CN107466281B - Unmanned vehicles's frame and unmanned vehicles - Google Patents
Unmanned vehicles's frame and unmanned vehicles Download PDFInfo
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- CN107466281B CN107466281B CN201680012476.4A CN201680012476A CN107466281B CN 107466281 B CN107466281 B CN 107466281B CN 201680012476 A CN201680012476 A CN 201680012476A CN 107466281 B CN107466281 B CN 107466281B
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- flight control
- aerial vehicle
- unmanned aerial
- management module
- airframe
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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 141
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- 238000004891 communication Methods 0.000 claims description 30
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- 230000033228 biological regulation Effects 0.000 description 16
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- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 7
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- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
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Classifications
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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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/80—Arrangement of on-board electronics, e.g. avionics systems or wiring
- B64U20/83—Electronic components structurally integrated with aircraft elements, e.g. circuit boards carrying loads
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/90—Cooling
- B64U20/96—Cooling using air
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Toys (AREA)
Abstract
An airframe for an unmanned aerial vehicle, comprising: the device comprises a central frame (1), a distribution circuit board (2) and a flight control installation component (3); the centre frame (1) comprises a top surface and a bottom surface opposite to the top surface; one of the distribution circuit board (2) and the flight control installation component (3) is arranged on the top surface of the central frame (1), and the other one is arranged on the bottom surface of the central frame (1); the center frame (1) is detachably connected with the distribution circuit board (2). The frame of the unmanned aerial vehicle and the unmanned aerial vehicle are provided, and the flight control installation component (3) is installed on the top surface or the bottom surface of the center frame (1), so that the installation position of the flight controller (31) is determined, and the installation and the maintenance are easy. And the center frame (1) is detachably connected with the distribution circuit board (2), so that the distribution circuit board (2) is not installed on the center frame (1) as a structural member, is not easy to damage, and is convenient to disassemble, assemble and maintain.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a frame of an unmanned aerial vehicle and the unmanned aerial vehicle.
Background
An unmanned aerial vehicle is a flying device in rapid development, and has the advantages of flexibility, quick response, unmanned flight and low operation requirement. At present, the application range of the unmanned aerial vehicle is widened to three fields of military, scientific research and civil use. In the unmanned aerial vehicle, a battery is used for supplying power, and a flight controller is used for controlling flight.
Unmanned vehicles in the prior art generally use lithium batteries for power supply, and a distribution circuit board is used for distributing electric energy to each rotor. The distribution circuit board is sometimes installed on the center frame of the aircraft as a structural member, and sometimes adopts a simple welding mode to distribute the electric energy of the battery to each rotor wing. The power distribution circuit board is installed on a center frame of an aircraft as a structural member, and when the power distribution circuit board is subjected to large external force, the power distribution circuit board is easy to damage, and unnecessary loss is brought to users. When a simple welding mode is adopted, the disassembly, the assembly and the maintenance of the distribution circuit board are inconvenient.
In the prior art, the flight controller of the unmanned aerial vehicle needs to be installed by a user, the installation position is relatively free and messy, and the installation and maintenance are not easy.
Disclosure of Invention
In a first aspect, an embodiment of the present invention provides a rack of an unmanned aerial vehicle, including: the central frame, the distribution circuit board and the flight control installation assembly;
the center frame comprises a top surface and a bottom surface opposite to the top surface;
one of the distribution circuit board and the flight control installation assembly is arranged on the top surface of the central frame, and the other one of the distribution circuit board and the flight control installation assembly is arranged on the bottom surface of the central frame;
the center frame is detachably connected with the distribution circuit board.
In a second aspect, an embodiment of the present invention provides an unmanned aerial vehicle, including: a power system and a frame of the unmanned aerial vehicle of any one of the above;
wherein the power system is mounted on a frame of the unmanned aerial vehicle and electrically connected with the flight controller.
The embodiment of the invention provides a frame of an unmanned aerial vehicle and the unmanned aerial vehicle. In a frame of an unmanned aerial vehicle comprising: the central frame, the distribution circuit board and the flight control installation assembly; the central plate comprises a top surface and a bottom surface opposite to the top surface; one of the distribution circuit board and the flight control installation assembly is arranged on the top surface of the central frame, and the other one of the distribution circuit board and the flight control installation assembly is arranged on the bottom surface of the central frame; the central frame is detachably connected with the distribution circuit board. Because the flight controller assembly is arranged on the top surface or the bottom surface of the center frame, the installation position of the flight controller is determined, and the installation and the maintenance are easy. And the center frame is detachably connected with the distribution circuit board, so that the distribution circuit board is not installed on the center frame as a structural member and is not easy to damage. And is convenient for disassembly and assembly and maintenance.
Drawings
Fig. 1 is a first structural schematic diagram of a frame of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a second structural schematic diagram of a frame of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 3 is a first structural schematic diagram of a distribution circuit board in a rack of an unmanned aerial vehicle according to a second embodiment of the present invention;
fig. 4 is a second structural schematic diagram of a distribution circuit board in a rack of an unmanned aerial vehicle according to a second embodiment of the present invention;
fig. 5 is an exploded schematic view of a flight control installation assembly in a frame of an unmanned aerial vehicle according to a second embodiment of the present invention;
fig. 6 is a schematic structural diagram of a lower cover of a power distribution circuit board in a rack of an unmanned aerial vehicle according to a third embodiment of the present invention;
fig. 7 is a schematic structural diagram of an upper cover of a center frame in a frame of an unmanned aerial vehicle according to a fourth embodiment of the present invention;
fig. 8 is a schematic structural diagram of an unmanned aerial vehicle according to a fifth embodiment of the present invention;
fig. 9 is a partially enlarged view of regions a and B in fig. 8.
Reference numerals:
1-center frame 2-power distribution circuit board 21-substrate 22-power distribution circuit board fastener 23-elastic shock pad 24-buffer hole 25-power interface 26-communication interface 27-flight control signal interface 28-electric regulation signal interface 29-electric regulation power supply interface 210-first expansion interface 211-second expansion interface 212-third expansion interface 213-insulating protective layer 3-flight control installation component 31-flight controller 32-flight control installation plate 321-center plate 322-side plate 33-flight control installation plate 34-double-faced adhesive tape 35-flight control locking bracket 36-flight control locking member 37-first heat-conducting adhesive tape 38-power management module 39-power management module installation plate 310-power management module installation plate locking member 311-power management module locking bracket 312 Part 313, heat dissipation fins 314, second heat conduction silica gel 315, plug 316, plug locking piece 317, plug locking piece 4, distributor circuit board lower cover 41, buckle 5, center frame upper cover 51, heat dissipation fan 52, air guide channel 53, exhaust hole 54, anti-skid structure 6, arm 63, motor mounting seat 7, power system 71, propeller 72, motor 73, electric regulation
Detailed Description
The technical solutions in 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 obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When a 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.
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 invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
Some embodiments of the invention are described in detail below with reference to the accompanying drawings. The embodiments described below and the features of the embodiments can be combined with each other without conflict.
Example one
The embodiment of the invention provides a rack of an unmanned aerial vehicle. Fig. 1 is a first structural schematic diagram of the airframe of the unmanned aerial vehicle according to an embodiment of the present invention, which is shown in a bottom view from the bottom of the airframe of the unmanned aerial vehicle, and fig. 2 is a second structural schematic diagram of the airframe of the unmanned aerial vehicle according to an embodiment of the present invention, which is shown in a top view from the top of the airframe of the unmanned aerial vehicle. The structure of the airframe of the unmanned aerial vehicle according to the first embodiment of the present invention is not limited to the structure shown in fig. 1 and 2. Fig. 1 and 2 are combined to form a schematic view of only one of the structures of the airframe of the unmanned aerial vehicle.
As shown in fig. 1 and 2, the airframe of the unmanned aerial vehicle provided in the present embodiment includes: centre frame 1, divide electric circuit board 2 and flight control installation component 3.
Wherein the steady 1 comprises a top surface and a bottom surface opposite to the top surface. One of the power distribution circuit board 2 and the flight control installation component 3 is arranged on the top surface of the central frame 1, and the other one is arranged on the bottom surface of the central frame 1; the central frame 1 is detachably connected with the distribution circuit board 2.
In this embodiment, the center frame 1 may be a structure having a cavity, and includes a top surface and a bottom surface, and the top surface and the bottom surface are disposed opposite to each other. Specifically, the center frame 1 includes an upper support plate, a lower support plate, and a plurality of partition plates. The upper supporting plate and the lower supporting plate are arranged at intervals relatively. The plurality of partition plates are fixedly connected between the upper supporting plate and the lower supporting plate and jointly enclose a plurality of battery bins for containing batteries with the upper supporting plate and the lower supporting plate. Of course, in the present invention, the center frame is not limited to the illustrated configuration, and may have another configuration, for example, a hollow housing configuration.
It will be appreciated that the flight control mounting assembly 3 may be provided on the top surface of the central frame 1 and the electrical distribution board 2 may be provided on the bottom surface of the central frame 1. Alternatively, the flight control mounting component 3 may be provided on the bottom surface of the center frame 1, and the power distribution circuit board 2 may be provided on the top surface of the center frame 1.
In this embodiment, specific positions where the flight control mounting component 3 and the power distribution circuit board 2 are provided on the top surface or the bottom surface of the center frame 1 are not limited. If the flight control installation component 3 and the distribution circuit board 2 can be arranged oppositely, they are all arranged in the middle area of the top surface or the bottom surface of the central frame 1. The flight control installation component 3 and the distribution circuit board 2 can be arranged oppositely. For example, the flight control mounting assembly 3 may be disposed in a left region of the top surface of the center frame 1, and the power distribution circuit board 2 may be disposed in a right region of the bottom surface of the center frame 1.
In this embodiment, the flight control installation component 3 and the center frame 1 may be detachably connected. Such as snap fit, screw connection, etc. Non-detachable connections may also be made. Such as welding, riveting, etc., and this embodiment is not limited thereto.
In this embodiment, the center frame 1 is detachably connected to the power distribution circuit board 2. Such as clamping, screwing, etc.
The frame of unmanned vehicles that this embodiment provided includes: centre frame 1, divide electric circuit board 2 and flight control installation component 3. The steady 1 comprises a top surface and a bottom surface opposite to the top surface. One of the power distribution circuit board 2 and the flight control mounting component 3 is arranged on the top surface of the central frame 1, and the other one is arranged on the bottom surface of the central frame 1. The central frame 1 is detachably connected with the distribution circuit board 2. Because the flight control installation component 3 is installed on the top surface or the bottom surface of the center frame 1, the installation position of the flight control is determined, and the installation and the maintenance are easy. And the central frame 1 is detachably connected with the distribution circuit board 2, so that the distribution circuit board 2 is not installed on the central frame 1 as a structural member and is not easy to damage. And is convenient for disassembly and assembly and maintenance.
Example two
The second embodiment of the invention provides a frame of an unmanned aerial vehicle. Fig. 3 is a schematic view of a first structure of a distribution circuit board in a rack of an unmanned aerial vehicle according to a second embodiment of the present invention. Fig. 4 is a second schematic structural diagram of the distribution circuit board in the rack of the unmanned aerial vehicle according to the second embodiment of the present invention, which is a bottom view of the distribution circuit board 2 after installation. Fig. 5 is an exploded schematic view of the structure of the flight control installation assembly 3 in the airframe of the unmanned aerial vehicle according to the second embodiment of the present invention. The structure of the distribution circuit board 2 of the frame of the unmanned aerial vehicle according to the second embodiment of the present invention is not limited to the structure shown in fig. 3 and 4. Fig. 3 and 4 are only schematic structural diagrams of one of the power distribution circuit boards 2. The structure of the flight control installation assembly 3 of the airframe of the unmanned aerial vehicle according to the second embodiment of the present invention is not limited to the structure shown in fig. 5. As shown in fig. 3, 4 and 5, the present embodiment further includes the following features based on the technical solution provided in the first embodiment.
Further, in the present embodiment, the center frame 1 and the sub-electric circuit board 2 are fixedly connected by a connecting member. For example, the connector may be a threaded fastener, a pin, a snap, a latch, or the like.
Specifically, in this embodiment, the number and the positions of the connecting members for fixedly connecting the center frame 1 and the sub-electric circuit board 2 through the connecting members are not limited. If the number of the connecting members is one, the connecting members may be provided at the center of the base plate 21 of the distribution circuit board 2. The connecting piece can also be a plurality of connecting pieces, as in fig. 3, the center frame 1 and the branch electric circuit board 2 are fixedly connected through the branch electric circuit board fastener 22 in the threaded fastener. Specifically, a plurality of through holes may be provided at intervals in the circumferential direction of the base plate 21 of the distribution board 2, and the distribution board 2 is fixed to the center frame 1 by the distribution board fasteners 22. Specifically in the illustrated embodiment, the distributor plate fastener 22 is a mounting screw.
In this embodiment, the center frame 1 and the power distribution circuit board 2 are fixedly connected through a connecting member. For example, the connector may be a threaded fastener, a pin, a snap, a latch, or the like. The connection structure of the central frame 1 and the distribution circuit board 2 is simple, and the installation and the disassembly are easy.
Further, in the present embodiment, the power distribution circuit board 2 is disposed on the bottom surface of the center frame 1, and the flight control mounting assembly 3 is disposed on the top surface of the center frame 1.
Specifically, in this embodiment, the central frame 1 may be a cylindrical cavity structure, the flight control installation component 3 is disposed on the top surface of the central frame 1, and the power distribution circuit board 2 is disposed on the bottom surface of the central frame 1. The flight control installation component 3 and the distribution circuit board 2 are oppositely arranged in the central areas of the top surface and the bottom surface.
In this embodiment, the power distribution circuit board 2 is disposed on the bottom surface of the central frame 1, and the flight control mounting assembly 3 is disposed on the top surface of the central frame 1, so as to facilitate connection and wiring between the power distribution circuit board and the flight control mounting assembly, as well as between other systems.
Further, the airframe of unmanned vehicles that this embodiment provides still includes: and the elastic shock absorption pad 23, wherein the elastic shock absorption pad 23 is connected with the substrate 21 of the distribution circuit board 2 to absorb shock of the substrate 21 of the distribution circuit board 2.
Specifically, in the present embodiment, the elastic cushion 23 may be made of an elastic material such as silicone rubber. The elastic shock-absorbing pad 23 is connected with the base plate 21 of the distributor circuit board 2, and specifically, the elastic shock-absorbing pad 23 can be connected with the upper surface and the lower surface of the base plate 21. So as not to influence the distribution circuit board 2 when the frame of unmanned vehicles is deformed by force, and the base plate 21 of the distribution circuit board 2 is damped.
Preferably, the base plate 21 of the distribution circuit board 2 is provided with a buffer hole 24; the elastic cushion 23 is deformed to pass through the cushion hole 24 and detachably coupled to the base plate 21.
It is understood that the base plate 21 has a center symmetrical structure, and the buffer holes 24 are plural and uniformly arranged on the base plate 21 in the circumferential direction of the base plate 21. When the frame of the unmanned aerial vehicle is stressed and deformed, the elastic shock absorption pads 23 are arranged above and below the base plate 21 for blocking, so that the base plate 21 can be effectively damped.
For example, the substrate 21 may have a central symmetrical structure such as a circle, a rectangle, or a diamond. Of course, in other embodiments of the present invention, the substrate may also have a non-centrosymmetric structure, such as an isosceles trapezoid structure.
Further, in the present embodiment, the substrate 21 is provided with a power supply control circuit, and a plurality of electrical interfaces are mounted on the substrate 21 and electrically connected to the power supply control circuit. The power supply control circuit is used for controlling the series-parallel connection relation of the batteries and distributing the total electric energy of the batteries after series-parallel connection to the electric interfaces.
Specifically, in the present embodiment, the power control circuit distributes the total power to the plurality of electrical interfaces in a voltage-average distribution and current-on-demand distribution manner.
In this embodiment, the number of the electrical interfaces may be the same as the number of the smart battery and the number of the horn of the unmanned aerial vehicle, and may be six or other values, which is not limited in this embodiment.
In this embodiment, can set up the battery installation position on the centre frame, with the fixed setting of intelligent battery in the battery installation position.
In this embodiment, the plurality of electrical interfaces may be detachably mounted on the substrate 21, or may be non-detachably mounted on the substrate 21, which is not limited in this embodiment.
The electrical interface includes a power interface 25 and a communication interface 26, the power interface 25 is used for being electrically connected with the positive electrode and the negative electrode of the battery, and the communication interface 26 is used for being in communication connection with a control circuit in the battery.
It is understood that, as shown in fig. 3, in the present embodiment, the positive electrode interface and the negative electrode interface of the power interface 25 may be separated, each group of power interfaces 25 includes a power positive electrode interface and a power negative electrode interface, and specifically, six groups of power interfaces 25 may be provided, and the power interfaces 25 are disposed at intervals at the edge of the substrate 21. Preferably, the power supply interfaces 25 may be uniformly arranged at the edge of the substrate 21 in groups. The number of the communication interfaces 26 may be six, and the communication interfaces 26 are provided inside the power supply interface 25 at intervals in the circumferential direction of the substrate 21. Preferably, the communication interfaces 26 may be uniformly disposed inside the power interface 25 in the circumferential direction of the substrate 21.
Further, in the present embodiment, the substrate 21 is provided with a flight control signal interface 27, the flight control mounting assembly 3 includes a flight controller 31, and the flight control signal interface 27 is in communication connection with the flight controller 31.
In this embodiment, the flight control signal interface 27 can be disposed at the center of the substrate 21, so as to reduce the difficulty of connecting the flight control signal interface 27 and the flight controller 31 to the maximum.
Further, in this embodiment, the substrate 21 is provided with a plurality of electrically tunable connection terminals, which are respectively used for electrically tuning and connecting with a plurality of arms. The electric regulation connecting terminal comprises an electric regulation signal interface 28 used for being in communication connection with the electric regulation communication interface, so that the electric regulation is in communication connection with the flight controller 31 through the power distribution circuit board 2. The electric regulation connecting terminal comprises an electric regulation power supply interface 29 which is electrically connected with the electric regulation power interface and supplies power for the electric regulation.
In this embodiment, the plurality of electrically tunable connection terminals may be detachably mounted on the substrate 21, for example, in a screw manner. The substrate 21 may be mounted in a non-detachable manner, such as a soldering manner, which is not limited in this embodiment.
In this embodiment, a plurality of electrically tunable connection terminals may be disposed on the lower surface of the substrate 21. Specifically, as shown in fig. 4, the electrically tunable power supply interfaces 29 may be disposed on the lower surface of the substrate 21 at intervals along the circumferential direction of the substrate 21. Preferably, the electrically-tunable power supply interfaces 29 may be uniformly disposed on the lower surface of the substrate 21 along the circumferential direction of the substrate 21. The electric regulation signal interfaces 28 are arranged on the inner side of the electric regulation power supply interface 29 at intervals along the circumferential direction of the substrate 21. Preferably, the electrical modulation signal interface 28 may be uniformly disposed inside the electrical modulation power supply interface 29 along the circumferential direction of the substrate 21.
In practical applications, a user sends a control signal to the flight controller 31 through a remote controller, and the flight controller 31 sends a control signal to the electrical tilt through the flight control signal interface 27 and the electrical tilt signal interface 28. The electric regulator sends a driving signal to a motor electrically connected with the electric regulator according to the control signal, and the motor is driven to change parameters such as rotating speed and steering so as to change the motion state of the unmanned aerial vehicle.
Further, in this embodiment, the substrate 21 is provided with at least one expansion interface, and the expansion interface is used for electrically connecting with an external device. For example, the expansion interface can provide a direct-current power supply of 18 volts, 22 volts and the like for supplying power to the carrying parts of the unmanned aerial vehicle
Specifically, in the present embodiment, at least one expansion interface is disposed on the substrate 21. The installation position of the expansion interface and the connection mode with the substrate 21 are not limited. As shown in fig. 3 and 4, the first expansion interface 210 and the third expansion interface 212 are provided on the lower surface of the substrate 21, and the second expansion interface 211 is provided on the upper surface of the substrate 21. The external equipment can be equipment such as a tripod head, a camera, a video camera and the like.
In this embodiment, the substrate 21 is provided with at least one expansion interface, and the expansion interface is used for being electrically connected with an external device, so as to reserve an external interface for the external device, and enable the unmanned aerial vehicle rack to meet different application scenarios.
Further, the unmanned vehicles's frame that this embodiment provided still includes insulating protective layer 213, has seted up the fretwork window on insulating protective layer 213, and insulating protective layer 213 bonds in the lower surface of base plate 21.
In this embodiment, the shape of the insulating protection layer 213 is the same as that of the substrate 21. The insulating protective layer 213 is an insulating protective cotton layer. In other embodiments, the insulating protection layer 213 may also be an insulating rubber layer.
Specifically, in the present embodiment, since the plurality of electrically tunable connection terminals, the at least one expansion interface, and the elastic cushion 23 are disposed on the lower surface of the substrate 21, the insulating protection layer 213 is bonded to the lower surface of the substrate 21 for insulating and protecting the electrical distribution circuit board 2. A hollow window is formed in the insulating protection layer 213. The hollow window can be used for interfaces, connecting pieces, elastic shock absorption pads 23 and the like. The shape of the exposed hollow window is not limited in this embodiment. As shown in fig. 4, the insulating protection layer 213 is circular, the hollow windows include arrow-shaped hollow windows and hollow windows recessed from the edge to the center, the arrow-shaped hollow windows are radially distributed on the insulating protection layer 213, the head is in a direction away from the center of the circle, and the tail is in a direction close to the center of the circle. Hollow windows which are sunken from the edges to the center are arranged between the adjacent arrow-shaped hollow windows. The elastic shock absorption pad 23 is exposed at the head part of the arrow, the electric regulation signal interface 28 is exposed at the tail part of the arrow-shaped hollow window, and the electric regulation power supply interface 29 is exposed at the hollow window which is sunken from the edge to the center.
The frame of the unmanned aerial vehicle provided by the embodiment further comprises an insulating protection layer 213, a hollow window is formed in the insulating protection layer 213, and the insulating protection layer 213 is adhered to the lower surface of the substrate 21. The power distribution circuit board 2 can be insulated and protected, and the safety of the power distribution circuit board 2 is improved.
Further, the flight control mounting assembly 3 further includes a flight control mounting plate 32, the flight control mounting plate 32 is fixedly disposed on the top surface of the center frame 1, and the flight controller 31 is fixedly disposed on the upper surface of the flight control mounting plate 32.
Specifically, in this embodiment, the flight control mounting plate 32 and the central frame 1 may be detachably connected through a connecting member, where the connecting member includes at least one of the following: threaded fasteners, pins, buckles 41 and bolts. Non-detachable connections may also be made, as may welding, riveting, etc. The fixed connection mode of the flight controller 31 and the flight control mounting plate 32 can be screw connection, clamping connection, bonding connection and the like. The flight control mounting plate 32 may be fixedly disposed in a central region of the top surface of the steady rest 1. The flight controller 31 may be fixedly provided at a central region of the upper surface of the flight control mounting plate 32.
Preferably, in the present embodiment, the flight control mounting plate 32 includes a central plate 321, and the flight controller 31 is fixedly disposed on an upper surface of the central plate 321. The central plate 321 extends outwards to form a plurality of side plates 322, and the flight control mounting plate 32 is detachably connected with the central frame 1 through the side plates 322. Specifically, the flight control mounting plate 32 is fixed to the center frame 1 by screwing through holes of the side plates 322 and the flight control mounting plate locking pieces 33. Specifically, in the illustrated embodiment, the flight control mounting plate locking member 33 is a locking screw. In other embodiments, the control panel lock 33 may be a latch, a catch, or the like.
Preferably, the flight controller is adhered to the upper surface of the center plate 321. Specifically, as shown in fig. 5, the flight controller 31 may be adhered to the upper surface of the center board 321 by a double-sided adhesive 34.
As shown in fig. 5, in the present embodiment, the center board 321 of the flight control mounting board 32 has a rectangular structure, the flight controller 31 has a rectangular structure, and the flight controller 31 is fixedly disposed on the upper surface of the center board 321. Four side plates 322 extend from four side edges of the central plate 321, a through hole is formed in each side plate 322, and the flight control installation plate 32 is fixed on the top surface of the central frame 1 through the through holes of the side plates 322 and the flight control installation plate locking pieces 33.
In this embodiment, the flight control mounting plate 32 includes a central plate 321, and the flight controller 31 is fixedly provided on an upper surface of the central plate 321. The central plate 321 extends outwards to form a plurality of side plates 322, and the flight control mounting plate 32 is detachably connected with the central frame 1 through the side plates 322. The flight control installation plate 32 is fixed to the center frame 1 by screwing through holes of the side plates 322 and the flight control installation plate locking pieces 33. The flight controller 31 is adhered to the upper surface of the center plate 321. Making flight controller 31 more convenient to disassemble and assemble and maintain.
Further, the flight control mounting assembly 3 further includes a flight control lock bracket 35 and a flight control lock piece 36. The flight control lock bracket 35 presses the flight controller 31 against the flight control mounting plate 32. The flight control lock 36 detachably fixes the flight control lock bracket 35 to the flight control mounting plate 32.
Specifically, in this embodiment, the shape of the flight control lock bracket 35 may be set according to the shape of the flight controller 31, and is matched with the shape of the flight controller 31, so that the flight control lock bracket 35 can press the flight controller 31 against the flight control mounting plate 32. The flight control lock 36 may be a threaded fastener, pin, snap, latch, or the like. To removably secure flight control lock bracket 35 to flight control mounting plate 32.
Preferably, as shown in fig. 5, in this embodiment, the flight control locking bracket 35 is formed by sequentially connecting the head and the tail of a first side strip, a first top strip and a second side strip, the lower ends of the first side strip and the second side strip are symmetrically provided with through holes, the first top strip abuts against the upper surface of the flight controller 31, and the flight control locking member 36 passes through the through holes and is locked on the side surface of the flight control mounting plate 32.
Specifically, in this embodiment, the flight control lock bracket 35 is formed by sequentially connecting the head and the tail of a first side strip, a first top strip, and a second side strip. The included angle between the first side strip and the first top strip is 90 degrees, and the included angle between the first top strip and the second side strip is 90 degrees. The flight control lock bracket 35 is a frame-shaped structure. Through holes are symmetrically formed in the lower ends of the first lateral strip and the second lateral strip, and the flight control locking bracket 35 is pressed on the flight controller 31, namely, the first top strip abuts against the upper surface of the flight controller 31, and the first lateral strip and the second lateral strip abut against the side surface of the flight controller 31. And then the flying control locking piece 36 passes through the through hole and is locked on the side surface of the flying control mounting plate 32.
In this embodiment, the flight control mounting assembly 3 further includes a flight control locking bracket 35 and a flight control locking piece 36, and the flight control locking bracket 35 presses the flight controller 31 against the flight control mounting plate 32. The flight control lock 36 detachably fixes the flight control lock bracket 35 to the flight control mounting plate 32. The flight controller 31 is more firmly fixed on the center frame 1, and the frame of the whole unmanned aerial vehicle is more stable.
In this embodiment, the flight control locking bracket 35 is formed by sequentially connecting the head and the tail of a first side strip, a first top strip and a second side strip. The lower ends of the first side strip and the second side strip are symmetrically provided with through holes, the first top strip abuts against the upper surface of the flight controller 31, and the flight control locking piece 36 penetrates through the through holes and is locked on the side surface of the flight control mounting plate 32. The flight controller 31 is more firmly fixed to the center frame 1, and is more convenient to assemble, disassemble and maintain.
Further, in the airframe of the unmanned aerial vehicle provided by the present embodiment, a first thermally conductive silicone rubber 37 is further included. First thermally conductive silicone rubber 37 is disposed between flight control lock bracket 35 and the upper surface of flight controller 31.
In this embodiment, the first thermal conductive silicone rubber 37 may be a strip structure having the same size as the first top strip. Set up first heat conduction silica gel 37 between the upper surface of flying accuse locking support 35 and flight controller 31, make to fly to be non-rigid contact between the first top strip of accuse locking support 35 and the flight controller 31, but carry out excessively through heat conduction silica gel, both guaranteed to lock flight controller 31, can protect flight controller 31's outward appearance again, and can conduct the heat that flight controller 31 produced to flying accuse locking support 35 on, reinforcing flight controller 31's heat dissipation function.
Further, in this embodiment, the flight control installation component 3 further includes a power management module 38, and the power management module 38 is electrically connected to the flight controller 31 and the power distribution circuit board 2, respectively. The power management module 38 is fixedly disposed below the flight control panel 32.
In this embodiment, the power management module 38 is configured to manage electric energy of the plurality of smart batteries. And can be fixedly arranged below the flight control installation plate 32 in a detachable mode. Specifically, the flight control mounting assembly 3 further includes a power management module mounting plate 39, the power management module mounting plate 39 is fixedly disposed on the lower surface of the flight control mounting plate 32, and the power management module 38 is fixedly disposed on the lower surface of the power management module mounting plate 39.
In this embodiment, the power management module mounting plate 39 is detachably fixed to the lower surface of the flight control mounting plate 32, and specifically may be disposed on the lower surface of the central plate 321 of the flight control mounting plate 32. The power management module 38 is detachably fixed on the lower surface of the power management module mounting plate 39, and may be specifically disposed in the central area of the lower surface of the power management module mounting plate 39.
Preferably, as shown in fig. 5, in the present embodiment, the circumferential edge of the power management module mounting plate 39 is provided with a through hole, and the power management module mounting plate 39 and the flight control mounting plate 32 are fixed by screwing through the through hole and the power management module mounting plate locking member 310.
Specifically, the power management module mounting plate 39 may be a rectangular structure, and a through hole may be provided on each side of the power management module mounting plate 39, and each power management module mounting plate locking member 310 is fixed to the flight control mounting plate 32 by screwing through the through hole.
Further, flight control mounting assembly 3 further includes a power management module locking bracket 311 and a power management module locking member 312. The power management module locking bracket 311 presses the power management module 38 against the power management module mounting plate 39. A power management module retaining member 312 removably secures the power management module retaining bracket 311 to the power management module mounting plate 39.
Specifically, in this embodiment, the shape of the locking bracket 311 can be set according to the shape of the power management module 38, and is matched with the shape of the power management module 38. Allowing the power management module locking bracket 311 to press the power management module 38 against the power management module mounting plate 39. The power management module locking bracket 311 may be a threaded fastener, a pin, a snap, a latch, or the like. To removably secure the power management module locking bracket 311 to the power management module 38.
Preferably, as shown in fig. 5, in this embodiment, the power management module locking bracket 311 is formed by sequentially connecting a third side strip, a first bottom strip, and a fourth side strip end to end. Through holes are symmetrically formed in the upper ends of the third side strip and the fourth side strip. The first bottom strip abuts the lower surface of power management module 38 and power management module retaining member 312 passes through the through hole and is retained on the side of power management module mounting plate 39.
Specifically, in this embodiment, the power management module locking bracket 311 is formed by sequentially connecting a third side strip, a first bottom strip, and a fourth side strip end to end. The included angle between the third side strip and the first bottom strip is 90 degrees, and the included angle between the first bottom strip and the fourth side strip is 90 degrees. The power management module locking bracket 311 is a frame structure, and through holes are symmetrically formed at the lower ends of the third side bar and the fourth side bar, so that the power management module locking bracket 311 is pressed on the power management module 38, that is, the first bottom bar abuts against the lower surface of the power management module 38, and the third side bar and the fourth side bar abut against the side surface of the power management module 38. And then through the through-holes by power management module retaining members 312 to the side of the power management module mounting plate 39.
In this embodiment, flight control mounting assembly 3 further includes a power management module locking bracket 311 and a power management module locking member 312. The power management module locking bracket 311 presses the power management module 38 against the power management module mounting plate 39. A power management module retaining member 312 removably secures the power management module retaining bracket 311 to the power management module mounting plate 39. The power management module 38 is more firmly fixed on the flight control installation plate 32, and therefore the whole unmanned aerial vehicle frame is more stable.
In this embodiment, the power management module locking bracket 311 is formed by sequentially connecting the third side strip, the first bottom strip, and the fourth side strip end to end. Through holes are symmetrically formed in the upper ends of the third side strip and the fourth side strip. The first bottom strip abuts against the lower surface of the power management module 38. A power management module retaining member 312 passes through the through hole and is retained on the side of the power management module mounting plate 39. The power management module 38 is more firmly fixed on the flight control mounting plate 32, and is more convenient to assemble, disassemble and maintain.
Further, the power management module mounting board 39 is provided with heat dissipation fins 313.
Specifically, in the present embodiment, the heat dissipation fins 313 may be disposed on the upper surface of the power management module mounting board 39, or the heat dissipation fins 313 may be disposed on both the upper and lower surfaces.
In this embodiment, the power management module mounting plate 39 is provided with the heat dissipation fins 313, so that the heat dissipation effect of the power management module 38 is improved.
Further, the airframe of the unmanned aerial vehicle provided by this embodiment further includes a second heat-conducting silica gel 314, and the second heat-conducting silica gel 314 is disposed between the power management module locking bracket 311 and the lower surface of the power management module 38.
Specifically, the second thermally conductive silicone gel 314 may be a bar-shaped structure having the same size as the first base bar. Second heat-conducting silica gel 314 is arranged between the lower surfaces of the power management module locking support 311 and the power management module 38, so that the first bottom strip of the power management module locking support 311 is in non-rigid contact with the power management module 38, but the heat-conducting silica gel is excessive, the power management module 38 can be locked, the appearance of the power management module 38 can be protected, heat generated by the power management module 38 can be conducted to the power management module locking support 311, and the heat dissipation function of the power management module 38 is enhanced.
Further, in the airframe of the unmanned aerial vehicle provided in this embodiment, the power management module 38 further includes a plug 315. Accordingly, flight control mounting assembly 3 further includes: a plug lock 316 and a plug lock 317. The plug retaining member 316 retains the plug 315 to the lower surface of the power management module retaining bracket 311 by means of the plug retaining member 317.
Specifically, as shown in fig. 5, in this embodiment, a portion of the plug 315 extending from the power management module 38 is suspended, and in order to protect the plug 315, the flight control installation assembly 3 further includes: a plug lock 316 and a plug lock 317. The plug retaining member 316 retains the plug 315 to the lower surface of the power management module retaining bracket 311 by means of the plug retaining member 317.
EXAMPLE III
The third embodiment of the invention provides a frame of an unmanned aerial vehicle. Fig. 6 is a schematic structural diagram of a lower cover of a power distribution circuit board in a rack of an unmanned aerial vehicle according to a third embodiment of the present invention. As shown in fig. 6, the present embodiment is a further refinement of the frame structure of the unmanned aerial vehicle based on the technical solution provided in the first embodiment or the second embodiment. The airframe of the unmanned aerial vehicle provided by this embodiment further includes the following structure.
Further, the airframe of the unmanned aerial vehicle provided by the embodiment further comprises a lower cover 4 of the distribution circuit board. The lower cover 4 of the distribution circuit board is arranged below the distribution circuit board 2 and is clamped and fixed with the distribution circuit board 2.
Specifically, in this embodiment, the shape of the lower cover 4 of the distribution circuit board is not limited, and only needs to be matched with the shape of the distribution circuit board 2. One or more buckles 41 can be arranged on the inner side of the lower cover 4 of the distribution circuit board in the circumferential direction, and the lower cover of the distribution circuit board 2 is fixedly arranged below the distribution circuit board 2 through the buckles 41.
The unmanned vehicles frame that this embodiment provided still includes the branch electric circuit board lower cover 4. The lower cover 4 of the distribution circuit board is arranged below the distribution circuit board 2 and is clamped and fixed with the distribution circuit board 2. The power distribution circuit board 2 can be further protected, and the power distribution circuit board 2 is prevented from being damaged.
Example four
The fourth embodiment of the invention provides a frame of an unmanned aerial vehicle. Fig. 7 is a schematic structural diagram of an upper cover of a center frame in a rack of an unmanned aerial vehicle according to a fourth embodiment of the present invention. As shown in fig. 7, this embodiment is a further refinement of the frame structure of the unmanned aerial vehicle based on the technical solutions provided in the first embodiment, the second embodiment, or the third embodiment. The airframe of the unmanned aerial vehicle provided by this embodiment further includes the following structure.
Further, the airframe of the unmanned aerial vehicle provided by the embodiment further includes a center frame upper cover 5, and the center frame upper cover 5 covers the flight controller 31 and is fixedly connected with the center frame 1.
Specifically, the shape of the center frame upper cover 5 is not limited, and only needs to match the shape of the flight controller 31, and if the shape of the flight controller 31 is rectangular, the shape of the center frame upper cover 5 may be hexagonal. The center frame upper cover 5 covers the flight controller 31 and is detachably connected to the center frame 1. Such as screwing, clamping, etc.
The frame of the unmanned aerial vehicle provided by the embodiment further comprises a center frame upper cover 5, and the center frame upper cover 5 covers the flight controller 31 and is fixedly connected with the center frame 1. The flight controller 31 can be protected to prevent the flight controller 31 from being damaged.
Further, a heat radiation fan is built in the top of the center frame upper cover 5, and the heat radiation fan 51 is electrically connected to the flight controller 31. The side of the heat radiation fan is provided with an air guide channel 52 and an air exhaust hole 53.
Specifically, as shown in fig. 7, a heat radiation fan may be built in the top of the upper cover of the center frame 1, and the heat radiation fan 51 is electrically connected to the flight controller 31 to obtain electric power from the flight controller 31. An air guide passage 52 is provided on one side surface of the heat dissipating fan, and an air discharge hole 53 is provided on a side surface in an outward extending direction of the air guide passage 52. The flight controller 31 can be efficiently cooled.
Further, the two side surfaces of the center frame upper cover 5 adjacent to the air outlet 53 are respectively provided with an anti-slip structure 54.
Specifically, in the present embodiment, the anti-slip structure 54 may be an anti-slip bump or other anti-slip structure, which is not limited in the present embodiment.
In this embodiment, the two side surfaces of the upper cover 5 adjacent to the air exhaust hole 53 are respectively provided with the anti-slip structure 54, which is more convenient for dismounting and maintaining the upper cover 5.
EXAMPLE five
The fifth embodiment of the invention provides an unmanned aerial vehicle. Fig. 8 is a schematic structural diagram of an unmanned aerial vehicle according to a fifth embodiment of the present invention. As shown in fig. 8, the present embodiment provides an unmanned aerial vehicle including: power system, and the frame of unmanned vehicles that any embodiment provided above.
Wherein, the driving system is arranged on the frame of the unmanned aerial vehicle and is electrically connected with the flight controller.
In this embodiment, the structure and function of the airframe of the unmanned aerial vehicle in the unmanned aerial vehicle are the same as those in any one of the first to fourth embodiments, and are not described again.
In this embodiment, the power system is mounted on the frame of the unmanned aerial vehicle and is electrically connected to the flight controller. In the implementation application, a user sends a control signal to the flight controller through the remote controller, and the flight controller controls parameters in the power system according to the control signal so as to change the motion state of the unmanned aerial vehicle.
The embodiment provides an unmanned vehicles, includes: the power system 7 and the frame of the unmanned aerial vehicle provided by any one of the above embodiments. Wherein, the power system 7 is arranged on the frame of the unmanned aerial vehicle and is electrically connected with the flight controller. In a frame of an unmanned aerial vehicle comprising: the central frame, the distribution circuit board and the flight control installation assembly; the central plate comprises a top surface and a bottom surface opposite to the top surface; one of the distribution circuit board and the flight control installation assembly is arranged on the top surface of the central frame, and the other one of the distribution circuit board and the flight control installation assembly is arranged on the bottom surface of the central frame; the central frame is detachably connected with the distribution circuit board. Because the flight controller assembly is arranged on the top surface or the bottom surface of the center frame, the installation position of the flight controller is determined, and the installation and the maintenance are easy. And the center frame is detachably connected with the distribution circuit board, so that the distribution circuit board is not installed on the center frame as a structural member and is not easy to damage. And is convenient for disassembly and assembly and maintenance.
Further, the frame of the unmanned aerial vehicle also comprises a horn 6 connected with the center frame 1, and the power system 7 comprises a power device for providing flight power, wherein the power device is arranged on the horn 6.
Specifically, in the present embodiment, the center frame 1 in the frame of the unmanned aerial vehicle may be detachably connected to the horn 6. For example, the center frame 1 and the machine arm 6 are fixedly connected through a connecting piece. The connecting piece can be any one of a threaded fastener, a pin, a buckle and a bolt. The power system 7 includes a power device, and the power device is mounted on the horn 6, and the specific mounting manner is not limited in this embodiment.
Further, the power plant includes a propeller 71 and a motor 72 that drives the propeller 71 to rotate. Specifically, in the present embodiment, a propeller 71 and a motor 72 that drives the propeller 71 to rotate may be provided at an end of each horn 6.
Further, the power system 7 further includes an electric governor 73, and the electric governor 73 is electrically connected to the motor 72 and is used for controlling the operating state of the motor 72. Specifically, in the present embodiment, the electronic controller 73 is electrically connected to the motor 72 and is configured to control an operating state of the motor 72, such as controlling a rotation speed and a rotation direction of the motor 72. Specifically, in the illustrated embodiment, the motor 72 is mounted on a motor mount, the motor mount 63 is fixed to the horn 6, and the electronic governor 73 is mounted in the motor mount 63.
Further, fig. 9 is a partially enlarged view of regions a and B in fig. 8. As shown in fig. 9, the electronic tilt 73 is mounted on a plurality of arms, and is electrically connected to a plurality of connection terminals of the electronic tilt 73 on the substrate. The electric tuning 73 comprises a communication interface, and the communication interface of the electric tuning 73 is in communication connection with the electric tuning signal interface 28 on the substrate, so that the electric tuning is in communication connection with the flight controller 31 through the power distribution circuit board 2. The electric power conditioner comprises a power interface, and the power interface of the electric power conditioner is electrically connected with an electric power conditioning power supply interface 29 on the substrate 21 to supply power for the electric power conditioner.
Specifically, in this embodiment, an electric regulator may be disposed on the plurality of horn 6, and the electric regulator is electrically connected to the electric regulator connection terminals on the substrate. It can be understood that the electric controller is provided with a communication interface and a power interface, and the electric controller signal interface 28 in the electric controller connection terminal provided on the substrate 21 is in communication connection with the communication interface provided on the electric controller, so that the electric controller is in communication connection with the flight controller 31 through the electric distribution circuit board 2. The electric tuning power supply interface 29 in the electric tuning connection terminal arranged on the substrate 21 is electrically connected with the power interface arranged on the electric tuning terminal to supply power for the electric tuning.
In the unmanned aerial vehicle provided in this embodiment, the setting manner of the electrical tuning connection terminal on the substrate 21 is the same as that in embodiment two, and is not described herein again, and the setting manner of the communication interface and the power interface on the electrical tuning is not limited in this embodiment.
The unmanned vehicles that this embodiment provided, electricity is transferred and is installed on a plurality of horn, and respectively with a plurality of electricity on the base plate are transferred connecting terminal electricity and are connected. The electric tuning comprises a communication interface, the communication interface 71 of the electric tuning is in communication connection with the electric tuning signal interface 28 on the base plate, so that the electric tuning is in communication connection with the flight controller 31 through the power distribution circuit board 2. The electric power regulator comprises a power interface, and the power interface 72 of the electric power regulator is electrically connected with the electric power regulation power supply interface 29 on the substrate 21 to supply power for the electric power regulator. The layout of the whole unmanned aerial vehicle is more compact, and the unmanned aerial vehicle has better stability.
The above description is only an embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes performed by the present specification and drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.
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; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; 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 (43)
1. An airframe for an unmanned aerial vehicle, comprising: the central frame, the distribution circuit board and the flight control installation assembly;
the center frame comprises a top surface and a bottom surface opposite to the top surface;
one of the distribution circuit board and the flight control installation assembly is arranged on the top surface of the central frame, and the other one of the distribution circuit board and the flight control installation assembly is arranged on the bottom surface of the central frame;
the center frame is detachably connected with the distribution circuit board;
the substrate of the distribution circuit board is provided with a flight control signal interface, the flight control mounting assembly comprises a flight controller, and the flight control signal interface is in communication connection with the flight controller; the base plate is provided with a plurality of electrically-adjusted connecting terminals, each electrically-adjusted connecting terminal comprises an electrically-adjusted signal interface and is used for being in communication connection with an electrically-adjusted communication interface, so that the electrical adjustment is in communication connection with the flight controller through the power distribution circuit board.
2. The unmanned aerial vehicle airframe as defined in claim 1, wherein the center frame is fixedly connected to the distributor circuit board by a connector.
3. The unmanned aerial vehicle airframe of claim 2, wherein the connector comprises at least one of: threaded fastener, pin, buckle, bolt.
4. The airframe of any one of claims 1 to 3, wherein the electrical distribution board is disposed on a bottom surface of the center frame.
5. The airframe as recited in claim 4, wherein the flight control mounting assembly is fixedly disposed on a top surface of the center frame.
6. The unmanned aerial vehicle airframe of claim 4, further comprising a resilient shock pad coupled to the sub-circuit board base plate to dampen the sub-circuit board base plate.
7. The unmanned aerial vehicle frame of claim 6, wherein the base plate of the distribution circuit board is provided with a buffer hole;
the elastic shock pad penetrates through the buffer hole through deformation and is detachably connected with the base plate.
8. The unmanned aerial vehicle airframe as claimed in claim 7, wherein the base plate is a centrosymmetric structure, and the buffer holes are plural and are uniformly arranged on the base plate in a circumferential direction of the base plate.
9. The unmanned aerial vehicle airframe of claim 8, wherein the base plate is provided with power control circuitry, a plurality of electrical interfaces being mounted on the base plate and electrically connected to the power control circuitry;
the power supply control circuit is used for controlling the series-parallel connection relation of the batteries and distributing the total electric energy of the batteries after series-parallel connection to the electric interfaces.
10. The unmanned aerial vehicle airframe as defined in claim 9, wherein the electrical interface comprises a power interface for electrically connecting with the positive and negative poles of the battery, and a communication interface for communicatively connecting with a control circuit within the battery.
11. The UAV airframe as recited in claim 10, wherein the power interface is spaced apart at an edge of the base plate.
12. The unmanned aerial vehicle airframe of claim 11, wherein the communication interface is disposed inside the power interface at intervals in a circumferential direction of the base plate.
13. The unmanned aerial vehicle frame of claim 1, wherein the electrical tilt connection terminal comprises an electrical tilt power supply interface for electrically connecting with an electrical tilt power supply interface to supply power to the electrical tilt.
14. The airframe as claimed in claim 13, wherein the substrate has at least one expansion interface for electrical connection with an external device.
15. The unmanned aerial vehicle airframe as defined in claim 14, further comprising an insulating protective layer adhered to a lower surface of the base plate;
the insulating protective layer is provided with a hollow window, and the hollow window corresponds to the fastening connecting piece or/and the interface on the substrate.
16. The unmanned aerial vehicle airframe as defined in claim 1, wherein the flight control mounting assembly further comprises a flight control mounting plate fixedly disposed on a top surface of the center frame, the flight control being fixedly disposed on an upper surface of the flight control mounting plate.
17. The airframe as claimed in claim 16, wherein the flight control mounting plate includes a central plate, and the flight control is fixedly disposed on an upper surface of the central plate.
18. The airframe as recited in claim 17, wherein the central panel extends outwardly to form a plurality of side panels, and the flight control mounting panel is removably attached to the central frame by the side panels.
19. The unmanned aerial vehicle airframe as defined in claim 18, wherein the flight control mounting plate is secured to the center frame by the side plates and flight control mounting plate locking members.
20. The airframe as recited in claim 19, wherein said flight controller is bonded to an upper surface of said center panel.
21. The airframe of claim 20, wherein the flight control mounting assembly further comprises a flight control lock bracket and a flight control lock;
the flight control locking bracket presses the flight controller on the flight control mounting plate;
the flight control locking piece detachably fixes the flight control locking bracket on the flight control installation plate.
22. The unmanned aerial vehicle frame of claim 21, wherein the flight control locking bracket is formed by sequentially connecting a first side strip, a first top strip and a second side strip end to end, the lower ends of the first side strip and the second side strip are symmetrically provided with through holes, the first top strip abuts against the upper surface of the flight controller, and the flight control locking piece passes through the through holes and is locked on the side surface of the flight control mounting plate.
23. The unmanned aerial vehicle airframe of claim 22, further comprising a first thermally conductive silicone disposed between the flight control lockout mount and the upper surface of the flight controller.
24. The airframe as recited in any one of claims 16 to 23, wherein the flight control mounting assembly further comprises a power management module electrically connected to the flight controller and the distribution circuit board, respectively.
25. The unmanned aerial vehicle airframe of claim 24, wherein a power management module is fixedly disposed below the flight control mounting plate.
26. The unmanned aerial vehicle airframe of claim 25, wherein the flight control mounting assembly further comprises a power management module mounting plate, the power management module mounting plate is fixedly disposed on a lower surface of the flight control mounting plate, and the power management module is fixedly disposed on a lower surface of the power management module mounting plate.
27. The unmanned aerial vehicle airframe as defined in claim 26, wherein a peripheral edge of the power management module mounting plate is provided with a through hole, and the power management module mounting plate and the flight control mounting plate are secured by the through hole and a power management module mounting plate locking member.
28. The unmanned aerial vehicle airframe of claim 27, wherein the flight control mounting assembly further comprises a power management module locking bracket and a power management module locking member;
the power management module locking bracket tightly presses the power management module on the power management module mounting plate;
the power management module locking piece detachably fixes the power management module locking support on the power management module mounting plate.
29. The unmanned aerial vehicle frame of claim 28, wherein the power management module locking bracket is formed by sequentially connecting a third side strip, a first bottom strip and a fourth side strip end to end, through holes are symmetrically formed in the upper ends of the third side strip and the fourth side strip, the first bottom strip abuts against the lower surface of the power management module, and the power management module locking member penetrates through the through holes and is locked on the side surface of the power management module mounting plate.
30. The UAV airframe as recited in claim 26, wherein the power management module mounting plate has heat fins disposed thereon.
31. The UAV airframe as recited in claim 30, further comprising a second thermally conductive silicone disposed between a power management module locking bracket and a lower surface of the power management module.
32. The UAV airframe as recited in claim 31, wherein the power management module further comprises a plug;
accordingly, the flight control mounting assembly further comprises: the plug locking piece I and the plug locking piece II are arranged on the plug;
the first plug locking piece locks the plug on the lower surface of the power management module locking support through the second plug locking piece.
33. The airframe as recited in any one of claims 25 to 32, further comprising a distributor board lower cover disposed below the distributor board and snap-fitted to the distributor board.
34. The frame for an unmanned aerial vehicle of claim 33, further comprising a center frame upper cover, wherein the center frame upper cover covers the frame for the flight controller and is fixedly connected to the center frame.
35. The airframe as claimed in claim 34, wherein a heat dissipation fan is built in the top of the center frame cover, and the heat dissipation fan is electrically connected to the flight controller.
36. The unmanned aerial vehicle airframe as claimed in claim 35, wherein the side of the cooling fan is provided with a wind guide passage and a wind exhaust hole.
37. The airframe as claimed in claim 36, wherein the center frame cover has anti-slip structures formed on both sides thereof adjacent to the air discharge hole.
38. An unmanned aerial vehicle, comprising: a power system, and a frame of the unmanned aerial vehicle of any of claims 1-37;
wherein the power system is mounted on a frame of the unmanned aerial vehicle and electrically connected with the flight controller.
39. The UAV according to claim 38 wherein the frame of the UAV further comprises a horn connected to the central frame, the power system comprising a power device for providing flight power, the power device being mounted on the horn.
40. The UAV according to claim 39 wherein the power plant comprises a propeller and a motor for driving the propeller in rotation.
41. The unmanned aerial vehicle of claim 40, wherein the power system further comprises an electrical trim electrically connected to the motor for controlling an operating state of the motor.
42. The unmanned aerial vehicle of claim 41, wherein the electrical tilt is mounted on a plurality of horn and is electrically connected to a plurality of electrical tilt connection terminals on the base plate, respectively.
43. The unmanned aerial vehicle of claim 38, wherein the electrical tilt comprises a power interface, and the power interface of the electrical tilt is electrically connected with a power supply interface of the electrical tilt on the substrate to supply power to the electrical tilt.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/CN2016/079485 WO2017177458A1 (en) | 2016-04-15 | 2016-04-15 | Frame of unmanned aerial vehicle and unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107466281A CN107466281A (en) | 2017-12-12 |
| CN107466281B true CN107466281B (en) | 2021-07-20 |
Family
ID=60042340
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201680012476.4A Expired - Fee Related CN107466281B (en) | 2016-04-15 | 2016-04-15 | Unmanned vehicles's frame and unmanned vehicles |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN107466281B (en) |
| WO (1) | WO2017177458A1 (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108394545B (en) * | 2018-03-27 | 2024-03-26 | 傲飞创新科技（深圳）有限公司 | Spliced unmanned aerial vehicle fuselage |
| CN108622398B (en) * | 2018-06-04 | 2023-07-25 | 广州市华科尔科技股份有限公司 | Oil-electricity hybrid multi-rotor unmanned aerial vehicle control system and control method |
| CN208530829U (en) * | 2018-06-26 | 2019-02-22 | 深圳市大疆创新科技有限公司 | Unmanned plane expansion system and its unmanned plane, expansion module |
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| CN107466281A (en) | 2017-12-12 |
| WO2017177458A1 (en) | 2017-10-19 |
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