CN113602495A - Platform device supporting multi-rotor unmanned aerial vehicle to take off and land in air - Google Patents
Platform device supporting multi-rotor unmanned aerial vehicle to take off and land in air Download PDFInfo
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- CN113602495A CN113602495A CN202111002421.4A CN202111002421A CN113602495A CN 113602495 A CN113602495 A CN 113602495A CN 202111002421 A CN202111002421 A CN 202111002421A CN 113602495 A CN113602495 A CN 113602495A
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- aerial vehicle
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 16
- 230000000712 assembly Effects 0.000 abstract description 12
- 238000000429 assembly Methods 0.000 abstract description 12
- 239000013585 weight reducing agent Substances 0.000 description 3
- 230000002035 prolonged effect Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000009827 uniform distribution Methods 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/02—Arrangements or adaptations of signal or lighting devices
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D5/00—Aircraft transported by aircraft, e.g. for release or reberthing during flight
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Abstract
The invention discloses a platform device supporting multi-rotor unmanned aerial vehicle to take off and land in the air, belonging to the field of unmanned aerial vehicles, and comprising a supporting plate, a lift component for providing lift force, an electric control component for supplying power and controlling the flight state of the platform device and a supporting frame; a plurality of weight-reducing air holes are formed in the supporting plate; the plurality of lift assemblies are arranged on the bottom surface of the support plate, and are symmetrically or circumferentially and uniformly distributed around the center of the bottom surface of the support plate; the electric control assembly is arranged on the bottom surface of the supporting plate and comprises a shell, a flight control system and a power supply system, wherein the flight control system is positioned in the shell and is electrically connected with the lift assembly, and the power supply system is electrically connected with the lift assembly and the flight control system; the support frame is fixedly arranged on the bottom surface of the support plate or the bottom surface of the machine shell. The invention effectively widens the task range executable by the existing multi-rotor unmanned aerial vehicle by providing a take-off and landing place for the multi-rotor unmanned aerial vehicle.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to a platform device supporting multi-rotor unmanned aerial vehicles to take off and land in the air.
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. Can be divided into fixed wing unmanned aerial vehicles, VTOL unmanned aerial vehicles, unmanned airship, helicopter unmanned aerial vehicle, many rotor unmanned aerial vehicle, parachute wing unmanned aerial vehicle etc. according to the platform configuration.
The multi-rotor unmanned aerial vehicle is a special unmanned helicopter with three or more rotor shafts, and the rotor shafts are driven by the rotation of a motor on each shaft, so that the lifting thrust is generated. The collective pitch of the rotors of the multi-rotor unmanned aerial vehicle is fixed, so that the total pitch of the rotors of the multi-rotor unmanned aerial vehicle is not variable like a common helicopter, and the size of the single-shaft propelling force can be changed by changing the relative rotating speed between different rotors during flight, so that the running track of the aircraft is controlled. And many rotor unmanned aerial vehicle have the nature controlled strong, but the characteristics of VTOL and hover, mainly are applicable to low latitude, low-speed, have the task type of VTOL and hover requirement. Hovering is the main characteristic of multi-rotor unmanned aerial vehicles and carries out mission operations.
Among the prior art, many rotor unmanned aerial vehicle's application scene constantly improves, and the task degree is more and more complicated, and duration and the distance of endurance to many rotor unmanned aerial vehicle require more and more high. However, because many rotor unmanned aerial vehicle is small slightly usually, consequently adopt battery powered more to make many rotor unmanned aerial vehicle's duration often less than 30 minutes, hardly satisfy the mission requirement, thereby can't return to the base and crash under the not enough condition of electric quantity.
Disclosure of Invention
Aiming at the problem that the requirement of a long endurance time task is difficult to meet due to short endurance time of a multi-rotor unmanned aerial vehicle in the prior art, the invention aims to provide a platform device supporting the take-off and landing of the multi-rotor unmanned aerial vehicle in the air.
In order to achieve the purpose, the technical scheme of the invention is as follows:
a platform device supporting multi-rotor unmanned aerial vehicle to take off and land in the air comprises a supporting plate, a lift assembly, an electric control assembly and a supporting frame, wherein the lift assembly is used for providing lift force, the electric control assembly is used for supplying power and controlling the flight state of the platform device; a plurality of weight-reducing air holes are formed in the supporting plate; the plurality of the lifting force components are arranged on the bottom surface of the supporting plate, and the plurality of the lifting force components are symmetrically or uniformly distributed in the circumferential direction around the center of the bottom surface of the supporting plate; the electric control assembly is arranged on the bottom surface of the supporting plate and comprises a casing, a flight control system and a power supply system, wherein the flight control system is positioned in the casing and is electrically connected with the lift assembly, and the power supply system is electrically connected with the lift assembly and the flight control system; the supporting frame is fixedly arranged on the bottom surface of the supporting plate or the bottom surface of the machine shell.
Preferably, the cabinet is installed at the center of the bottom surface of the support plate.
Preferably, the lifting assembly is detachably and fixedly connected to the bottom surface of the supporting plate; or the lifting force component is detachably and fixedly connected with the shell through the machine arm.
Preferably, the lift assembly comprises a motor and a blade mounted on an output end of the motor, and the blade is located on a side of the motor facing away from the support plate.
Preferably, the motor comprises a stator housing and a rotor shaft, and the stator housing is detachably and fixedly connected with the support plate or the horn through bolts or screws.
Furthermore, a lifting indication mark is arranged at the center of the top surface of the supporting plate.
Preferably, the take-off and landing indication mark is a sign.
Preferably, the shape of the support plate is a regular hexagon, six lift assemblies are arranged, and one lift assembly is arranged below each edge of the support plate.
Preferably, the weight-reducing ventilation holes are uniformly distributed on the support plate in a rectangular array or an annular array.
Preferably, the support frame comprises at least two inclined support rods which are symmetrically arranged, and a horizontal bottom rod connected to the lower end of each inclined support rod.
By adopting the technical scheme, the invention has the beneficial effects that: under the support of the electric control assembly, the supporting plate can be supported to fly in the air through the cooperative matching of the plurality of lift assemblies, so that the multi-rotor unmanned aerial vehicle can take off and land on the supporting plate, the platform device can convey the multi-rotor unmanned aerial vehicle to a task area, the task duration of the multi-rotor unmanned aerial vehicle is prolonged, or the multi-rotor unmanned aerial vehicle completing the task is connected back, the multi-rotor unmanned aerial vehicle is prevented from being crashed after power is lost, and the task range of the existing multi-rotor unmanned aerial vehicle is expanded.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a top view of the present invention;
fig. 3 is a schematic diagram of the present invention.
In the figure, 1-a supporting plate, 2-a lifting force component, 21-a motor, 22-a blade, 3-a lifting indication mark, 4-a supporting frame, 41-an inclined supporting rod, 42-a horizontal bottom rod and 5-a weight reduction vent hole.
Detailed Description
The following further describes embodiments of the present invention with reference to the drawings. It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
It should be noted that in the description of the present invention, the terms "upper", "lower", "left", "right", "front", "rear", and the like indicate orientations or positional relationships based on structures shown in the drawings, and are only used for convenience in describing the present invention, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
In the technical scheme, the terms "first" and "second" are only used for referring to the same or similar structures or corresponding structures with similar functions, and are not used for ranking the importance of the structures, or comparing the sizes or other meanings.
In addition, unless expressly stated or limited otherwise, the terms "mounted" and "connected" are to be construed broadly, e.g., the connection may be a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; the two structures can be directly connected or indirectly connected through an intermediate medium, and the two structures can be communicated with each other. To those skilled in the art, the specific meanings of the above terms in the present invention can be understood in light of the present general concepts, in connection with the specific context of the scheme.
Example one
A platform device for supporting multi-rotor unmanned aerial vehicle to take off and land in the air is shown in figures 1-3 and comprises a support plate 1, a lift assembly 2 for providing lift, an electric control assembly (not shown in the figure) for supplying power and controlling the flight state of the platform device and a support frame 4.
The support plate 1 is of a flat plate structure, a plurality of weight reduction air holes 5 are formed in the support plate 1, and the weight reduction air holes 5 are uniformly distributed in the support plate 1 in a rectangular array mode or in another embodiment in an annular array mode.
The lift force components 2 are arranged in a plurality of numbers, and the lift force components 2 are all arranged on one side of the bottom surface of the support plate 1, and the lift force components 2 are symmetrically or circumferentially and uniformly distributed around the center of the bottom surface of the support plate 1. It can be understood that when the number of the lift assemblies 2 is even, the plurality of lift assemblies 2 can be uniformly distributed in a symmetrical (central symmetrical) manner around the center of the bottom surface of the support plate 1, and can also be uniformly distributed in a circumferential manner around the center of the bottom surface of the support plate 1 on the same circumference; when the number of the lift assemblies 2 is odd, the plurality of lift assemblies 2 are preferably distributed on the same circumference in a manner of being uniformly distributed in the circumferential direction around the center of the bottom surface of the support plate 1. For example, in the present embodiment, the lift assemblies 2 are configured with six and arranged in a circumferentially uniform distribution; correspondingly, the shape of the support plate 1 is preferably a regular hexagon, and one lift assembly 2 is arranged below the middle position of each side of the support plate 1.
In this embodiment, the lift assembly 2 further includes a motor 21 and a blade 22 installed at an output end of the motor 21, and the blade 22 is located on a side of the motor 21 away from the support plate 1. The motor 21 includes a stator housing and a rotor shaft, and the support plate 1 is further provided with a screw hole or a threaded hole, so that the stator housing can be detachably and fixedly connected with the support plate 1 through a bolt or a screw.
The electrical control assembly is mounted on the bottom surface of the support plate 1 and preferably at the center of the bottom surface of the support plate 1, i.e. the electrical control assembly is located within the circumference of the plurality of lift assemblies 2. In this embodiment, the electric control assembly includes a housing, and a flight control system and a power supply system installed in the housing; the flight control system is electrically connected with each lift assembly 2, so that the working state of each lift assembly 2 is controlled through the flight control system, and therefore the flight control of the platform device is realized; wherein the power supply system comprises at least a battery, which is electrically connected with the flight control system and each lift assembly 2 for supplying power.
The supporting frame 4 is fixedly installed on one side of the bottom surface of the casing, and the supporting frame 4 specifically includes at least two inclined struts 41 arranged in an inclined manner and a horizontal bottom rod 42 connected to the lower end of each inclined strut 41. Wherein the inclined struts 41 are arranged in a centrosymmetric, axisymmetrical or circumferentially uniformly distributed manner. In this embodiment, two inclined support rods 41 are disposed and symmetrically disposed on two sides of the housing. It will be appreciated that in another preferred embodiment, the support frame 4 may also be fixedly mounted on the bottom surface of the support plate 1.
In one embodiment, a lifting and falling indication mark 3 is arranged at the center of the top surface of the support plate 1, for example, the lifting and falling indication mark 3 is a sign.
When the multi-rotor unmanned aerial vehicle is used, on one hand, the multi-rotor unmanned aerial vehicle can be supported by the supporting plate 1, the platform device can be controlled to fly through the flight control system, and then the multi-rotor unmanned aerial vehicle can be transported to a task area of the multi-rotor unmanned aerial vehicle, and the multi-rotor unmanned aerial vehicle takes off from the platform device, so that the multi-rotor unmanned aerial vehicle has enough electric quantity to execute a task, and the air-remaining time is prolonged; on the other hand, the multi-rotor unmanned aerial vehicle which has performed the task but is lack of power can land on the platform device positioned in the task area, and then the multi-rotor unmanned aerial vehicle is controlled to return by the flight control system. Therefore, the platform device provided by the invention can effectively expand the range of tasks executable by the existing multi-rotor unmanned aerial vehicle.
Example two
The difference from the first embodiment is that: in this embodiment, the casing is further connected with the horn, the number of the horn is the same as that of the lift assemblies 2, so that each lift assembly 2 is detachably and fixedly connected with the casing through one horn, and the arrangement is such that the casing, the horn, the lift assemblies 2 and the support frame 4 integrally form a multi-rotor unmanned aerial vehicle, and at the moment, the casing is the body of the unmanned aerial vehicle, so that the supporting plate 1 is installed on the top surface of the existing multi-rotor unmanned aerial vehicle, and the blades 22 in the lift assemblies 2 deviate from the supporting plate 1, thereby conveniently and quickly obtaining the platform device disclosed by the invention.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the described embodiments. It will be apparent to those skilled in the art that various changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, and the scope of protection is still within the scope of the invention.
Claims (10)
1. The utility model provides a support platform device of many rotor unmanned aerial vehicle air take-off and land which characterized in that: the lifting device comprises a supporting plate, a lifting assembly for providing lifting force, an electric control assembly for supplying power and controlling the flight state of the platform device, and a supporting frame; a plurality of weight-reducing air holes are formed in the supporting plate; the plurality of the lifting force components are arranged on the bottom surface of the supporting plate, and the plurality of the lifting force components are symmetrically or uniformly distributed in the circumferential direction around the center of the bottom surface of the supporting plate; the electric control assembly is arranged on the bottom surface of the supporting plate and comprises a casing, a flight control system and a power supply system, wherein the flight control system is positioned in the casing and is electrically connected with the lift assembly, and the power supply system is electrically connected with the lift assembly and the flight control system; the supporting frame is fixedly arranged on the bottom surface of the supporting plate or the bottom surface of the machine shell.
2. The platform device according to claim 1, wherein: the case is installed at the center of the bottom surface of the support plate.
3. The platform device according to claim 1, wherein: the lifting assembly is detachably and fixedly connected to the bottom surface of the supporting plate; or the lifting force component is detachably and fixedly connected with the shell through the machine arm.
4. A platform arrangement according to claim 3, wherein: the lift assembly comprises a motor and a paddle arranged on the output end of the motor, and the paddle is located on one side of the support plate deviated from the motor.
5. The platform device according to claim 4, wherein: the motor comprises a stator shell and a rotor shaft, wherein the stator shell is detachably and fixedly connected with the supporting plate or the machine arm through bolts or screws.
6. The platform device according to claim 1, wherein: and a lifting indication mark is arranged at the center of the top surface of the supporting plate.
7. The platform device according to claim 6, wherein: the lifting indication mark is a sign.
8. The platform device according to claim 1, wherein: the shape of backup pad is regular hexagon, the lift subassembly is provided with six, just the below of each limit of backup pad all disposes one the lift subassembly.
9. The platform device according to claim 1, wherein: the weight-reducing air holes are uniformly distributed on the supporting plate in a rectangular array or annular array mode.
10. The platform device according to claim 1, wherein: the support frame comprises at least two inclined support rods which are symmetrically arranged and horizontal bottom rods connected to the lower ends of the inclined support rods.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111002421.4A CN113602495A (en) | 2021-08-30 | 2021-08-30 | Platform device supporting multi-rotor unmanned aerial vehicle to take off and land in air |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111002421.4A CN113602495A (en) | 2021-08-30 | 2021-08-30 | Platform device supporting multi-rotor unmanned aerial vehicle to take off and land in air |
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| Publication Number | Publication Date |
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| CN113602495A true CN113602495A (en) | 2021-11-05 |
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| CN202111002421.4A Pending CN113602495A (en) | 2021-08-30 | 2021-08-30 | Platform device supporting multi-rotor unmanned aerial vehicle to take off and land in air |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114771835A (en) * | 2022-04-28 | 2022-07-22 | 复旦大学 | Fixed wing unmanned aerial vehicle air landing system |
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2021
- 2021-08-30 CN CN202111002421.4A patent/CN113602495A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114771835A (en) * | 2022-04-28 | 2022-07-22 | 复旦大学 | Fixed wing unmanned aerial vehicle air landing system |
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