CN112550752B - Multimode take-off and landing unmanned aerial vehicle for plateau middle and low altitude supervision - Google Patents
Multimode take-off and landing unmanned aerial vehicle for plateau middle and low altitude supervision Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/06—Ground or aircraft-carrier-deck installations for launching aircraft using catapults
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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Abstract
The invention discloses a multimode take-off and landing unmanned aerial vehicle for monitoring low and medium altitudes in plateaus, which not only can be used for sliding off and landing and lifting by itself, but also can be used for catapult take-off by taking gunpowder as a power source, a user can select a proper take-off and landing mode according to the field condition so as to achieve better use effect, and the gunpowder is used as the power, so that the generated thrust is large, the structure is simple, and the multimode take-off and landing unmanned aerial vehicle comprises: fuselage, wing constitute, the wing includes: the fixed wing and the tail wing are provided with the rotor wings, so that the sliding, lifting and self-lifting can be realized, the ejection bin is arranged at the tail of the machine body, the movable plate is arranged in the ejection bin, when the impact force is received, the movable plate moves to extrude a medium on one side of the movable plate, the impact force of part of gunpowder is absorbed through compressing the medium, and the damage of the gunpowder explosion to the ejection bin is reduced.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a multimode take-off and landing unmanned aerial vehicle for plateau medium and low altitude supervision.
Background
The unmanned plane is called unmanned plane for short, and is an unmanned aerial vehicle operated by radio remote control equipment and a self-contained program control device. Unmanned aerial vehicles are in fact a general term for unmanned aerial vehicles, and can be defined from a technical perspective as follows: unmanned fixed wing aircraft, unmanned VTOL aircraft, unmanned airship, unmanned helicopter, unmanned multi-rotor aircraft, unmanned paravane, etc. Compared with manned aircraft, it has the advantages of small volume, low cost, convenient use, low requirement on the operation environment, strong battlefield viability and the like; the unmanned aerial vehicle for middle and low altitude surveillance has wider application and is applied to various scenes such as power patrol inspection, agriculture and the like, and particularly, in the power patrol inspection, the unmanned aerial vehicle provided with a high-definition digital video camera, a camera and a GPS positioning system can perform positioning autonomous cruise along a power grid and transmit shot images in real time, monitoring personnel can synchronously watch and control on a computer, the traditional manual power line patrol mode is changed, conditions are hard, the efficiency is low, and a first-line power patrol worker occasionally encounters dangers of being bitten by dogs and snakes. The unmanned aerial vehicle realizes electronization, informatization and intelligent routing inspection, and improves the working efficiency of routing inspection of the power line, the emergency rescue level and the power supply reliability. Under emergency situations such as mountain torrents, earthquake disasters and the like, the unmanned aerial vehicle can survey and emergently investigate potential dangers of lines, such as collapse of a tower foundation and other problems, is not influenced by road conditions at all, avoids the trouble of climbing a tower, can survey visual dead angles of human eyes, and is very helpful for rapidly recovering power supply; and in the agricultural, unmanned aerial vehicle utilizes the device flight on the farmland of having integrateed high definition digital camera, spectral analysis appearance, thermal infrared sensor etc. and accurately calculates the planting area of insuring the plot, and the data gathered can be used to aassessment crops risk condition, insurance rate to can be for the damaged farmland of suffering from a disaster, in addition, unmanned aerial vehicle's patrol has still realized the monitoring to crops. The application of unmanned aerial vehicles in the field of environmental protection can be roughly divided into three types. Firstly, the method comprises the following steps: and (3) environmental monitoring: the conditions of air, soil, vegetation and water quality are observed, and the development of sudden environmental pollution events can be quickly tracked and monitored in real time; II, environment law enforcement: an environmental monitoring department utilizes an unmanned aerial vehicle carrying acquisition and analysis equipment to cruise in a specific area, monitors the exhaust gas and wastewater discharge of an enterprise factory and searches for a pollution source; thirdly, environmental management: the flexible wing unmanned aerial vehicle carrying the catalyst and being arranged for meteorological detection is used for spraying in the air, and the haze is eliminated in a certain area as the working principle of pesticide spraying of the unmanned aerial vehicle. The reason for recommendation is: the unmanned aerial vehicle carries out the aerial photography, and the persistence is strong, still can adopt modes such as far infrared night is taken photo, realizes all-weather navigation monitoring, and unmanned aerial vehicle law enforcement is not restricted by space and topography again. The system has the advantages of strong timeliness, good maneuverability and wide patrol range, and particularly in Jingjin Ji areas with severe haze, law enforcement personnel can timely troubleshoot pollution sources and slow down the pollution degree of the haze to a certain extent.
However, in the prior art, the unmanned aerial vehicle has a single take-off and landing mode, most of the fixed wings run and land, and the rotor wings lift and land by themselves, which has high requirements on the ground, and the rotor wings lift and land can be influenced by weather, in a plateau environment, the weather conditions are complex, and the take-off and landing field is uneven, which has great influence on take-off, so that the take-off and landing of the unmanned aerial vehicle in the plateau environment are obviously limited, so that the prior art provides an unmanned aerial vehicle for catapulting and lifting off, which is placed on an inclined slide way, and provides a catapulting force for the unmanned aerial vehicle, and catapulting and lifting off the unmanned aerial vehicle.
The Chinese invention patent with the application number of 2016106746804 discloses an aircraft carrier aircraft catapult device, an aircraft is catapulted out by the explosion of gunpowder, as is well known, the gunpowder is an explosive, a large amount of heat energy can be released after detonation, high-temperature and high-pressure gas is generated, and a great thrust force can be generated only by a small amount of gunpowder, which is obviously an effective pushing means, but the technology uses the gunpowder in the catapult of a carrier aircraft, as is well known, the weight of the carrier aircraft is far greater than that of an unmanned aerial vehicle, the required amount of gunpowder is great to catapult the carrier aircraft, although the calorific value of the gunpowder and the generated pressure are calculated, the output dotted line of the gunpowder is not ideal, the carrier aircraft with the great driving weight takes off, power needs to be continuously provided, the gunpowder has great power only in the initial stage and then is lost, the unmanned aerial vehicle can not provide stable power, more importantly, the thrust for pushing the carrier-based aircraft is very large, the required gunpowder is also very large, the pressure generated by gunpowder explosion does not act on the carrier-based aircraft completely, and can also act on a reaction vessel, if the reaction vessel is not protected, the gunpowder can be easily exploded into a ring, so the technology is not suitable for being used on the carrier-based aircraft, but the technical characteristic of catapult takeoff through gunpowder explosion can be used on the unmanned aerial vehicle, because the weight of the unmanned aerial vehicle is far smaller than that of the carrier-based aircraft, the required thrust is greatly reduced, a small amount of gunpowder can achieve the effect, because the unmanned aerial vehicle has small mass, the launch does not need to continuously provide power, the power generated by the gunpowder explosion is enough to push the unmanned aerial vehicle to the sky, and then the flight can be realized by utilizing the power of the unmanned aerial vehicle per se, compared with the complex structure in the prior art, obviously, the method is more practicable, but the prior art is not related to the unmanned aerial vehicle.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle capable of taking off and landing in multiple modes, which not only can take off and land in a conventional running mode and a self-operated lifting mode, but also can take off in an ejection mode, is convenient for a user to select different take-off modes according to specific conditions, and is more convenient to use.
In order to achieve the purpose, the invention adopts the following technical scheme:
a multimode take-off and landing unmanned aerial vehicle for plateau middle and low altitude supervision comprises: fuselage, wing, fin, jettison gear, during the use, unmanned aerial vehicle places on the slide of jettison gear, takes off from the jettison gear through the thrust that jettison gear produced, the wing includes: the unmanned aerial vehicle comprises fixed wings, rotor wings and an empennage, wherein the fixed wings are arranged on two sides of a fuselage, a control unit is arranged in the fuselage and used for controlling the motion of the unmanned aerial vehicle, the rotor wings are arranged on the fixed wings, the rotor wings are arranged on a straight rod, the straight rod is parallel to the axis of the fuselage, a support frame is further arranged on the part of the straight rod, facing downwards, of the side face of the straight rod, the height of the support frame is higher than that of the fuselage, the straight rod is at least provided with two rotor wings, and wing wheels are arranged at the bottom of the support frame;
the ejection device is an ejection bin, the ejection bin is arranged at the tail of the machine body, the shell of the ejection bin is an open cylinder and is of a double-layer structure, namely: the ejection cabin comprises an outer wall and an inner wall, wherein a certain gap is reserved between the outer wall and the inner wall, a reinforcing net is arranged in the gap, the reinforcing net is of a net structure formed by interweaving metal strips, the reinforcing net is fixed on the outer side of the inner wall, a bottom ring is arranged at the edge of an open end of the ejection cabin, the bottom ring is a magnetic ring, a movable plate is further arranged in the inner wall, the movable plate and the inner wall are the same in cross-sectional shape and can vertically move in the inner wall, the movable plate divides the space of the inner wall into two parts, one part is a closed space close to the closed end, the other part is located at the open end, and the two parts are filled with media;
the magnetic catapult is characterized in that the magnetic plate is arranged at the tail end of the lowest point of the catapult slide way, the magnetic plate is a magnetic flat plate, a small amount of gunpowder can be fixed on the magnetic plate when the magnetic plate is used, the catapult bin covers the gunpowder on the magnetic plate by using magnetic force, and catapult take-off is performed by using thrust generated by gunpowder explosion.
Further, the thickness of the reinforcing mesh is smaller than the width of a gap between the inner wall and the outer wall.
Further, the medium is water and air, the height of the water is 1/3 of the height of the closed part when the closed part is not pressurized, and the rest part of the closed part is air.
Furthermore, the outer side of the outer wall is also provided with a clamping ring which is fixed on the outer side of the outer wall.
Furthermore, a plurality of radiating fins are arranged on the outer side surface of the outer wall, and the radiating fins are inclined metal sheets.
The invention has at least the following beneficial effects:
(1) Can take off and land, lift by oneself in the roll-off, can also launch and take off, the mode is more, and the user can select different modes of taking off and land according to the condition in place in the use.
(2) Catapult takes off and passes through gunpowder as the power supply, compares in prior art and passes through elastic component such as spring as the power supply for, gunpowder is simpler as the structure of power supply, and is lower to the support requirement, can adjust the size of thrust through calculating moreover, has bigger flexibility, and the gunpowder explosion produces thrust bigger, and thrust is more sufficient.
(3) The ejection cabin is internally provided with the movable plate and the radiating fins, the medium on the other side of the movable plate can be compressed through the movement of the movable plate, so that the pressure generated by part of explosion is offset, and the ejection cabin is ensured not to be damaged by gunpowder by matching with the reinforcing measures of the ejection cabin.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiment(s) of the invention and together with the description, serve to explain the invention and not to limit the invention.
In the drawings:
FIG. 1 is a schematic view showing the structure of example 1 of the present invention;
FIG. 2 is a schematic side view of embodiment 2 of the present invention;
fig. 3 is a schematic structural view of an ejection cabin in embodiment 2 of the invention;
fig. 4 schematically shows a structural view of a portion a in fig. 3;
wherein the figures include the following reference numerals:
1-fuselage, 2-fixed wing, 3-rotor wing, 31-support frame, 32-wing wheel and 4-empennage;
5-ejection cabin, 51-outer wall, 52-inner wall, 53-reinforcing net, 54-clamping ring, 55-heat dissipation fin, 56-movable plate, 57-bottom ring;
6-magnetic plate, 7-powder.
Detailed Description
It should be noted that the following detailed description is exemplary and is intended to provide further explanation of the disclosure; unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application; as used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
Moreover, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
For convenience of description, spatially relative terms such as "over 8230 \ 8230;," 'over 8230;, "\8230;,"' over 8230;, "above," etc. may be used herein to describe the spatial relationship of one device or feature to another device or feature as shown in the figures; it will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures.
Example 1
As shown in fig. 1 is a multimode take-off and landing unmanned aerial vehicle for plateau middle and low altitude supervision, not only can take off and land, lift by oneself by the roll, but also can use gunpowder as the power supply to launch and take off, and the user can select appropriate take-off and land mode according to the place circumstances to reach better result of use, its structure includes: fuselage 1, wing constitute, the wing includes: the fixed wing 2, the fin 4 are provided with rotor 3 on the fixed wing 2 to can realize the rolloff take off and land, lift by oneself.
As shown in fig. 1, the wing includes: the unmanned aerial vehicle comprises fixed wings 2, rotor wings 3 and an empennage 4, wherein the fixed wings 2 are arranged on two sides of a body 1, a control unit is arranged in the body 1 and used for controlling the movement of the unmanned aerial vehicle, the rotor wings 3 are arranged on the fixed wings 2, the rotor wings 3 are arranged on a straight rod, the straight rod is parallel to the axis of the body 1, a support frame 31 is further arranged on the downward side part of the straight rod, the height of the support frame 31 is higher than that of the body 1, so that the unmanned aerial vehicle can be stably placed on the ground, the straight rod is at least provided with two rotor wings 3, the rotor wings 3 are in circuit connection with the control unit in the body 1 and move under the control of the control unit, and the empennage 4 is connected to the tail part of the straight rod to ensure the stability in the movement process; of course, the empennage 4, the rotor 3, the fixed wing 2 and the control unit in the fuselage 1 are mature prior art, and users can flexibly purchase the empennage, the rotor, the fixed wing and the control unit according to actual needs.
Example 2
The present embodiment differs from the previous embodiment in that: the tail of the machine body 1 is provided with an ejection bin 5, the gunpowder 7 in the ejection bin 5 is ignited to eject the unmanned aerial vehicle by using the impact force of the gunpowder 7 when the ejection bin 5 is used, in order to reduce the damage of gunpowder explosion to the ejection bin 5, a movable plate 56 is arranged in the ejection bin 5, when the ejection bin 5 is impacted, the movable plate 56 moves to the other side to extrude the medium on one side of the movable plate 56, and the impact force of the gunpowder to the ejection bin 5 is buffered by compressing the medium.
As shown in fig. 2, the wing wheels 32 are provided at the bottom of the support frame 31, and the wing wheels 32 can rotate when receiving a thrust, and the wing wheels 32 have the same size, so that the body 1 can be stably placed on the ground and can move.
As shown in fig. 4, the ejection bin 5 is an open cylinder, and has a double-layer structure, the outer layer is an outer wall 51, the inner layer is an inner wall 52, a certain gap is left between the outer wall 51 and the inner wall 52, a reinforcing mesh 53 is arranged in the gap, the reinforcing mesh 53 is a mesh structure formed by interweaving metal strips, the reinforcing mesh 53 is fixed on the outer side of the inner wall 52 to play a role similar to a reinforcing rib, the thickness of the reinforcing mesh 53 is smaller than the width of the gap between the outer wall 51 of the inner wall 52, the edge of the open end of the ejection bin is provided with a bottom ring 57, the bottom ring 57 seals the gap between the inner wall 52 and the outer wall 51, and the bottom ring 57 is a magnetic ring and can attract the magnetic plate 6 to be fixed on the magnetic plate 6 when in use; as shown in fig. 3, a movable plate 56 is further disposed in the inner wall 52, the movable plate 56 and the inner wall 52 have the same cross-sectional shape, and can move in the inner wall 52 along the axial direction of the ejection chamber, the movable plate 56 divides the space of the inner wall 52 into two parts, one part is a closed space near the closed end, the other part is an open end, a certain amount of water is disposed in the closed part, the height of the water is 1/3 of the height of the closed part when no pressure is applied, the rest part is air, when pressure is applied, the air is partially dissolved in the water, the other part is compressed, so that the impact force is absorbed by the two media, and the two media recover to the original shape after the pressure disappears.
Furthermore, a tightening ring 54 is further provided on the outer side of the outer wall 51, the tightening ring 54 is a metal ring band made of the same material as the reinforcing mesh 53, and the tightening ring 54 is fixed on the outer side of the outer wall 51 and absorbs part of the pressure when the pressure is applied.
More closely, a plurality of heat dissipation fins 55 are arranged on the outer side surface of the outer wall 51, the heat dissipation fins 55 are inclined metal sheets, so that the heat conductivity is good, the powder explosion is a heat release process, a large amount of heat can be generated besides a large pressure, heat dissipation needs to be performed in time, the heat dissipation fins 55 can utilize airflow generated in the flight process to cool down in the flight process of the unmanned aerial vehicle, specifically, a part of heat generated by explosion is absorbed by the inner wall 52 after the ejection cabin 5 is ejected and takes off, the other part of heat is directly dissipated in the air, the heat absorbed by the inner wall 52 is conducted outwards, the outer wall 51 and the heat dissipation fins 55 are heated, and as the contact area between the heat dissipation fins 55 and the outside air is large, in addition, the ejection cabin 5 is located at the tail part in the use process, the airflow flowing along the body 1 can blow over the surfaces of the heat dissipation fins 55, so that the heat dissipation is accelerated, and the damage of the explosion heat to the ejection cabin 5 is reduced.
The unmanned aerial vehicle stated in this embodiment need assist through the ejector rack when carrying out catapult takeoff, the ejector rack is prior art, just is a slide that a section is smooth to raise, and unmanned aerial vehicle is in the lower position of slide, through power unit upward movement, realizes the slip takeoff, the ejector rack in this embodiment is provided with a magnetic sheet 6 at the end of the slide minimum of prior art, and other structures are the same with prior art, magnetic sheet 6 is a flat board that has magnetism, and when using, unmanned aerial vehicle's ejection storehouse 5 can be fixed on magnetic sheet 6 with the help of magnetism, forms a confined space, after the thickness of magnetic sheet 6 is greater than the thickness of outer wall 51 and inner wall 52, can bear the impact of gunpowder 7 explosion.
The catapult-assisted take-off process is described with reference to fig. 3:
firstly, a small amount of gunpowder 7 is fixed on a magnetic plate 6, the specific type of the gunpowder can be purchased according to actual needs, and the dosage of the gunpowder 7 can be obtained through calculation, the embodiment is not described in detail, an unmanned aerial vehicle is placed on a catapult frame, a catapult bin 5 at the tail of the unmanned aerial vehicle is adsorbed on the magnetic plate 6, the gunpowder 7 on the magnetic plate 6 is covered, then the gunpowder 7 is ignited, the gunpowder 7 explodes to generate huge pressure and release heat, the pressure in the catapult bin is rapidly increased, the unmanned aerial vehicle is catapulted out, meanwhile, the pressure generated by explosion can enable a movable plate 56 in the catapult bin 5 to move towards a closed end, media in the catapult bin are compressed, and part of impact force is absorbed through the media; the impact force of the explosion of the gunpowder 7 also acts on the inner wall 52, is absorbed by the reinforcing mesh 53 and the hooping ring 54, and reduces the damage of the inner wall 52 and the outer wall 51 caused by the impact force, and the heat generated by the explosion is conducted to the surfaces of the heat dissipation fins 55 through the inner wall 52 and dissipated through the heat dissipation fins 55, so that the damage of the gunpowder 7 to the ejection chamber 5 is reduced.
As a preferred embodiment, the reinforcing net is made of high-carbon steel, has higher strength, can bear higher impact force and has a better protection effect.
In this embodiment, the fuselage, the control unit, the fixed wing, the rotor wing, and the tail wing are mature technologies in the prior art, and users can flexibly choose and purchase according to actual situations, and therefore, detailed descriptions are omitted.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (5)
1. A multimode take-off and landing unmanned aerial vehicle for plateau middle and low altitude supervision comprises: fuselage, wing, fin, jettison device, during the use, unmanned aerial vehicle places on the slide of launching cradle, and the thrust that produces through jettison device takes off from the launching cradle, its characterized in that: the wing includes: the unmanned aerial vehicle comprises fixed wings, rotor wings and an empennage, wherein the fixed wings are arranged on two sides of a fuselage, a control unit is arranged in the fuselage and used for controlling the movement of the unmanned aerial vehicle, the rotor wings are arranged on the fixed wings, the rotor wings are arranged on a straight rod, the straight rod is parallel to the axis of the fuselage, a support frame is further arranged at the part, facing downwards, of the side face of the straight rod, the height of the support frame is higher than that of the fuselage, the straight rod is at least provided with two rotor wings, and wing wheels are arranged at the bottom of the support frame;
the ejection device is ejection storehouse, and ejection storehouse sets up at the fuselage afterbody, the shell in ejection storehouse is open cylinder, and is bilayer structure, promptly: the ejection cabin comprises an outer wall and an inner wall, wherein a certain gap is reserved between the outer wall and the inner wall, a reinforcing net is arranged in the gap, the reinforcing net is of a net structure formed by interweaving metal strips, the reinforcing net is fixed on the outer side of the inner wall, a bottom ring is arranged at the edge of an open end of the ejection cabin, the bottom ring is a magnetic ring, a movable plate is further arranged in the inner wall, the movable plate and the inner wall are the same in cross-sectional shape and can move in the inner wall along the vertical direction, the movable plate divides the space of the inner wall into two parts, one part is a closed space close to the closed end, the other part is located at the open end, and a medium is filled in the closed space;
the tail end of the lowest point of the ejection rack slideway is provided with a magnetic plate, the magnetic plate is a magnetic flat plate, a small amount of gunpowder can be fixed by the magnetic plate when the magnetic plate is used, the ejection bin covers the gunpowder on the magnetic plate by using magnetic force, and ejection take-off is carried out by using thrust generated by gunpowder explosion.
2. The multimode take-off and landing unmanned aerial vehicle for plateau middle and low altitude surveillance as claimed in claim 1, wherein: the thickness of the reinforcing net is smaller than the width of a gap between the inner wall and the outer wall.
3. The multimode take-off and landing unmanned aerial vehicle for plateau middle and low altitude surveillance as claimed in claim 1, characterized in that: the medium is water and air, the height of the water is 1/3 of the height of the closed part when the closed part is not pressurized, and the rest part of the closed part is air.
4. The multimode take-off and landing unmanned aerial vehicle for plateau middle and low altitude surveillance as claimed in claim 1, characterized in that: the outer side of the outer wall is also provided with a clamping ring which is fixed on the outer side of the outer wall.
5. The multimode take-off and landing unmanned aerial vehicle for plateau middle and low altitude surveillance as claimed in claim 1, characterized in that: and a plurality of radiating fins are arranged on the outer side surface of the outer wall, and the radiating fins are inclined metal sheets.
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| CN111516867A (en) * | 2020-05-13 | 2020-08-11 | 陈厚然 | Multi-power-mode fixed-wing aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB579968A (en) * | 1941-01-20 | 1946-08-22 | Charles Dennistoun Burney | Improvements in or relating to the launching and landing of aeroplanes or seaplanes |
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