heavy, so that the normal work of the unmanned aerial vehicle is seriously influenced.
Disclosure of Invention
Therefore, the invention provides a novel unmanned aerial vehicle suitable for emergency surveying and mapping guarantee of plateau areas, which can at least solve at least part of the problems, and the unmanned aerial vehicle can normally work in the high-altitude areas.
The invention provides an unmanned aerial vehicle suitable for emergency surveying and mapping guarantee in plateau areas, which comprises a body, wherein an engine is installed at the front end of the body, and a carburetor is connected to the engine; the engine exhaust pipe is externally connected with an air guide pipe, and the free end of the air guide pipe faces to and is close to the air inlet of the carburetor.
Optionally, according to the unmanned aerial vehicle of the present invention, the air duct is a soft copper tube.
Optionally, according to the drone of the present invention, the diameter of the airway tube is 5 mm.
Optionally, according to the unmanned aerial vehicle of the invention, the engine is externally provided with a baffle plate capable of shielding the carburetor.
Optionally, the unmanned aerial vehicle further includes a landing gear, and the landing gear is detachably connected to the body.
Optionally, according to the unmanned aerial vehicle of the present invention, the lower abdomen of the fuselage is provided with two metal pipes traversing the fuselage, and the landing gear is bound on the metal pipes.
Optionally, in accordance with the drone of the present invention, the drone further comprises an ejection system, the landing gear being disposed on the ejection system.
Optionally, according to the unmanned aerial vehicle of the present invention, the ejection system includes an ejection rack, an ejector bracket and a power system, wherein the ejection rack is disposed obliquely, the ejector bracket is connected to the ejection rack and can slide along the ejection rack, and the ejector bracket is connected to the power system.
Optionally, according to the drone of the present invention, the ejector bracket includes two support plates arranged in parallel and a first beam and a second beam vertically connected to the support plates; the two ends of the first cross beam and the two ends of the second cross beam are both connected with vertical plates, and limiting grooves are formed in the vertical plates.
Optionally, according to the drone of the present invention, the ejector bracket is provided with a locking mechanism.
According to the unmanned aerial vehicle, the air guide pipe is externally connected to the exhaust pipe of the engine, heat generated by tail gas of the engine can be fed to the carburetor through the air guide pipe, and the air inlet of the carburetor is heated, so that the air inlet is effectively prevented from being frozen, the safe and stable operation of the engine is ensured, and the flight performance is improved.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. In the drawings:
FIG. 1 is a schematic view of the connection between an engine and a carburetor of the unmanned aerial vehicle according to the present invention;
FIG. 2 is a schematic view of the connection between the engine and the carburetor of the unmanned aerial vehicle with the flap according to the present invention;
fig. 3 is a schematic structural diagram of a catapult bracket in the unmanned aerial vehicle according to the invention;
fig. 4 is a schematic view of the ejector bracket of the unmanned aerial vehicle in a locked state according to the present invention; and
fig. 5 is a schematic diagram of the unmanned aerial vehicle according to the present invention, with the ejector bracket in an unlocked state.
Detailed Description
The invention is further described with reference to the following figures and detailed description of embodiments.
The invention provides an unmanned aerial vehicle for surveying and mapping, which can normally work in a severe environment with high altitude by improving a connection structure of an engine and a carburetor.
The unmanned aerial vehicle comprises a body, an engine is mounted at the front end of the body, a carburetor is connected to the engine, and fig. 1 shows a schematic connection diagram of the engine and the carburetor in the unmanned aerial vehicle. As shown in fig. 1, an air duct 3 is externally connected to an exhaust pipe 10 of the engine 1, and a free end of the air duct 3 faces and is close to an air inlet of the carburetor 2 (there may be a plurality of exhaust pipes of the engine, and only one exhaust pipe is schematically shown in fig. 1). Therefore, partial tail gas in the engine exhaust pipe is conveyed to the air inlet of the carburetor through the gas guide pipe, so that the heat generated by the tail gas is utilized to heat the air inlet of the carburetor, and the air inlet is effectively prevented from being frozen. This improve structure need not to carry out extensive change to current unmanned aerial vehicle and other parts, only need bore one or more holes on the blast pipe of engine, then insert the air duct in the hole can, operating is simple, and the effect is obvious after improving. In order to illustrate the improvement of the performance of the engine after the improvement, the applicant carries out a comparative test on the air inlet temperature and other parameter indexes of the same type of engine before and after the structural modification, and the test environment is as follows: the outdoor temperature is 5 ℃ and the air humidity is 70 percent. The specific test results are shown in table 1 below:
TABLE 1 comparison of operating states of the same engine at the same throttle position
As can be seen from the comparison table, the intake temperature of the modified engine is obviously improved compared with that before modification, and the modified engine is more stable and has higher power under low temperature and low pressure compared with that before modification.
In the unmanned aerial vehicle, the air duct 3 is a soft copper tube. The copper tube has light weight, good thermal conductivity and high low-temperature strength, is more flexible, easier to twist, less prone to crack and break than common metals, and has certain frost heaving resistance and impact resistance. And the soft copper tube can exist in the form of a coil pipe except for a straight tube, and the coil pipe has the advantage of longer length, and can be freely intercepted according to the length when being used in a place with longer connection point, thereby avoiding the occurrence of leak holes when the copper tube is welded. Regard it as the air duct, can adapt to various abominable operational environment, convey the heat furthest in the engine exhaust to the carburetor air inlet, and do not increase the holistic weight of unmanned aerial vehicle basically. The diameter of the air duct 3 can be adjusted according to the type of the unmanned aerial vehicle, and in one embodiment of the invention, the diameter of the air duct is 5 mm. The soft copper tube with the tube diameter of 5mm which is generally sold on the market is adopted.
In the unmanned aerial vehicle, a baffle plate 4 is further arranged outside the engine 1, as shown in fig. 2, the baffle plate 4 wraps the engine 1 and the carburetor 2, so that the air flow can be prevented from directly blowing to the carburetor, and a closed area is formed for enclosing the carburetor to keep the temperature of the carburetor. The baffle plate is preferably made of an aluminum alloy sheet with light weight and high strength.
The unmanned aerial vehicle also comprises an undercarriage, and the undercarriage is detachably connected with the body. For example, two metal tubes are provided across the fuselage at the lower belly of the fuselage, and the landing gear is secured to the metal tubes by a connector such as a strap or rope, which is very convenient to secure and remove.
Furthermore, the unmanned aerial vehicle also comprises an ejection system, wherein the undercarriage is arranged on the ejection system, and the unmanned aerial vehicle is ejected and taken off through the ejection system. In one embodiment of the invention, the ejection system comprises an ejection rack, an ejector bracket and a power system, wherein the ejection rack is arranged obliquely, one end of the ejection rack is fixed on the ground, and the other end of the ejection rack is arranged at a certain height with the ground through a manufacturing device such as a bracket. The ejection rack is positioned at the starting end of one end of the ground, and the other end of the ejection rack is used as the tail end. The ejector bracket is connected to an ejection rack and can slide along the ejection rack, and the ejector bracket is connected with the power system. Before ejection, the ejector bracket is positioned at the starting end of the ejection frame, when the ejection takes off, the ejector bracket drives the unmanned aerial vehicle on the undercarriage to slide towards the tail end of the ejection frame under the power applied by the power system, and after the unmanned aerial vehicle reaches the tail end, the undercarriage is separated from the ejector bracket, so that the take-off is realized. It will be appreciated that the ejection system and landing gear may be any known product known in the art, provided that they cooperate to enable the catapult-assisted take-off of an aircraft.
Referring to fig. 3, in one embodiment of the present invention, the ejector bracket includes two support plates 5 arranged in parallel and a first beam 6 and a second beam 7 vertically connected to the support plates. The distance between the two supporting plates 5 is slightly larger than the width of the ejection rack so as to ensure that the ejector bracket can slide along the ejection rack. The two ends of the first cross beam 6 and the two ends of the second cross beam 7 are both connected with first vertical plates 8, and limiting grooves 9 are formed in the first vertical plates 8. 4 extending parts capable of being accommodated in the limiting grooves are arranged on the undercarriage, and the 4 extending parts are placed in the limiting grooves, so that the undercarriage can be limited on the ejector bracket.
Furthermore, in order to prevent the extension part of the undercarriage from accidentally sliding out of the limiting groove, a locking mechanism is further arranged on the ejector bracket. Through this locking mechanism, can ensure that unmanned aerial vehicle is injectd on the catapult bracket with the engine start-up after under quiescent condition, avoid appearing the accident and drop and the dangerous situation that leads to. Fig. 4 and 5 show schematic views of a locking mechanism employed in one embodiment of the present invention in locked and unlocked states, respectively.
Referring to fig. 4 and 5, a second vertical plate 11 is further connected to the second cross beam 7 and is spaced from the first vertical plate 8, a sliding block 12 is placed in a groove formed by a gap between the first vertical plate 8 and the second vertical plate 14, a small hole 15 is formed in the sliding block 12, a rope or a belt is passed through the small hole, and then the rope or the belt is connected to the starting end of the ejection rack. The length of the rope or belt is typically about 1 meter. A hook tab 11 is pivotally connected to the first vertical plate 8. A spring 13 can be connected to the hook plate 11, and one end of the spring 13 is fixed to the second beam. By providing the spring 13, the direction and speed of rotation of the hook plate 11 can be controlled, preventing the hook plate from rotating violently and causing damage to the ejector bracket (the spring is not shown in fig. 3).
When the aircraft does not need to take off, the extension part 16 with the undercarriage is placed in the limiting groove 9 of the catapult bracket, and the slider is used for extruding the hook piece to fix the undercarriage on the bracket, so that the locking mechanism is in a locking state as shown in figure 4. When the unmanned aerial vehicle takes off in an ejection mode, the ejector bracket slides towards the tail end of the ejection rack under the power provided by the power system. When the ejector carriage advances with the undercarriage and drone about 1 metre, the belt or rope is under tension, applying a pulling force to the slider, which is pulled to slide out of the groove between the first and second vertical plates 8, 14. Losing the pressing action of the slider, the hook piece 11 moves downward under the spring tension, as shown in fig. 5. At this point, the blocking effect of the hook piece on the undercarriage disappears, and the undercarriage is unlocked. Under the powerful thrust effect that driving system provided for the catapult bracket, the unmanned aerial vehicle undercarriage was restricted on the catapult bracket all the time to drive unmanned aerial vehicle with higher speed. When the catapult bracket moves to the tail end of the catapult frame, the unmanned aerial vehicle accelerates to the speed of about 80km per hour, and the undercarriage flies out of the bracket by means of inertia to realize the catapult takeoff of the unmanned aerial vehicle.
According to the unmanned aerial vehicle, the power of the engine at a low temperature is improved by slightly adjusting the structure of the engine, so that the unmanned aerial vehicle can normally work in a severe working environment with a higher altitude, and an emergency surveying and mapping task in a plateau area is completed.
It should be noted that the above-mentioned embodiments illustrate rather than limit the invention, and that those skilled in the art will be able to design alternative embodiments without departing from the scope of the appended claims. In the claims, any reference signs placed between parentheses shall not be construed as limiting the claim. The word "comprising" does not exclude the presence of elements or steps not listed in a claim. The usage of the words first, second and third, etcetera do not indicate any ordering and these words may be interpreted as names.
Claims (10)
1. An unmanned aerial vehicle suitable for emergency surveying and mapping guarantee in plateau areas comprises a body, wherein an engine (1) is mounted at the front end of the body, and a carburetor (2) is connected to the engine; wherein,
an air duct (3) is externally connected to the engine exhaust pipe, and the free end of the air duct (3) faces and is close to the air inlet of the carburetor (2).
2. The drone of claim 1, wherein: the gas-guide tube (3) is a soft copper tube.
3. A drone according to claim 2, characterized in that: the diameter of the air duct (3) is 5 mm.
4. The drone of claim 1, wherein: and a baffle plate (4) capable of shielding the carburetor (2) is arranged outside the engine (1).
5. A drone according to any one of claims 1 to 4, characterised in that: the unmanned aerial vehicle further comprises an undercarriage, and the undercarriage is detachably connected with the body.
6. A drone according to claim 5, characterised in that: the lower belly of the fuselage is provided with two metal tubes which transversely penetrate through the fuselage, and the undercarriage is bound on the metal tubes.
7. A drone according to claim 5, characterised in that: the unmanned aerial vehicle further comprises an ejection system, and the landing gear is arranged on the ejection system.
8. A drone according to claim 7, characterized in that: the ejection system comprises an ejection rack, an ejector bracket and a power system, wherein,
the ejection rack is obliquely arranged, the ejector bracket is connected to the ejection rack and can slide along the ejection rack, and the ejector bracket is connected with the power system.
9. The drone of claim 8, wherein: the ejector bracket comprises two support plates (5) which are arranged in parallel, and a first cross beam (6) and a second cross beam (7) which are vertically connected to the support plates; the two ends of the first cross beam (6) and the two ends of the second cross beam (7) are connected with first vertical plates (8), and limiting grooves (9) are formed in the first vertical plates (8).
10. A drone according to claim 9, characterized in that: and a locking mechanism is arranged on the ejector bracket.
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)
| 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 device |
| 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 device |
| 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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