CN213414246U - Cloud platform is grafting device fast and has its fuselage assembly, unmanned vehicles - Google Patents

Abstract

The utility model provides a quick grafting device of cloud platform and fuselage assembly, unmanned vehicles who has it, the quick grafting device of cloud platform includes: connecting plate, driving piece, first barrel and task module. The connecting plate is detachably arranged in the machine body; the driving piece is rotatably arranged at the upper end of the connecting plate, and at least one part of the driving piece extends out of the machine body; the first cylinder is arranged at the lower end of the connecting plate and fixedly connected with the driving piece; one of the task module and the first barrel is provided with a first clamping groove, and the other of the task module and the first barrel is provided with a first clamping platform matched with the first clamping groove. According to the utility model discloses quick grafting device of cloud platform can be directly through the rotary driving spare alright with the assembly between first barrel and the task module of realization, and structural layout is reasonable, and easily operation has promoted user experience.

Description

Cloud platform is grafting device fast and has its fuselage assembly, unmanned vehicles

Technical Field

The utility model belongs to the technical field of unmanned vehicles technique and specifically relates to a quick grafting device of cloud platform and fuselage assembly, unmanned vehicles who has it are related to.

Background

Along with the development of society, the application field of unmanned vehicles is constantly expanding, both trade aircraft and consumption aircraft have obtained the sufficient progress, especially multi-screw unmanned vehicles and the small-size unmanned vehicles that fixed wing unmanned vehicles represented, all obtained wide application in each application field, such as fields such as aerial photograph detection, electric power inspection, environmental monitoring and disaster inspection, and in current some unmanned aerial vehicles, because the size is great, and the cloud platform is installed in the unmanned aerial vehicle bottom, lead to needing whole upset unmanned aerial vehicle to carry out the assembly of cloud platform, the installation is complicated, user experience is not good.

Disclosure of Invention

The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, an object of the utility model is to provide a quick grafting device of cloud platform, the quick grafting device of cloud platform structural configuration is reasonable, and easily operation has promoted user experience.

The utility model also provides an unmanned vehicles's fuselage assembly with above-mentioned cloud platform device of pegging graft fast.

The utility model also provides an unmanned vehicles of fuselage assembly with above-mentioned unmanned vehicles.

According to the utility model discloses cloud platform device of pegging graft fast includes: the connecting plate is detachably arranged in the machine body; the driving piece is rotatably arranged at the upper end of the connecting plate, and at least one part of the driving piece extends out of the machine body; the first cylinder is arranged at the lower end of the connecting plate and fixedly connected with the driving piece; task module, task module with be formed with first joint groove on one in the first barrel, task module with be formed with on another in the first barrel with first joint groove complex first joint platform the driving piece includes: the rotating member is fixedly connected with the first cylinder, the elastic member is suitable for keeping the rotating member and the pivoting member in a separated state, and when the elastic force of the elastic member is overcome to enable the rotating member and the pivoting member to be matched with each other, the rotating member and the pivoting member rotate synchronously.

According to the utility model discloses quick grafting device of cloud platform through the cooperation of driving piece with first barrel for the user can be directly through the rotary driving piece alright with the assembly between first barrel and the task module of realization, and structural layout is reasonable, and easy to operate has promoted user experience.

In some embodiments of the present invention, the device for quickly inserting a holder further comprises: the second barrel, first barrel with inject accommodation space between the connecting plate, the second barrel is located in the accommodation space, be equipped with in the second barrel be suitable for with task module complex circuit connection subassembly.

Optionally, a second clamping table is formed on one of the second barrel and the first barrel, and a second clamping groove matched with the second clamping table is formed on the other one of the second barrel and the first barrel.

In some embodiments of the present invention, the connecting plate comprises: the connecting plate comprises a central plate and three supporting leg plates, wherein the three supporting leg plates are uniformly arranged around the circumference of the central plate in a spaced mode, one end, far away from the central plate, of each supporting leg plate is provided with a mounting hole, and a fastener is suitable for penetrating through the mounting hole to mount the connecting plate in the fuselage.

The utility model also provides an unmanned vehicles's fuselage assembly with above-mentioned cloud platform device of pegging graft fast.

According to the utility model discloses unmanned vehicles's fuselage assembly, unmanned vehicles's fuselage assembly still includes: the device comprises a machine body, a control device and a control device, wherein the machine body comprises an upper shell and a lower shell, and an installation space is defined between the upper shell and the lower shell; the first fixing frame is arranged in the mounting space; the connecting plate is detachably connected with the first fixing frame.

According to the utility model discloses unmanned vehicles's fuselage assembly can protect the inside spare part of fuselage assembly through last casing and lower casing betterly, can realize being connected of cloud platform quick grafting device and fuselage better through first fixed frame, and simultaneously, the quick grafting device of aerial ladder can comparatively convenient realization assembly, and from this, the fuselage assembly of this application assembles simply, and structural layout is reasonable, has promoted user experience.

Optionally, the fuselage assembly of the unmanned aerial vehicle further comprises: the second fixing frame is detachably arranged at the lower end of the first fixing frame and provided with a second mounting groove with a downward opening, a slotted hole allowing the task module to pass through is formed in the upper end of the second mounting groove, and at least one part of the task module is positioned in the second mounting groove after the task module is mounted on the first barrel; and the filling shell is suitable for being matched with the second mounting groove so as to seal the task module in the second mounting groove, and the lower surface of the filling shell, the lower surface of the second fixing frame and the lower surface of the lower shell are in the same arc-shaped surface.

Further, first fixed frame with be formed with at least one spliced pole on at least one in the fixed frame of second, first fixed frame with be formed with the connecting hole on another in the fixed frame of second, the fastener is suitable for to pass the connecting hole with the spliced pole cooperation, with will fixed frame of first fixed frame and second is fixed continuous, first fixed frame with the fixed frame cooperation of second is connected the back upper and lower both ends respectively with go up the casing with the inner wall butt of lower casing.

Optionally, unmanned vehicles's fuselage assembly still includes control module and battery module, control module with battery module all with first fixed frame can be dismantled continuously, battery module is close to installation space's front end, control module is close to installation space's rear end, the quick grafting device of cloud platform is located battery module with between the control module to the focus of adjustment fuselage assembly.

The utility model also provides an unmanned vehicles of fuselage assembly with above-mentioned unmanned vehicles.

According to the utility model discloses unmanned vehicles still includes: the machine head is detachably arranged at the front end of the machine body assembly; the second wing sections are symmetrically arranged on two sides of the fuselage assembly; the wingtip winglet is arranged at the front end of the second wing section and forms an included angle with the second wing section; the dual-rotor power assembly is symmetrically arranged on the rotor arms at the two sides of the second wing section relative to the fuselage, the empennage is of an inverted V-shaped structure, and the end part of the empennage is connected with the rotor arms through tail support rods; the fixed wing power component is arranged at the tail part of the airframe assembly.

According to the utility model discloses unmanned vehicles, through bispin wing power component and fixed wing power component, make unmanned vehicles can take off and land with zero speed, and have the ability of hovering, appearance design through streamlined setting, air component when having reduced flight, flight speed has been promoted, the quick grafting device convenient assembling of cloud platform simultaneously, user experience has been promoted, simultaneously can make unmanned vehicles can carry out the mapping of taking photo by plane betterly, electric power patrols and examines, the investigation operation of being not convenient for people for going on such as environmental monitoring and disaster inspection, and is rational in infrastructure, flight is stable, use the scene extensively.

Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.

Drawings

The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:

fig. 1 is an exploded view of a rapid tripod head plugging device according to an embodiment of the present invention;

fig. 2 is an assembly view of the first cylinder, the second cylinder and the connecting plate of the holder quick plugging device according to the embodiment of the present invention;

fig. 3 is an exploded view of a fuselage assembly of an unmanned aerial vehicle according to an embodiment of the present disclosure;

fig. 4 is a schematic view of a lower housing side structure of a fuselage assembly according to an embodiment of the invention;

FIG. 5 is a schematic view of the structure of FIG. 4 without the filling shell installed;

FIG. 6 is a schematic diagram of the task module of FIG. 5 with the task module removed;

fig. 7 is a task module schematic diagram of a pan/tilt/zoom apparatus according to an embodiment of the present invention;

fig. 8 is a schematic structural view of the bottom side of the second fixing frame of the pan/tilt/zoom apparatus according to the embodiment of the present invention;

fig. 9 is a schematic structural view of the top side of the second fixing frame of the pan/tilt/zoom apparatus according to the embodiment of the present invention;

fig. 10 is an assembly view of the rapid insertion device of the pan/tilt head according to the embodiment of the present invention with the first fixed frame;

fig. 11 is a cross-sectional view of a fuselage assembly according to an embodiment of the present invention;

fig. 12 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the invention.

Reference numerals:

100: the holder is quickly inserted into the device;

1: a connecting plate; 11: a center plate; 12: a leg plate;

2: a drive member; 21: a knob member; 22: a pivot member; 23: an elastic member;

3: a first cylinder; 4: a task module; 5: a second cylinder;

200: a fuselage assembly of the unmanned aerial vehicle;

6: a body; 61: an upper housing; 62: a lower housing;

7: a first fixed frame; 71: connecting columns;

8: a second fixed frame; 81: a second mounting groove; 82: filling the shell; 83: connecting holes;

9: a control module; 10: a battery module;

1000: an unmanned aerial vehicle;

101: a machine head; 102: a second wing section; 103: a wingtip winglet; 104: an aileron; 105: a rotor arm; 106: a dual rotor power assembly; 107: a fixed wing power assembly; 108: a tail wing; 109: a tail stay bar; 110: and a fixing member.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present invention, and should not be construed as limiting the present invention.

The following describes, with reference to fig. 1 to 12, a cradle head quick-plugging device 100 and a fuselage assembly 200 and an unmanned aerial vehicle 1000 of the unmanned aerial vehicle having the same according to an embodiment of the present invention.

Referring to fig. 1 to 12, a holder quick plugging device 100 according to an embodiment of the present invention includes: connecting plate 1, driving piece 2, first barrel 3 and task module 4.

Specifically, referring to fig. 1 and 10, the connecting plate 1 is detachably disposed in the machine body 6, the driving member 2 is rotatably disposed at the upper end of the connecting plate 1, and at least a portion of the connecting plate extends out of the machine body 6, the first barrel 3 is disposed at the lower end of the connecting plate 1, the first barrel 3 is fixedly connected with the driving member 2, one of the task module 4 and the first barrel 3 is formed with a first clamping groove, and the other of the task module 4 and the first barrel 3 is formed with a first clamping platform matched with the first clamping groove. In other words, the first barrel 3 and the task module 4 can be connected by controlling the first clamping groove to be matched with the first clamping table, and the first barrel 3 and the task module 4 can be disconnected by releasing the matching between the first clamping groove and the first clamping table. Meanwhile, the connecting plate 1 can better fix the holder quick plugging device 100 in the machine body 6, and the stability of the structure is ensured.

From this, the user can be directly be located the outside part of fuselage 6 through operation driving piece 2 for driving piece 2 rotates, and then drives the first barrel 3 that links to each other with driving piece 2 is fixed and rotate, and first barrel 3 rotates the back, and joint can be realized better in first joint groove and first joint platform, thereby accomplishes the assembly of first barrel 3 and task module 4. On the other hand, when task module 4 is dismantled to needs, only need with driving piece 2 antiport to the first barrel of drive 3 antiport, alright make first joint groove and first joint platform break away from the cooperation.

According to the utility model discloses quick grafting device 100 of cloud platform through the cooperation of driving piece 2 with first barrel 3 for the user can be directly through rotary driving piece 2 alright with the assembly between realizing first barrel 3 and task module 4, and structural configuration is reasonable, and easily operation has promoted user experience.

In some examples, referring to fig. 7, the task module 4 may be a camera, a temperature detection device, or other devices, and may be selected according to the requirement of the job, which is not limited herein.

In some embodiments of the present invention, as shown in fig. 1, the driving member 2 comprises: the rotary knob member 21, the pivoting member 22 and the elastic member 23 arranged between the rotary knob member 21 and the pivoting member 22, the pivoting member 22 is fixedly connected with the first cylinder 3, the elastic member 23 is suitable for keeping the rotary knob member 21 and the pivoting member 22 in a separated state, and when the elastic force of the elastic member 23 is overcome to enable the rotary knob member 21 and the pivoting member 22 to be matched with each other, the rotary knob member 21 and the pivoting member 22 rotate synchronously. From this, can be through pressing and rotating knob piece 21, drive pivot piece 22 rotates, and then drive first barrel 3 and rotate for first barrel 3 is connected with task module 4 cooperation, and loose knob piece 21 after the connection is accomplished, and knob piece 21 and pivot piece 22 are in the separation state, can avoid first barrel 3 to take place to rotate effectively, guarantee and task module 4 between be connected, structural layout is reasonable.

In other embodiments of the present invention, referring to fig. 1 and 2, the holder quick plugging device 100 further includes: second barrel 5, inject accommodation space between first barrel 3 and the connecting plate 1, second barrel 5 is located accommodation space, is equipped with in the second barrel 5 to be suitable for with task module 4 complex circuit connection subassembly, that is to say, can provide the normal work in order to guarantee task module 4 for task module 4 through circuit connection subassembly for task module 4. In one specific example, the circuit may also be a control circuit, and may issue a task instruction to the task module 4 so as to meet the work requirement.

Optionally, a second clamping table is formed on one of the second barrel 5 and the first barrel 3, and a second clamping groove matched with the second clamping table is formed on the other one of the second barrel 5 and the first barrel 3, so that the second barrel 5 can be better fixed in the accommodating space through the matching of the second clamping table and the second clamping groove, that is, the connection of the first barrel 3, the connecting plate 1 and the second barrel 5 is better maintained, the circuit connecting assembly can be normally matched with the task module 4, and the structural layout is reasonable.

In some embodiments of the present invention, as shown in fig. 2, the connection plate 1 includes: a central plate 11 and three leg plates 12, the three leg plates 12 being arranged at regular intervals around the circumference of the central plate 11, an end of each leg plate 12 remote from the central plate 11 being formed with a mounting hole through which a fastener is adapted to pass to mount the connecting plate 1 in the fuselage 6. Therefore, the rapid tripod head plugging device 100 can be simply assembled with the body 6 by connecting the three leg plates 12 with the body 6, and meanwhile, the central plate 11 can be effectively prevented from deforming, so that the assembled structure is stable.

The utility model also provides an unmanned vehicles's fuselage assembly 200 with above-mentioned cloud platform device 100 of pegging graft fast.

According to the utility model discloses unmanned vehicles's fuselage assembly 200, as shown in fig. 3, fuselage assembly 200 still includes: a body 6 and a first fixed frame 7.

Specifically, the body 6 includes an upper shell 61 and a lower shell 62, and an installation space is defined between the upper shell 61 and the lower shell 62, so that the installation space can better place and fix the components of the body assembly 200, and plays a certain role in protection.

Further, the first fixed frame 7 is arranged in the installation space, and the connecting plate 1 is detachably connected with the first fixed frame 7, in other words, the connecting plate 1 is connected with the machine body 6 through the connection with the first fixed frame 7, so that the operation is easy.

According to the utility model discloses unmanned vehicles's fuselage assembly 200 can protect the inside spare part of fuselage assembly 200 better through last casing 61 and lower casing 62, can realize being connected of cloud platform quick grafting device 100 and fuselage 6 better through first fixed frame 7, and simultaneously, the quick grafting device of aerial ladder can comparatively conveniently assemble task module 4, and from this, the fuselage assembly 200 of this application assembles simply, and structural layout is reasonable, has promoted user experience.

Optionally, with reference to fig. 3-11, the fuselage assembly 200 of the unmanned aerial vehicle further comprises: a second fixing frame 8 and a filling shell 82.

Specifically, the second fixing frame 8 is detachably provided at the lower end of the first fixing frame 7, the second fixing frame 8 has a second mounting groove 81 with a downward opening, the upper end of the second mounting groove 81 has a slot hole allowing the task module 4 to pass through, and at least a portion of the task module 4 is located in the second mounting groove 81 after being mounted on the first barrel 3.

That is to say, in the process of task module 4 installation, because some unmanned vehicles 1000's size is great to lead to unable installing unmanned vehicles 1000 upset, consequently, task module 4's installation can be accomplished comparatively simply conveniently to the slotted hole of this application accessible second mounting groove 81. Specifically, other structures of the quick cloud platform inserting device 100 have all been assembled inside the fuselage 6, at this moment, the user can stretch into the slotted hole with the one end that task module 4 has first joint groove or first joint mouth, simultaneously, press down knob piece 21 and make it be connected with pivot piece 22, and rotate knob piece 21, thereby drive the rotation of first barrel 3, and then make the first joint groove and the cooperation that first joint was buckled of first barrel 3 and task module 4, accomplish the assembly of task module 4 and first barrel 3. When task module 4 needs to be removed, knob piece 21 is pressed and turned reversely to remove task module 4, so that structural layout is reasonable, and user experience is improved.

In a specific example, the task modules 4 are all located in the second installation groove 81, so that air resistance caused by the fact that the task modules 4 protrude in the flying process can be well avoided, and the flying capacity of the unmanned aerial vehicle 1000 is improved.

As shown in fig. 4, the filling shell 82 is adapted to cooperate with the second mounting groove 81 to enclose the task module 4 in the second mounting groove 81, and the lower surface of the filling shell 82, the lower panel of the second fixing frame 8 and the lower surface of the lower shell 62 are in the same arc surface, so that the filling shell 82 can better protect the cradle head quick plugging device 100 after the assembly is completed, and the lower surface of the filling shell 82 and the lower surfaces of the second fixing frame 8 and the lower shell 62 can form a streamline structure, thereby effectively avoiding influencing aerodynamic force of the unmanned aerial vehicle 1000, and enhancing flight capability of the unmanned aerial vehicle 1000.

It should be noted that an opening that does not block the shooting angle of the holder quick plugging device 100 is formed on the lower surface of the filling shell 82, so as to ensure that the holder quick plugging device 100 is protected and the normal operation of the holder quick plugging device 100 is not affected.

Further, be formed with at least one spliced pole 71 on at least one in first fixed frame 7 and the fixed frame 8 of second, the fastener is suitable for passing connecting hole 83 and spliced pole 71 cooperation to with the fixed frame 8 of first fixed frame 7 and second fixed frame, the upper and lower both ends after first fixed frame 7 and the fixed frame 8 cooperation are connected respectively in the inner wall butt of last casing 61 and lower casing 62. From this, the overall structure after the connection is more compact, and overall layout is reasonable.

In a specific example as shown in fig. 10, a plurality of connecting posts 71 are formed on the first fixing frame 7, a plurality of connecting holes 83 corresponding to the connecting posts are formed on the second fixing frame 8, and the stability of connection is further improved by matching the connecting posts 71 with the connecting holes 83.

In another specific example, the first fixing frame 7 has a mounting protrusion extending from the periphery thereof, and the upper case 61 and the lower case 62 are fixedly connected to the upper surface and the lower surface of the mounting protrusion, respectively, and the connection manner may be an adhesive manner, without limitation, so that the connection stability can be improved well.

Optionally, the fuselage assembly 200 of the unmanned aerial vehicle further includes a control module 9 and a battery module 10, the control module 9 and the battery module 10 are detachably connected to the first fixing frame 7, the battery module 10 is adjacent to the front end of the installation space, the control module 9 is adjacent to the rear end of the installation space, the rapid cradle head plugging device 100 is located between the battery module 10 and the control module 9 to adjust the center of gravity of the fuselage assembly 200, that is, the center of gravity of the adjusted rapid cradle head plugging device 100 can better balance the stress difference between the battery module 10 and the control module 9 caused by the installation position, the weight difference and other factors, the center of gravity is stable, and the stability of the flight process of the aircraft is further improved.

The utility model also provides an unmanned vehicles 1000 who has above-mentioned fuselage assembly 200.

According to the utility model discloses unmanned vehicles 1000, referring to fig. 12, unmanned vehicles 1000 still includes: a nose 101, a second wing section 102, a wingtip winglet 103, a rotor arm 105, a tail wing 108, a dual rotor power assembly 106, and a fixed wing power assembly 107.

The machine head 101 is detachably disposed at the front end of the machine body assembly 200, and preferably, a receiving cavity is formed in the machine head 101.

As shown in fig. 12, the second wing section 102 is symmetrically disposed on both sides of the fuselage assembly 200, and the winglet 103 is disposed at the front end of the second wing section 102 and forms an angle with the second wing section 102, so that the winglet 103 can better prevent the air from flowing around the upper and lower surfaces of the second wing section 102, thereby reducing the damage of the air flowing around to the lift force.

In a specific example, the fuselage 6 and the second wing section 102 are connected by a fixing member 110, an aileron 104 is further disposed at a trailing edge position of the second wing section 102, the aileron 104 can be flipped up and down relative to the fuselage 6 to control the flight attitude of the unmanned aerial vehicle 1000, the aileron 104 includes an upper surface and a lower surface opposite to each other, the upper surface is substantially flush with the top surface of the second wing section 102, and the lower surface of the aileron 104 is substantially flush with the bottom surface of the second wing section 102. Preferably, a steering engine capable of controlling the ailerons 104 to turn is arranged in the first wing section 6, so as to control the flight direction of the unmanned aerial vehicle 1000. Specifically, the steering wheel sets up in mounting 110, and the output shaft of multistage steering wheel is worn out along mounting 110's lateral wall to be connected with aileron 104 through coupling assembling and rotate in order to drive aileron 104.

In some examples, the wing includes, but is not limited to, the second wing section 102, and may include a third wing section and a fourth wing section, and may be configured according to the size of the unmanned aerial vehicle 1000, and is not limited thereto, and the connection between the wing sections is the same as the connection between the fuselage 6 and the second wing section 102.

Furthermore, rotor arms 105 perpendicular to the second wing section 102 are arranged on the second wing section 102, two dual-rotor power assemblies 106 are arranged on each rotor arm 105 and are respectively arranged on two sides of the wing, the dual-rotor power assemblies 106 are symmetrically arranged on the rotor arms 105 on two sides of the second wing section 102 relative to the fuselage 6, the tail wing 108 is in an inverted V-tail layout, and tail support rods 109 at two ends of a V shape are connected with the rotor arms 105.

In a specific example, the tail wing 108 includes two tail wing plates, the two tail wing plates are pivoted with each other, are arranged in an inverted V shape, and can be folded with each other, so that the storage space of the tail wing 108 can be reduced when the tail wing 108 is detached, and in addition, a movable control surface is installed at the rear edge of the tail wing plates, so that the inverted V-shaped tail wing 108 has the engineering of a normal fixed wing vertical tail and a normal tail, the structure weight is small, and the control efficiency is high. In some examples, tail 108 may also employ a double-droop tail or other configuration of tail.

Optionally, the fixed-wing power assembly 107 adopts a tail-push propeller layout, and a driving motor shaft is connected to a carbon fiber thrust propeller and is located at a tail portion of the fuselage assembly 200, wherein the fixed-wing power assembly 107 can provide a horizontal flight driving force for the unmanned aerial vehicle 1000, and after the unmanned aerial vehicle 1000 reaches a certain horizontal flight speed, the wings can provide sufficient lift force for the unmanned aerial vehicle 1000, so as to ensure that the unmanned aerial vehicle 1000 can normally fly.

In other examples, dual rotor power assembly 106 includes a carbon fiber propeller coupled to a brushless dc motor shaft, a brushless dc motor coupled to rotor arm 105 via a motor mount, and a motor mount, whereby dual rotor power assembly 106 provides VTOL flight capability for UAV 1000, i.e., enables UAV 1000 to better VTOL and hover.

According to the utility model discloses unmanned vehicles 1000, through bispin wing power component 106 and fixed wing power component 107, make unmanned vehicles 1000 take off and land with zero speed, and have the ability of hovering, appearance design through streamlined setting, air component when having reduced the flight, flight speed has been promoted, task module 4 can make unmanned vehicles 1000 carry out the aerial photography survey and drawing betterly simultaneously, electric power is patrolled and examined, the investigation operation of being not convenient for people for going on such as environmental monitoring and disaster inspection, and is rational in infrastructure, flight is stable, the application scene is wide.

Other constructions and operations of the cradle head quick-plugging device 100 according to the embodiment of the present invention are known to those skilled in the art and will not be described in detail herein.

In the description herein, references to the description of the terms "some embodiments," "optionally," "further," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims (9)

1. A device (100) for the rapid insertion of a head, comprising:

the connecting plate (1), the said connecting plate (1) is set in fuselage (6) removably;

the driving piece (2) is rotatably arranged at the upper end of the connecting plate (1), and at least one part of the driving piece (2) extends out of the machine body (6);

the first cylinder (3) is arranged at the lower end of the connecting plate (1), and the first cylinder (3) is fixedly connected with the driving piece (2);

a task module (4), wherein a first clamping groove is formed in one of the task module (4) and the first barrel (3), and a first clamping table matched with the first clamping groove is formed in the other one of the task module (4) and the first barrel (3);

the driver (2) comprises:

the rotary knob comprises a rotary knob body (21), a pivoting piece (22) and an elastic piece (23) arranged between the rotary knob body (21) and the pivoting piece (22), wherein the pivoting piece (22) is fixedly connected with the first cylinder body (3), the elastic piece (23) is suitable for keeping the rotary knob body (21) and the pivoting piece (22) in a separated state, and when the elastic force of the elastic piece (23) is overcome to enable the rotary knob body (21) and the pivoting piece (22) to be matched with each other, the rotary knob body (21) and the pivoting piece (22) rotate synchronously.

2. The head quick-plugging device (100) according to claim 1, further comprising: second barrel (5), first barrel (3) with inject accommodation space between connecting plate (1), second barrel (5) are located in the accommodation space, be equipped with in second barrel (5) be suitable for with task module (4) complex circuit connection subassembly.

3. The holder quick-plugging device (100) according to claim 2, wherein a second clamping platform is formed on one of said second cylinder (5) and said first cylinder (3), and a second clamping groove matched with said second clamping platform is formed on the other of said second cylinder (5) and said first cylinder (3).

4. Cradle head quick-plugging device (100) according to claim 1, characterized in that said connection plate (1) comprises:

a central plate (11) and three leg plates (12), wherein the three leg plates (12) are uniformly arranged around the circumference of the central plate (11) at intervals, and a mounting hole is formed at one end of each leg plate (12) far away from the central plate (11), and a fastener is suitable for passing through the mounting hole to mount the connecting plate (1) in the fuselage (6).

5. A fuselage assembly (200) of an unmanned aerial vehicle, comprising:

the airplane body (6), wherein the airplane body (6) comprises an upper shell (61) and a lower shell (62), and an installation space is defined between the upper shell (61) and the lower shell (62);

the first fixing frame (7), the said first fixing frame (7) locates in the said installation space;

cradle head quick plugging device (100), said cradle head quick plugging device (100) comprising a cradle head quick plugging device (100) according to any one of claims 1 to 4, said connecting plate (1) being removably associated with said first fixed frame (7).

6. The fuselage assembly (200) of the unmanned aerial vehicle of claim 5, further comprising:

the second fixing frame (8), the second fixing frame (8) is detachably arranged at the lower end of the first fixing frame (7), the second fixing frame (8) is provided with a second mounting groove (81) with a downward opening, the upper end of the second mounting groove (81) is provided with a slotted hole allowing the task module (4) to pass through, and at least one part of the task module (4) is positioned in the second mounting groove (81) after being mounted on the first barrel (3);

a filling shell (82), wherein the filling shell (82) is suitable for being matched with the second mounting groove (81) so as to seal the task module (4) in the second mounting groove (81), and the lower surface of the filling shell (82), the lower surface of the second fixing frame (8) and the lower surface of the lower shell (62) are in the same arc-shaped plane.

7. The unmanned aerial vehicle's fuselage assembly (200) of claim 6, characterized in that, be formed with at least one spliced pole (71) on at least one in the first fixed frame (7) with the fixed frame of second (8), first fixed frame (7) with be formed with connecting hole (83) on another in the fixed frame of second (8), the fastener is suitable for passing connecting hole (83) with spliced pole (71) cooperation, with the fixed frame of first (7) and second (8) is fixed to be linked to each other, first fixed frame (7) with the upper and lower both ends after the fixed frame of second (8) cooperation is connected respectively with go up casing (61) with the inner wall butt of lower casing (62).

8. The fuselage assembly (200) of an unmanned aerial vehicle according to claim 5, further comprising a control module (9) and a battery module (10), wherein the control module (9) and the battery module (10) are both detachably connected to the first fixed frame (7), the battery module (10) is adjacent to the front end of the installation space, the control module (9) is adjacent to the rear end of the installation space, and the cradle head quick-plug device (100) is located between the battery module (10) and the control module (9) to adjust the center of gravity of the fuselage (6) assembly.

9. An unmanned aerial vehicle (1000), comprising:

a fuselage assembly (200), the fuselage assembly (200) comprising the fuselage assembly (200) of any one of claims 5 to 8;

the machine head (101), the machine head (101) is detachably arranged at the front end of the machine body assembly (200);

the second wing sections (102), the second wing sections (102) are symmetrically arranged on two sides of the fuselage assembly (200);

the wingtip winglet (103) is arranged at the front end of the second wing section (102), and an included angle is formed between the wingtip winglet (103) and the second wing section (102);

the double-rotor wing power assembly comprises rotor wing arms (105), a tail wing (108), double-rotor wing power assemblies (106) and fixed wing power assemblies (107), wherein the rotor wing arms (105) parallel to the second wing section (102) are arranged on the second wing section (102), two double-rotor wing power assemblies (106) are arranged on each rotor wing arm (105) and are respectively arranged on two sides of the second wing section (102), the double-rotor wing power assemblies (106) are symmetrically arranged on the rotor wing arms (105) on two sides of the second wing section (102) relative to a fuselage (6), the tail wing (108) is of an inverted V-shaped structure, and the end parts of the tail wing power assemblies are connected with the rotor wing arms (105) through tail stay bars (109); the fixed wing power component (107) is arranged at the tail part of the fuselage assembly (200).

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