CN110901892B - Laser vertical fixed wing unmanned aerial vehicle with low-speed high lift-drag ratio layout - Google Patents
Laser vertical fixed wing unmanned aerial vehicle with low-speed high lift-drag ratio layout Download PDFInfo
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- CN110901892B CN110901892B CN201911234652.0A CN201911234652A CN110901892B CN 110901892 B CN110901892 B CN 110901892B CN 201911234652 A CN201911234652 A CN 201911234652A CN 110901892 B CN110901892 B CN 110901892B
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- 230000009467 reduction Effects 0.000 claims description 18
- 239000003638 chemical reducing agent Substances 0.000 abstract description 4
- 238000000034 method Methods 0.000 description 5
- 230000009471 action Effects 0.000 description 3
- 230000008569 process Effects 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- 208000035473 Communicable disease Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/10—Stabilising surfaces adjustable
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/38—Constructions adapted to reduce effects of aerodynamic or other external heating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
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Abstract
The invention discloses a laser vertical fixed wing unmanned aerial vehicle with low-speed high lift-drag ratio layout, which comprises a fuselage, wherein wings are arranged on two sides of the fuselage, connecting rods are arranged on the wings, front driving spiral fans and rear driving spiral fans are respectively arranged on two sides of the connecting rods, a drag reducer is arranged at the tail end of each connecting rod, the drag reducer comprises a sliding tail wing and a tail wing, one ends of the sliding tail wing and the tail wing are respectively arranged on the connecting rods of the wings, and the other ends of the sliding tail wing and the tail wing are in sliding connection on the tail wing.
Description
Technical Field
The embodiment of the invention relates to the technical field of unmanned aerial vehicle equipment, in particular to a laser vertical fixed wing unmanned aerial vehicle with low-speed and high lift-drag ratio layout.
Background
Unmanned aircraft, for short, "unmanned aircraft," is unmanned aircraft that is maneuvered using a radio remote control device and a self-contained programming device, or is operated autonomously, either entirely or intermittently, by an on-board computer. Unmanned aerial vehicles can be classified into military and civilian applications according to the field of application. In civil aspects, the application in the fields of aerial photography, agriculture, plant protection, miniature self-timer shooting, express delivery transportation, disaster relief, wild animal observation, infectious disease monitoring, mapping, news report, electric power inspection, disaster relief, film and television shooting, romantic manufacturing and the like is greatly expanded, the application of the unmanned aerial vehicle is greatly expanded, the laser hanging fixed wing unmanned aerial vehicle is one type of various unmanned aerial vehicles, the lifting force and the resistance of the laser hanging fixed wing unmanned aerial vehicle are influenced during flight, and the important parameters for determining the aerodynamic efficiency of an airplane are also realized, but the lift-drag ratio of the existing laser hanging fixed wing unmanned aerial vehicle is lower, and the use of the unmanned aerial vehicle is influenced.
Disclosure of Invention
The invention provides a laser vertical-up fixed wing unmanned aerial vehicle with low-speed high lift-drag ratio layout, which aims to solve the defects in the prior art.
In order to achieve the above object, the present invention provides the following technical solutions:
the utility model provides a laser of low-speed high lift-drag ratio overall arrangement hangs up fixed wing unmanned aerial vehicle, includes the fuselage, the fuselage both sides are equipped with the wing, install the connecting rod on the wing, and the connecting rod is located the both sides of wing and installs front drive helical fan and back drive helical fan respectively, the drag reduction ware is installed to the tail end of connecting rod, drag reduction ware includes slide fin and fin, slide fin and fin's one end is installed respectively on the connecting rod of wing, slide fin's the other end sliding connection is on the fin, slide fin is connected with the slider with fin one end that contacts, one side surface of fin is equipped with two sets of slide rails that are parallel to each other, and slider sliding connection is in the slide rail, slide fin and fin's surface is equipped with the fan, the fuselage is located the fin both sides and is equipped with drag reduction flank, the lateral wall of drag reduction flank adopts the circular arc, and drag reduction flank inner wall side has seted up the runner, and runner parallel arrangement multiunit.
Preferably, the outer wall of the tail fin is provided with a groove, a fixed pipe is arranged in the center of the groove, and the fan blade is rotationally connected to the fixed pipe.
Preferably, the mounting mode of the fan blade on the sliding tail fin is the same as that of the tail fin.
Preferably, the tail ends of the sliding tail wing and the tail wing are connected with connecting rings, and the connecting rings are sleeved on the connecting rods.
Preferably, the connecting rod comprises a connecting front rod, a connecting tail rod and a main rod, wherein two ends of the main rod are respectively connected with the connecting front rod and the connecting tail rod, and a steering shaft is arranged at the joint of the main rod and the connecting front rod and the connecting tail rod.
Preferably, the main rod is welded on the bottom surface of the wing.
Preferably, the front driving spiral fan is arranged on the front connecting rod through a fixing frame, and the rear driving spiral fan is arranged on the tail connecting rod through a fixing frame.
Preferably, the front end thickness of the wing is lower than the rear end thickness and differs by 3CM.
The invention provides a laser vertical-movement fixed wing unmanned aerial vehicle with low-speed and high lift-drag ratio layout, which has the following beneficial effects:
(1) According to the invention, the drag reducer consisting of the sliding tail wing and the tail wing is arranged on the rear side of the unmanned aerial vehicle, one ends of the sliding tail wing and the tail wing are arranged on the connecting rod, the other ends of the sliding tail wing and the tail wing are connected and are in sliding connection, when the unmanned aerial vehicle flies, the included angle between the sliding tail wing and the tail wing can be automatically changed under the action of wind speed, so that the rising resistance is reduced, and the rotatable fan blades are arranged on the surfaces of the sliding tail wing and the tail wing, and the wind power is utilized to drive the fan blades to rotate rapidly, so that the lifting force of the unmanned aerial vehicle is improved, and the rising resistance ratio is improved.
(2) According to the invention, the drag reduction side wings are arranged on two sides of the tail of the fuselage, the outer walls of the drag reduction side wings are provided with the arc convex edges, the smooth appearance can reduce wind resistance, and the inner walls are provided with the plurality of groups of flow channels, so that when flying, the width of the air channel is increased when wind passes through, and the resistance is reduced.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions of the prior art, the drawings which are used in the description of the embodiments or the prior art will be briefly described, it being obvious that the drawings in the description below are only some embodiments of the invention, and that other drawings can be obtained from these drawings without inventive faculty for a person skilled in the art.
FIG. 1 is a top view of the present invention;
FIG. 2 is a schematic diagram of a resistor-reducing device according to the present invention;
FIG. 3 is a schematic view of the front structure of the tail wing of the present invention;
FIG. 4 is a schematic view of the reverse side structure of the tail wing of the present invention;
FIG. 5 is a schematic view of a slide tail structure according to the present invention;
FIG. 6 is a schematic representation of the drag reducing wing structure of the present invention;
fig. 7 is a schematic view of a wing fold structure of the present invention.
In the figure: 1. a body; 2. front driving spiral fan; 3. a connecting rod; 4. a wing; 5. rear driving the spiral fan; 6. a drag reducing flank; 7. a connecting ring; 8. a slide tail; 9. a tail wing; 10. a resistor-reducing device; 11. a groove; 12. a fixed tube; 13. a fan blade; 14. a slide block; 15. a slide rail; 16. an arc convex edge; 17. a flow passage; 18. a steering shaft; 19. connecting a front rod; 20. connecting tail rods; 21. and (3) a main rod.
Detailed Description
In order to make the objects, features and advantages of the present invention more obvious and understandable, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is apparent that the embodiments described below are only some embodiments of the present invention, not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it will be understood that when one component is referred to as being "connected" to another component, it can be directly connected to the other component or intervening components may also be present. When an element is referred to as being "disposed on" another element, it can be directly on the other element or intervening elements may also be present.
Furthermore, the terms "long," "short," "inner," "outer," and the like, as used herein, refer to an orientation or positional relationship based on that shown in the drawings, for convenience of description of the present invention, and are not intended to indicate or imply that the apparatus or elements referred to must have this particular orientation, operate in a particular orientation configuration, and thus should not be construed as limiting the invention.
The technical scheme of the invention is further described below by the specific embodiments with reference to the accompanying drawings.
Example 1
As shown in fig. 1-7, the present invention provides a technical solution: the utility model provides a laser of low-speed high lift-drag ratio overall arrangement hangs up fixed wing unmanned aerial vehicle, includes fuselage 1, fuselage 1 both sides are equipped with wing 4, install connecting rod 3 on the wing 4, and connecting rod 3 is located the both sides of wing 4 and installs respectively front drive helical fan 2 and back drive helical fan 5, drag reduction ware 10 is installed to the tail end of connecting rod 3, drag reduction ware 10 includes slide fin 8 and fin 9, slide fin 8 and fin 9's one end is installed respectively on wing 4's connecting rod 3, slide fin 8's the other end sliding connection is on fin 9, slide fin 8 and fin 9 contact's one end is connected with slider 14, fin 9's one side surface is equipped with two sets of slide rail 15 that are parallel to each other, and slider 14 sliding connection is in slide rail 15, slide fin 8 and fin 9's surface is equipped with fan 13, fuselage 1 is located the fin both sides and is equipped with drag reduction flank 6, drag reduction flank 6's lateral wall adopts circular arc chiffon side 17, and runner 17 parallel arrangement multiunit.
The outer wall of the tail wing 9 is provided with a groove 11, a fixed pipe 12 is arranged in the center of the groove 11, the fan 13 is rotationally connected to the fixed pipe 12, the installation mode of the fan 13 on the sliding tail wing 8 is the same as that of the tail wing 9, the fan 13 is driven to rotate rapidly by wind speed, and the rotating fan 13 can generate power to increase lift force; the tail ends of the sliding tail wing 8 and the tail wing 9 are connected with a connecting ring 7, the connecting ring 7 is sleeved on the connecting rod 3, and the connecting ring 7 is sleeved on the connecting rod 3, so that later disassembly is facilitated; the connecting rod 3 comprises a connecting front rod 19, a connecting tail rod 20 and a main rod 21, wherein two ends of the main rod 21 are respectively connected with the connecting front rod 19 and the connecting tail rod 20, a steering shaft 18 is arranged at the joint of the main rod 21 and the connecting front rod 19 and the connecting tail rod 20, and the connecting front rod 19 and the connecting tail rod 20 can be folded to be perpendicular to the main rod 21 or unfolded on a straight line; the main rod 21 is welded on the bottom surface of the wing 4, so that the front driving spiral fan 2 and the rear driving spiral fan 5 are conveniently contained on the bottom surface of the wing 4; the front driving spiral fan 2 is arranged on the connecting front rod 19 through a fixing frame, and the rear driving spiral fan 5 is arranged on the connecting tail rod 20 through a fixing frame, so that the front driving spiral fan 2 and the rear driving spiral fan 5 are respectively positioned on the front side and the rear side of the machine body 1; the front end thickness of the wing 4 is lower than the rear end thickness and the difference is 3CM, and the arrangement that the front end is thin and the rear end is thick is adopted, so that the wing is more convenient to pass in wind, and the resistance is reduced.
It should be noted that, in the laser vertical-lift fixed wing unmanned aerial vehicle with low-speed and high lift-drag ratio layout, since the sliding tail 8 and the tail 9 in the drag reducer 10 are inclined to a certain angle, and one end of the sliding tail 8 is slidably connected to the sliding rail 15 of the tail 9 by the slide block 14, so that the sliding tail 8 and one end of the tail 9 are slidably connected, when the unmanned aerial vehicle works, the angle formed between the sliding tail 8 and the tail 9 is adaptively changed under the action of wind speed so as to reduce the lifting resistance, when the unmanned aerial vehicle flies, the fan 13 rotationally connected with the grooves 11 on the surfaces of the sliding tail 8 and the tail 9 rotates rapidly under the blowing of wind, so as to provide lift force for the unmanned aerial vehicle, thereby increasing the lift-drag ratio, and reducing the obstruction when the wind passes through the surfaces of the sliding tail 8 and the tail 9, thereby facilitating the flying of the unmanned aerial vehicle, when wind passes through the drag reduction side wings 6 on two sides of the tail end of the machine body 1, as the outer walls of the drag reduction side wings 6 are provided with the arc convex edges 16, the smooth appearance can reduce wind resistance, and the inner walls of the drag reduction side wings 6 are provided with a plurality of groups of flow passages 17, when wind passes through, the width of the wind passage is increased, so that resistance is reduced, wherein the front driving spiral fan 2 and the rear driving spiral fan 5 are arranged on the detachable folding connecting rod 3, when the wind needs to be stored, under the action of the steering shaft 18, the front connecting rod 19 and the rear connecting spiral fan 20 provided with the front driving spiral fan 2 and the rear driving spiral fan 5 are folded to an angle perpendicular to the main rod 21, so that the front driving spiral fan 2 and the rear driving spiral fan 5 can be stored under the wing 4, and when the wind passes through, the front connecting rod 19, the rear connecting tail rod 20 and the main rod 21 are rotated to a straight line, and the wind resistance reducing machine is convenient and simple.
The description of the foregoing embodiments has been provided for the purposes of illustration and description. It is not intended to be exhaustive or to limit the disclosure. Individual elements or features of a particular embodiment are generally not limited to the particular embodiment, but, where applicable, may be interchanged and used with the selected embodiment even if not specifically shown or described. The same elements or features may also be varied in many ways. Such variations are not to be regarded as a departure from the disclosure, and all such modifications are intended to be included within the scope of the disclosure.
Example embodiments are provided so that this disclosure will be thorough, and will fully convey the scope to those skilled in the art. Numerous details are set forth, such as examples of specific parts, devices, and methods, in order to provide a thorough understanding of embodiments of the present disclosure. It will be apparent to one skilled in the art that the exemplary embodiments may be embodied in many different forms without the use of specific details, and neither should be construed to limit the scope of the disclosure. In certain example embodiments, well-known processes, well-known device structures, and well-known techniques are not described in detail.
The terminology used herein is for the purpose of describing particular example embodiments only and is not intended to be limiting. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. The terms "comprises" and "comprising" are inclusive and, therefore, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. The method steps, processes, and operations described herein are not to be construed as necessarily requiring their performance in the particular order discussed and illustrated, unless specifically indicated. It should also be appreciated that additional or alternative steps may be employed.
When an element or layer is referred to as being "on," "engaged with," "connected to" or "coupled to" another element or layer, it can be directly on, engaged with, connected to or coupled to the other element or layer, or intervening elements or layers may also be present. In contrast, when an element or layer is referred to as being "directly on" … …, "" directly engaged with "… …," "directly connected to" or "directly coupled to" another element or layer, there may be no intervening elements or layers present. Other words used to describe the relationship of elements should be interpreted in a similar manner (e.g., "between … …" and "directly between … …", "adjacent" and "directly adjacent", etc.). The term "and/or" as used herein includes any and all combinations of one or more of the associated listed items. Although the terms first, second, third, etc. may be used herein to describe various elements, components, regions, layers and/or sections, these elements, components, regions, layers and/or sections should not be limited by these terms. These terms may be only used to distinguish one element, component, region or section from another element, component, region or section. Unless clearly indicated by the context, terms such as the terms "first," "second," and other numerical values are used herein to not imply a sequence or order. Accordingly, a first element, component, region, layer or section discussed below could be termed a second element, component, region, layer or section without departing from the teachings of the example embodiments.
Spatially relative terms, such as "inner," "outer," "below," "beneath," "lower," "above," "upper" and the like, may be used herein for ease of description to describe one element or feature's relationship to another element or feature's illustrated in the figures. Spatially relative terms may be intended to encompass different orientations of the device in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "below" or "beneath" other elements or features would then be oriented "above" the other elements or features. Thus, the example term "below" … … can encompass both upward and downward orientations. The device may be otherwise oriented (rotated 90 degrees or otherwise) and interpreted in the relative description of the space herein.
Claims (6)
1. The utility model provides a laser of low-speed high lift-to-drag ratio overall arrangement hangs up fixed wing unmanned aerial vehicle, includes fuselage (1), its characterized in that: the utility model provides a drag reduction device, including fuselage (1), wing (4) are equipped with on fuselage (1), install connecting rod (3) on wing (4), and connecting rod (3) are located the both sides of wing (4) and install front drive spiral fan (2) and back drive spiral fan (5) respectively, drag reduction ware (10) are installed to the tail end of connecting rod (3), drag reduction ware (10) are including slide fin (8) and fin (9), the one end of slide fin (8) and fin (9) is installed respectively on connecting rod (3) of wing (4), the other end sliding connection of slide fin (8) is on fin (9), slide fin (8) are connected with slider (14) with the one end that fin (9) contacted, one side surface of fin (9) is equipped with slide rail (15) that two sets of are parallel to each other, and slider (14) sliding connection is in slide rail (15), slide fin (8) and fin (9) all are equipped with fin (13), fuselage (1) is located the tail both sides and is equipped with drag reduction (6), the inner wall (16) of flank (6) are adopted and side (6) are offered to the side of flank (17), and the flow channels (17) are provided with a plurality of groups in parallel;
the outer wall of the tail wing (9) is provided with a groove (11), a fixed pipe (12) is arranged in the center of the groove (11), and the fan blade (13) is rotationally connected to the fixed pipe (12);
the connecting rod (3) comprises a connecting front rod (19), a connecting tail rod (20) and a main rod (21), wherein two ends of the main rod (21) are respectively connected with the connecting front rod (19) and the connecting tail rod (20), and a steering shaft (18) is arranged at the joint of the main rod (21) and the connecting front rod (19) and the connecting tail rod (20).
2. The laser lift-off fixed wing unmanned aerial vehicle with low-speed and high lift-to-drag ratio layout according to claim 1, wherein: the fan blade (13) on the sliding tail wing (8) is installed in the same mode as the tail wing (9).
3. The laser lift-off fixed wing unmanned aerial vehicle with low-speed and high lift-to-drag ratio layout according to claim 1, wherein: the tail ends of the sliding tail wing (8) and the tail wing (9) are connected with a connecting ring (7), and the connecting ring (7) is sleeved on the connecting rod (3).
4. The laser lift-off fixed wing unmanned aerial vehicle with low-speed and high lift-to-drag ratio layout according to claim 1, wherein: the main rod (21) is welded on the bottom surface of the wing (4).
5. The laser lift-off fixed wing unmanned aerial vehicle with low-speed and high lift-to-drag ratio layout according to claim 1, wherein: the front driving spiral fan (2) is arranged on the connecting front rod (19) through a fixing frame, and the rear driving spiral fan (5) is arranged on the connecting tail rod (20) through a fixing frame.
6. The laser lift-off fixed wing unmanned aerial vehicle with low-speed and high lift-to-drag ratio layout according to claim 1, wherein: the front end thickness of the wing (4) is lower than the rear end thickness and differs by 3CM.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911234652.0A CN110901892B (en) | 2019-12-05 | 2019-12-05 | Laser vertical fixed wing unmanned aerial vehicle with low-speed high lift-drag ratio layout |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911234652.0A CN110901892B (en) | 2019-12-05 | 2019-12-05 | Laser vertical fixed wing unmanned aerial vehicle with low-speed high lift-drag ratio layout |
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| Publication Number | Publication Date |
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| CN110901892A CN110901892A (en) | 2020-03-24 |
| CN110901892B true CN110901892B (en) | 2024-03-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911234652.0A Active CN110901892B (en) | 2019-12-05 | 2019-12-05 | Laser vertical fixed wing unmanned aerial vehicle with low-speed high lift-drag ratio layout |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5415365A (en) * | 1993-11-08 | 1995-05-16 | Ratliff; Paul D. | High performance amphibious aircraft |
| CA2235309A1 (en) * | 1998-04-20 | 1999-10-20 | Anant Grewal | Active noise and vibration control, especially in aircraft |
| CN205633042U (en) * | 2016-05-06 | 2016-10-12 | 北京京东尚科信息技术有限公司 | Unmanned aerial vehicle |
| CN106741820A (en) * | 2016-12-20 | 2017-05-31 | 中国科学院长春光学精密机械与物理研究所 | A kind of VTOL fixed-wing unmanned vehicle |
| CN107972869A (en) * | 2017-11-29 | 2018-05-01 | 北京航空航天大学 | A kind of across water sky medium unmanned vehicle of variable configuration binary |
| CN110466750A (en) * | 2019-08-19 | 2019-11-19 | 西北工业大学 | A kind of Portable vertical landing scouting monitoring unmanned plane |
| CN211391661U (en) * | 2019-12-05 | 2020-09-01 | 广东电网有限责任公司 | Laser of low-speed high lift-drag ratio overall arrangement hangs down fixed wing unmanned aerial vehicle |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8757537B2 (en) * | 2005-11-02 | 2014-06-24 | The Boeing Company | Systems and methods for rotor/wing aircraft |
-
2019
- 2019-12-05 CN CN201911234652.0A patent/CN110901892B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5415365A (en) * | 1993-11-08 | 1995-05-16 | Ratliff; Paul D. | High performance amphibious aircraft |
| CA2235309A1 (en) * | 1998-04-20 | 1999-10-20 | Anant Grewal | Active noise and vibration control, especially in aircraft |
| CN205633042U (en) * | 2016-05-06 | 2016-10-12 | 北京京东尚科信息技术有限公司 | Unmanned aerial vehicle |
| CN106741820A (en) * | 2016-12-20 | 2017-05-31 | 中国科学院长春光学精密机械与物理研究所 | A kind of VTOL fixed-wing unmanned vehicle |
| CN107972869A (en) * | 2017-11-29 | 2018-05-01 | 北京航空航天大学 | A kind of across water sky medium unmanned vehicle of variable configuration binary |
| CN110466750A (en) * | 2019-08-19 | 2019-11-19 | 西北工业大学 | A kind of Portable vertical landing scouting monitoring unmanned plane |
| CN211391661U (en) * | 2019-12-05 | 2020-09-01 | 广东电网有限责任公司 | Laser of low-speed high lift-drag ratio overall arrangement hangs down fixed wing unmanned aerial vehicle |
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| CN110901892A (en) | 2020-03-24 |
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