CN111301078B - Carrying platform of combined type fixed wing unmanned aerial vehicle and operation method thereof - Google Patents
Carrying platform of combined type fixed wing unmanned aerial vehicle and operation method thereof Download PDFInfo
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- CN111301078B CN111301078B CN201911267879.5A CN201911267879A CN111301078B CN 111301078 B CN111301078 B CN 111301078B CN 201911267879 A CN201911267879 A CN 201911267879A CN 111301078 B CN111301078 B CN 111301078B
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- 230000007246 mechanism Effects 0.000 claims abstract description 26
- 238000003825 pressing Methods 0.000 claims abstract description 20
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 17
- 239000002131 composite material Substances 0.000 claims description 6
- 230000009471 action Effects 0.000 description 5
- 230000006872 improvement Effects 0.000 description 4
- 238000013507 mapping Methods 0.000 description 2
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
- B60F3/00—Amphibious vehicles, i.e. vehicles capable of travelling both on land and on water; Land vehicles capable of travelling under water
- B60F3/0061—Amphibious vehicles specially adapted for particular purposes or of a particular type
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
- B60F3/00—Amphibious vehicles, i.e. vehicles capable of travelling both on land and on water; Land vehicles capable of travelling under water
- B60F3/0007—Arrangement of propulsion or steering means on amphibious vehicles
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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
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Abstract
The invention discloses a carrying platform of a combined type fixed wing unmanned aerial vehicle and an operation method thereof, wherein the carrying platform comprises a chassis, a bearing platform is arranged above the chassis through an upper and lower adjusting mechanism, an air bag is arranged between the chassis and the bearing platform, a first power mechanism provides power for a driving wheel, and a second power mechanism drives blades to rotate; the left side and the right side above the bearing table are symmetrically provided with a left limiting structure and a right limiting structure; the first cylinder is installed on the right side of the upper end face of the bearing table through bolts, the upper end of a piston rod of the first cylinder is welded with the middle of the lower end face of the rectangular transverse plate, the second cylinder is installed in the middle of the top of the rectangular transverse plate through bolts, the left end of a piston rod of the second cylinder is welded with the right side wall of the rectangular vertical plate, and the bottom of the rectangular vertical plate is welded with the middle of the upper end face of the pressing plate. According to the invention, the wings of the unmanned aerial vehicle are limited by the two pressing plates, so that the limiting effect is good; the invention can be used on land or in water, and has strong adaptability.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicle carrying platforms, and particularly relates to a carrying platform of a combined type fixed wing unmanned aerial vehicle and an operation method of the carrying platform.
Background
Drones tend to be more suitable for tasks that are too "fool, dirty, or dangerous" than manned aircraft. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle + industry is applied, and is really just needed by the unmanned aerial vehicle. At present, the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand industrial application and develop unmanned aerial vehicle technology.
Categorised according to the usage, unmanned aerial vehicle can be divided into for military use unmanned aerial vehicle and civilian unmanned aerial vehicle. Military unmanned aerial vehicles can be divided into reconnaissance unmanned aerial vehicles, decoy unmanned aerial vehicles, electronic countermeasure unmanned aerial vehicles, communication relay unmanned aerial vehicles, unmanned fighters, target drone and the like; civilian unmanned aerial vehicles can be divided into patrol/watch on unmanned aerial vehicles, agricultural unmanned aerial vehicles, meteorological unmanned aerial vehicles, exploration unmanned aerial vehicles, surveying and mapping unmanned aerial vehicles, and the like. By scale classification (civil aviation regulations), unmanned aerial vehicles can be divided into micro unmanned aerial vehicles, light unmanned aerial vehicles, small unmanned aerial vehicles and large unmanned aerial vehicles. The micro unmanned aerial vehicle is an unmanned aerial vehicle with the mass of an air machine less than or equal to 7kg, the mass of a light unmanned aerial vehicle more than 7kg but less than or equal to 116kg, and the corrected airspeed is less than 100km/h (55nmile/h) and the lift limit is less than 3000m in full-horsepower flat flight. The small unmanned aerial vehicle is an unmanned aerial vehicle with the mass of the air aircraft less than or equal to 5700kg, except for micro and light unmanned aerial vehicles. Large-scale unmanned aerial vehicle is that the empty quick-witted quality is greater than 5700 kg.
When large-scale unmanned aerial vehicle in some now uses, need use the carrying platform, traditional carrying platform is difficult to accomplish land and water dual-purpose, is difficult to carry on spacingly to unmanned aerial vehicle's wing.
Disclosure of Invention
The invention aims to provide a carrying platform of a composite fixed wing unmanned aerial vehicle and an operation method thereof, so as to solve one or more technical problems. In the invention, the wings of the unmanned aerial vehicle are limited by the two pressing plates, so that the limiting effect is good; can be used on land and also can be used in water, and has strong adaptability.
In order to achieve the purpose, the invention adopts the following technical scheme:
the invention relates to a carrying platform of a composite fixed wing unmanned aerial vehicle, which comprises a chassis; further comprising:
the top of the base plate is provided with a bearing platform through an up-down adjusting mechanism, and an air bag is arranged between the base plate and the bearing platform;
one end of the bottom of the chassis is provided with a driving wheel, and the other end of the bottom of the chassis is provided with a driven wheel; the chassis is provided with a first power mechanism which is used for providing power for the driving wheel;
the chassis is provided with a paddle, the paddle and the driven wheel are positioned at the same end of the chassis, and the paddle is used for driving the carrying platform in water; the chassis is provided with a second power mechanism which is used for driving the blades to rotate;
two limiting structures are arranged on the bearing table; the two limiting structures are bilaterally symmetrical about the middle point of the bearing platform and are used for fixing the unmanned aerial vehicle;
wherein, every limit structure all includes: the air cylinder device comprises a first air cylinder and a second air cylinder, wherein the first air cylinder is vertically arranged, and the second air cylinder is horizontally arranged;
the fixed end of the first air cylinder is fixedly arranged on the bearing table, and a rectangular transverse plate is fixedly arranged at the piston rod end of the first air cylinder;
the fixed end fixed mounting of second cylinder is in on the rectangle diaphragm, the piston rod end fixed of second cylinder is provided with the rectangle riser, the bottom welding of rectangle riser has the clamp plate that is used for fixed unmanned aerial vehicle.
The invention has the further improvement that the top of the chassis is arranged in the bearing platform through an up-down adjusting mechanism, and the up-down adjusting mechanism comprises a plurality of connecting units; each of the connection units includes: a first threaded tube, a threaded rod and a second threaded tube; the upper end of the first threaded pipe is fixedly connected with the bearing table; the threaded rod is installed inside the first threaded pipe through threaded connection; the second threaded pipe is installed outside the threaded rod through threaded connection; the lower end of the second threaded pipe is fixedly connected to the chassis; the inner wall threads of the first threaded pipe and the second threaded pipe are arranged in an up-down symmetrical mode, and the first threaded pipe and the second threaded pipe can move towards the center of the threaded rod or move towards opposite directions by twisting the threaded rod.
The invention has the further improvement that each limit structure also comprises: the positioning plate and the first telescopic rod; the positioning plate is fixedly connected to the supporting plate; one end of the first telescopic rod is fixedly connected to the positioning plate, and the other end of the first telescopic rod is fixedly connected to the rectangular vertical plate.
The invention has the further improvement that each limit structure also comprises: a second telescopic tube; the second telescopic pipe is arranged between the bearing platform and the supporting plate.
A further development of the invention consists in that the first telescopic tube comprises: a first outer tube and a first inner rod; the first inner rod is movably inserted into the first outer pipe, one end of the first outer pipe, which is far away from the first inner pipe, is fixedly connected with the rectangular vertical plate, and one end of the first inner pipe, which is far away from the first outer pipe, is fixedly connected with the positioning plate;
the second extension tube comprises: a second outer tube and a second inner rod; the second inner rod is movably inserted into the second outer tube, the upper end of the second outer tube is fixedly connected with the supporting plate, and the lower end of the second inner rod is fixedly connected with the bearing table.
The invention has the further improvement that the bottom of the bearing platform and the top of the chassis are both provided with a clamping groove; the top and the bottom of the air bag are respectively inserted in the clamping groove.
The invention is further improved in that a first rubber layer is arranged on the inner wall of the clamping groove.
The invention is further improved in that the bottom of the pressure plate is provided with a second rubber layer.
The invention relates to an operation method of a carrying platform of a composite fixed wing unmanned aerial vehicle, which comprises the following steps:
the unmanned aerial vehicle lands on the middle part of the bearing platform;
the second air cylinder is started to push the rectangular vertical plate and the pressure plate to the center of the bearing table; the first air cylinder is started to drive the supporting plate, the second air cylinder and the pressing plate to move downwards, and the wings of the unmanned aerial vehicle are limited by the left pressing plate and the right pressing plate;
when the bearing platform is used in water, the bearing platform floats on the water surface through the air bag and is driven by the paddle;
when the land is used, the vehicle runs by driving wheels.
Compared with the prior art, the invention has the following beneficial effects:
the carrying platform disclosed by the invention has the advantages that the wings of the unmanned aerial vehicle are limited by the two pressing plates, the limiting effect is good, the carrying platform can be used on the land and in the water, and the carrying platform has strong adaptability. In the invention, due to the action of the air bag, the bearing platform can float on the water surface, so that the unmanned aerial vehicle can conveniently land on the bearing platform on the water surface. In the invention, the driving wheel is controlled to rotate by the first power mechanism to drive the bearing platform to move on the land, and the blades are driven to start by the second power mechanism, so that the bearing platform can move in water, can be used on the land and can also be used in the water, and has strong adaptability. According to the invention, the unmanned aerial vehicle is landed in the middle of the bearing platform, then the second air cylinder is controlled to be started, the rectangular vertical plate and the pressing plate are pushed to the center of the bearing platform, then the first air cylinder is started to drive the rectangular transverse plate, the second air cylinder, the rectangular vertical plate and the pressing plate to move downwards, the wings of the unmanned aerial vehicle are limited through the two pressing plates, and the limiting effect is good.
In the invention, the distance between the chassis and the bearing platform can be adjusted through the up-down adjusting mechanism, so that the chassis, the bearing platform and the air bag can be conveniently disassembled and assembled.
In the invention, the limiting of the air bag can be improved by arranging the clamping groove; the air bag can be protected by arranging the first rubber layer.
According to the invention, the first telescopic pipe can be arranged to reduce the shaking of the rectangular vertical plate when the rectangular vertical plate moves left and right, and the second telescopic pipe can be arranged to reduce the shaking of the supporting plate when the supporting plate moves up and down.
According to the invention, the second rubber layer is arranged, so that the protection of the wings of the unmanned aerial vehicle can be improved.
According to the operation method, the unmanned aerial vehicle is landed in the middle of the bearing table, the second air cylinder is controlled to be started, the rectangular vertical plate and the pressing plate are pushed to the center of the bearing table, then the first air cylinder is started to drive the rectangular transverse plate, the second air cylinder, the rectangular vertical plate and the pressing plate to move downwards, the wings of the unmanned aerial vehicle are limited through the two pressing plates, and the limiting effect is good.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art are briefly introduced below; it is obvious that the drawings in the following description are some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
Fig. 1 is a schematic cross-sectional structural view of a carrying platform of a composite fixed wing drone according to an embodiment of the present invention;
FIG. 2 is a schematic view of the construction of a first threaded tube, a threaded rod and a second threaded tube in an embodiment of the present invention;
FIG. 3 is a schematic structural view of a second telescopic tube according to an embodiment of the present invention;
in fig. 1 to 3: 1. a chassis; 2. a bearing table; 3. an air bag; 4. a driving wheel; 5. a driven wheel; 6. a first power mechanism; 7. a paddle; 8. a second power mechanism; 9. a first cylinder; 10. a rectangular transverse plate; 11. a second cylinder; 12. a rectangular vertical plate; 13. pressing a plate; 14. positioning a plate; 15. a first telescopic tube; 151. a first outer tube; 152. a first inner bar; 16. a second telescopic tube; 161. a second outer tube; 162. a second inner bar; 17. a first threaded pipe; 18. a threaded rod; 19. a second threaded pipe; 20. a rectangular clamping groove; 21. a first rubber layer; 22. a second rubber layer.
Detailed Description
In order to make the purpose, technical effect and technical solution of the embodiments of the present invention clearer, the following clearly and completely describes the technical solution of the embodiments of the present invention with reference to the drawings in the embodiments of the present invention; it is to be understood that the described embodiments are only some of the embodiments of the present invention. Other embodiments, which can be derived by one of ordinary skill in the art from the disclosed embodiments without inventive faculty, are intended to be within the scope of the invention.
Example 1
Referring to fig. 1 to 3, a composite fixed wing drone carrying platform according to an embodiment of the present invention includes: the device comprises a chassis 1, wherein a bearing platform 2 is arranged above the chassis 1 through an up-down adjusting mechanism.
From top to bottom adjustment mechanism includes in proper order: a first threaded tube 17, a threaded rod 18 and a second threaded tube 19; the upper end of the first threaded pipe 17 is welded with the lower end face of the bearing platform 2, the threaded rod 18 is installed inside the first threaded pipe 17 through threaded connection, the second threaded pipe 19 is installed outside the threaded rod 18 through threaded connection, the lower end of the second threaded pipe 19 is welded on the top of the base plate 1, the inner wall threads of the first threaded pipe 17 and the second threaded pipe 19 are arranged in an up-and-down symmetrical mode, the first threaded pipe 17 and the second threaded pipe 19 move towards the center of the threaded rod 18 by clockwise twisting the threaded rod 18, the threaded rod 18 is twisted anticlockwise, the first threaded pipe 17 and the second threaded pipe 19 move in opposite directions, the first threaded pipe 17 and the second threaded pipe 19 are separated from the threaded rod 18, the distance between the base plate 1 and the bearing platform 2 can be adjusted, and the base plate 1, the bearing platform 2 and the air bag 3 can be conveniently disassembled and assembled.
An air bag 3 is arranged between the chassis 1 and the bearing platform 2.
Preferably, in order to improve the limit of the air bag 3, rectangular clamping grooves 20 are integrally formed at the bottom of the bearing platform 2 and the top of the chassis 1, and the top and the bottom of the air bag 3 are respectively inserted into the upper rectangular clamping groove 20 and the lower rectangular clamping groove 20.
Preferably, in order to improve the protection of the airbag 3, a first rubber layer 21 is adhered to the inner wall of the rectangular slot 20.
All rotate around the left both sides in bottom of chassis 1 and install action wheel 4, all rotate around both sides on the bottom right side of chassis 1 and install from driving wheel 5, there is first power unit 6 in the left side of the up end of chassis 1 through support fixed mounting, first power unit 6 provides power to action wheel 4, the right side of the up end of chassis 1 rotates and installs paddle 7, there is second power unit 8 on the right side of the up end of chassis 1 through support fixed mounting, second power unit 8 drives paddle 7 and rotates.
The left side and the right side above the bearing table 2 are symmetrically provided with a left limiting structure and a right limiting structure;
the right limiting structure comprises a first air cylinder 9, the first air cylinder 9 is installed on the right side of the upper end face of the bearing platform 2 through a bolt, the upper end of a piston rod of the first air cylinder 9 is welded with the middle of the lower end face of the rectangular transverse plate 10, a second air cylinder 11 is installed in the middle of the top of the rectangular transverse plate 10 through a bolt, the left end of a piston rod of the second air cylinder 11 is welded with the right side wall of the rectangular vertical plate 12, and the bottom of the rectangular vertical plate 12 is welded with the middle of the upper end face of the pressing plate 13.
Preferably, the second rubber layer 22 is adhered to the bottom of the pressure plate 13, so that the protection of wings of the unmanned aerial vehicle is improved;
preferably, in order to reduce the shaking of the rectangular vertical plate 12 when moving left and right, a positioning plate 14 is welded on the right side of the upper end surface of the rectangular transverse plate 10, and a first telescopic pipe 15 is installed between the rectangular vertical plate 12 and the positioning plate 14.
Preferably, a second extension tube 16 is installed between the platform 2 and the rectangular cross plate 10 in order to reduce the shaking of the rectangular cross plate 10 during the vertical movement.
The first extension tube 15 comprises a first outer tube 151 and a first inner rod 152, the first inner rod 152 is movably inserted into the first outer tube 151, the left end of the first outer tube 151 is welded with the right side wall of the rectangular vertical plate 12, and the right end of the first inner rod 152 is welded with the left side wall of the positioning plate 14; the second extension tube 16 comprises a second outer tube 161 and a second inner rod 162, the second inner rod 162 is inserted into the second outer tube 161, the upper end of the second outer tube 161 is welded to the lower end face of the rectangular transverse plate 10, and the lower end of the second inner rod 162 is welded to the lower end face of the bearing table 2.
The working principle of the invention is as follows: descending unmanned aerial vehicle at the bus department of plummer 2, then controlling second cylinder 11 and starting, promoting rectangle riser 12 and clamp plate 13 to the center department of plummer 2, then starting first cylinder 9, driving rectangle diaphragm 10, second cylinder 11, rectangle riser 12, clamp plate 13 downstream, spacing effectual wing to unmanned aerial vehicle through two clamp plates 13.
In the invention, the bearing platform 2 can float on the water surface due to the action of the air bag 3, so that the unmanned aerial vehicle can conveniently land on the bearing platform 2 on the water surface.
Through the rotation of first power unit 6 control action wheel 4, drive plummer 2 and remove on the land, drive paddle 7 through second power unit 8 and start for plummer 2 can remove in aqueous, and paddle 7 is equipped with two, and another reversal of a corotation is controlled, makes things convenient for turning to of plummer 2, and first power unit 6, second power unit 8 adopt accessible remote control's mechanism, and this is prior art, no longer gives unnecessary details in this scheme.
Consequently, this scheme carries on spacingly through two clamp plates to unmanned aerial vehicle's wing, and is spacing effectual, can use on the land, also can use in aqueous, has extremely strong adaptability.
In conclusion, the invention discloses a carrying platform of a combined type fixed wing unmanned aerial vehicle, which comprises a chassis, wherein a bearing platform is arranged above the chassis through an upper and lower adjusting mechanism, an air bag is arranged between the chassis and the bearing platform, a first power mechanism provides power for a driving wheel, and a second power mechanism drives blades to rotate; the left side and the right side above the bearing table are symmetrically provided with a left limiting structure and a right limiting structure; the first cylinder is installed on the right side of the upper end face of the bearing table through bolts, the upper end of a piston rod of the first cylinder is welded with the middle of the lower end face of the rectangular transverse plate, the second cylinder is installed in the middle of the top of the rectangular transverse plate through bolts, the left end of a piston rod of the second cylinder is welded with the right side wall of the rectangular vertical plate, and the bottom of the rectangular vertical plate is welded with the middle of the upper end face of the pressing plate. According to the invention, the two pressure plates are used for limiting the wings of the unmanned aerial vehicle, so that the limiting effect is good, the unmanned aerial vehicle can be used on land or in water, and the unmanned aerial vehicle has strong adaptability.
Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art can make modifications and equivalents to the embodiments of the present invention without departing from the spirit and scope of the present invention, which is set forth in the claims of the present application.
Claims (5)
1. The utility model provides a platform is carried on to combined type fixed wing unmanned aerial vehicle, includes chassis (1), its characterized in that still includes:
a bearing platform (2) is arranged at the top of the chassis (1) through an up-down adjusting mechanism, and an air bag (3) is arranged between the chassis (1) and the bearing platform (2);
one end of the bottom of the chassis (1) is provided with a driving wheel (4), and the other end is provided with a driven wheel (5); the chassis (1) is provided with a first power mechanism (6), and the first power mechanism (6) is used for providing power for the driving wheel (4);
the chassis (1) is provided with a paddle (7), the paddle (7) and the driven wheel (5) are positioned at the same end of the chassis (1), and the paddle (7) is used for driving the carrying platform in water; the chassis (1) is provided with a second power mechanism (8), and the second power mechanism (8) is used for driving the blades (7) to rotate;
two limiting structures are arranged on the bearing table (2); the two limiting structures are bilaterally symmetrical about the midpoint of the bearing table (2) and are used for fixing the unmanned aerial vehicle;
wherein, every limit structure all includes: a first cylinder (9) arranged vertically and a second cylinder (11) arranged horizontally;
the fixed end of the first air cylinder (9) is fixedly arranged on the bearing table (2), and a rectangular transverse plate (10) is fixedly arranged at the piston rod end of the first air cylinder (9);
the fixed end of the second cylinder (11) is fixedly arranged on the rectangular transverse plate (10), a rectangular vertical plate (12) is fixedly arranged at the piston rod end of the second cylinder (11), and a pressing plate (13) for fixing the unmanned aerial vehicle is welded at the bottom of the rectangular vertical plate (12);
wherein, every limit structure all still includes: a positioning plate (14) and a first telescopic pipe (15); the positioning plate (14) is fixedly connected to the rectangular transverse plate (10); one end of the first extension tube (15) is fixedly connected to the positioning plate (14), and the other end of the first extension tube is fixedly connected to the rectangular vertical plate (12);
every limit structure all still includes: a second telescopic tube (16); the second telescopic pipe (16) is arranged between the plummer (2) and the rectangular transverse plate (10);
the first telescopic tube (15) comprises: a first outer tube (151) and a first inner rod (152); the first inner rod (152) is movably inserted into the first outer pipe (151), one end of the first outer pipe (151) far away from the first inner pipe (152) is fixedly connected with the rectangular vertical plate (12), and one end of the first inner pipe (152) far away from the first outer pipe (151) is fixedly connected with the positioning plate (14); the second telescopic tube (16) comprises: a second outer tube (161) and a second inner rod (162); the second inner rod (162) is movably inserted into the second outer tube (161), the upper end of the second outer tube (161) is fixedly connected with the rectangular transverse plate (10), and the lower end of the second inner rod (162) is fixedly connected with the bearing table (2);
the bottom of the bearing table (2) and the top of the chassis (1) are both provided with a clamping groove; the top and the bottom of the air bag (3) are respectively inserted in the clamping grooves.
2. The carrying platform of the combined type fixed wing unmanned aerial vehicle of claim 1, characterized in that the top of the chassis (1) is installed in the bearing platform (2) through an up-down adjusting mechanism, and the up-down adjusting mechanism comprises a plurality of connecting units;
each of the connection units includes: a first threaded tube (17), a threaded rod (18) and a second threaded tube (19);
the upper end of the first threaded pipe (17) is fixedly connected with the bearing table (2); the threaded rod (18) is mounted inside the first threaded pipe (17) through threaded connection; the second threaded pipe (19) is mounted on the outside of the threaded rod (18) by means of a threaded connection; the lower end of the second threaded pipe (19) is fixedly connected to the chassis (1);
the inner wall threads of the first threaded pipe (17) and the second threaded pipe (19) are arranged in an up-down symmetrical mode, and the first threaded pipe (17) and the second threaded pipe (19) can move to the center of the threaded rod (18) or the first threaded pipe (17) and the second threaded pipe (19) can move in opposite directions by twisting the threaded rod (18).
3. The carrying platform of the combined type fixed wing unmanned aerial vehicle as claimed in claim 1, wherein the inner wall of the slot is provided with a first rubber layer (21).
4. A composite fixed wing drone carrying platform according to claim 1, characterised in that the bottom of the pressure plate is provided with a second rubber layer (22).
5. A method of operating a ride-on platform of claim 1, comprising the steps of:
the unmanned aerial vehicle lands on the middle part of the bearing platform;
the second air cylinder is started to push the rectangular vertical plate and the pressure plate to the center of the bearing table; the first air cylinder is started to drive the supporting plate, the second air cylinder and the pressing plate to move downwards, and the wings of the unmanned aerial vehicle are limited by the left pressing plate and the right pressing plate;
when the bearing platform is used in water, the bearing platform floats on the water surface through the air bag and is driven by the paddle;
when the land is used, the vehicle runs by driving wheels.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911267879.5A CN111301078B (en) | 2019-12-11 | 2019-12-11 | Carrying platform of combined type fixed wing unmanned aerial vehicle and operation method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911267879.5A CN111301078B (en) | 2019-12-11 | 2019-12-11 | Carrying platform of combined type fixed wing unmanned aerial vehicle and operation method thereof |
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| CN111301078A CN111301078A (en) | 2020-06-19 |
| CN111301078B true CN111301078B (en) | 2021-05-25 |
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| CN114670738B (en) * | 2022-03-24 | 2023-07-25 | 江西翱翔星云科技有限公司 | Unmanned aerial vehicle carrier vehicle and operation method thereof |
| CN115122837B (en) * | 2022-06-13 | 2023-04-07 | 安徽理工大学 | Amphibious robot for underground reservoir constructed by abandoned mine |
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| CN104163082B (en) * | 2014-09-01 | 2016-05-11 | 南京工业职业技术学院 | The amphibious automatic sampling vehicle of a kind of intelligent water environment |
| US11027843B2 (en) * | 2017-12-19 | 2021-06-08 | Wing Aviation Llc | System and methods for automatic payload pickup by UAV |
| CN108974384B (en) * | 2018-07-19 | 2020-06-02 | 湖北恒空科技有限公司 | Unmanned aerial vehicle descending platform |
| CN208915420U (en) * | 2018-08-14 | 2019-05-31 | 深圳市奥贝尔电子有限公司 | A kind of unmanned plane wing facilitating installation |
| CN110497750A (en) * | 2019-07-02 | 2019-11-26 | 刘璐 | A kind of amphibious Multipurpose high-speed ferryboat |
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Effective date of registration: 20240619 Address after: No. 669, Hangtian Middle Road, Xi'an national civil aerospace industry base, Shaanxi 710100 Patentee after: Electric Power Research Institute of State Grid Shaanxi Electric Power Co.,Ltd. Country or region after: China Patentee after: National Network (Xi'an) Environmental Protection Technology Center Co.,Ltd. Patentee after: Sichuan hengchuangtiandi automation equipment Co.,Ltd. Patentee after: STATE GRID CORPORATION OF CHINA Address before: No.669, Hangtian Middle Road, Chang'an District, Xi'an City, Shaanxi Province Patentee before: STATE GRID SHAANXI ELECTRIC POWER Research Institute Country or region before: China Patentee before: National Network (Xi'an) Environmental Protection Technology Center Co.,Ltd. Patentee before: Sichuan hengchuangtiandi automation equipment Co.,Ltd. Patentee before: STATE GRID CORPORATION OF CHINA |