CN113386966A - Unmanned aerial vehicle convenient to dismouting - Google Patents
Unmanned aerial vehicle convenient to dismouting Download PDFInfo
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- CN113386966A CN113386966A CN202110842152.6A CN202110842152A CN113386966A CN 113386966 A CN113386966 A CN 113386966A CN 202110842152 A CN202110842152 A CN 202110842152A CN 113386966 A CN113386966 A CN 113386966A
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- 230000007246 mechanism Effects 0.000 claims abstract description 106
- NOQGZXFMHARMLW-UHFFFAOYSA-N Daminozide Chemical group CN(C)NC(=O)CCC(O)=O NOQGZXFMHARMLW-UHFFFAOYSA-N 0.000 claims description 8
- 239000002828 fuel tank Substances 0.000 claims description 5
- 230000005611 electricity Effects 0.000 abstract description 16
- 238000010586 diagram Methods 0.000 description 7
- 210000002445 nipple Anatomy 0.000 description 3
- 238000013459 approach Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Forklifts And Lifting Vehicles (AREA)
Abstract
The invention provides an unmanned aerial vehicle convenient to disassemble and assemble, which comprises a vehicle body, a central wing, an outer wing, a tail wing and a tail stay bar, wherein a horizontal power mechanism is arranged at the rear end of the vehicle body; the unmanned aerial vehicle comprises a first positioning mechanism, a second positioning mechanism, a first electric connector and a second electric connector, wherein the first positioning mechanism positions the vehicle body and the central wing to enable the first electric connector to be connected with the second electric connector; unmanned aerial vehicle includes that third electricity connects and the fourth electricity connects, and second positioning mechanism location outer wing and tail vaulting pole and make the third electricity connect to connect in the fourth electricity. When the first positioning mechanism is connected with the body and the central wing, the body and the central wing can be close to each other, the first electric connector is connected with the second electric connector, and when the second positioning mechanism is connected with the outer wing and the central wing, the outer wing and the central wing can be close to each other, so that the third electric connector is connected with the fourth electric connector.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to an unmanned aerial vehicle convenient to disassemble and assemble.
Background
With the development of economy, aviation flight appliances, especially unmanned aerial vehicles, are more and more widely applied. The unmanned aerial vehicle is used as a toy and an aeromodelling, is also used in the fields of aerial photography, surveying and mapping, cargo delivery, military operation and the like, and has wide application prospect.
Currently, commercially available drones are mainly classified into fixed-wing drones and rotor-wing vertical take-off and landing drones. The fixed wing unmanned aerial vehicle has large load, but needs to provide a long runway and an open field for taking off and landing, and has high requirements on taking off and landing fields; but rotor VTOL formula unmanned aerial vehicle VTOL takes off and land perpendicularly, and is less to taking off and land the place requirement, but the overall structure dismouting is comparatively complicated, leads to the dismouting time longer, causes the maintenance overlength consuming time, is not convenient for use.
Disclosure of Invention
The invention mainly aims to provide an unmanned aerial vehicle convenient to disassemble and assemble.
In order to achieve the main purpose, the unmanned aerial vehicle convenient to disassemble and assemble provided by the invention comprises a body, a central wing, an outer wing, a tail wing and a tail stay bar, wherein a load assembly is arranged at the front end of the body, a horizontal power mechanism is arranged at the rear end of the body, and a vertical power mechanism is arranged on the tail stay bar; the unmanned aerial vehicle comprises a first positioning mechanism, a second positioning mechanism, a first electric connector and a second electric connector, wherein the first electric connector is arranged on the vehicle body, the second electric connector is arranged on the central wing, the first electric connector is connected with a connecting piece of the vehicle body, the connecting piece is arranged opposite to the bottom side of the central wing, and the first positioning mechanism positions the vehicle body and the central wing to enable the first electric connector to be connected with the second electric connector; the unmanned aerial vehicle comprises a third electric connector and a fourth electric connector, the third electric connector is arranged on the outer wing, the fourth electric connector is arranged on the tail support rod, and the second positioning mechanism positions the outer wing and the tail support rod to enable the third electric connector to be connected with the fourth electric connector; the tail fin is detachably connected to the tail stay bar.
It is seen by above-mentioned scheme, unmanned aerial vehicle is equipped with horizontal power unit and vertical power unit, unmanned aerial vehicle both can realize taking off perpendicularly, do and realize the ski-jump take off, and, the quick assembly disassembly of fuselage and central wing can be realized to first positioning mechanism, can make fuselage and central wing be close to each other when first positioning mechanism connects fuselage and central wing, make first electricity connect thereupon and connect in the second electricity and connect, the quick assembly disassembly of central wing and outer wing can be realized to the second positioning mechanism, can make outer wing and central wing be close to each other when second positioning mechanism connects outer wing and central wing, make the third electricity connect thereupon and connect in the fourth electricity and connect.
Preferably, a first end of the first positioning mechanism is removably attached to the fuselage and a second end of the first positioning mechanism is removably attached to the center wing.
Further, a first electrical connector is threadably connected to the attachment member of the fuselage and a second electrical connector is threadably connected to the center wing.
Preferably, the second positioning mechanism abuts against the positioning groove of the tail stay bar, the first end of the second positioning mechanism is detachably connected to the central wing, the second end of the second positioning mechanism is detachably connected to the outer wing, the central wing is provided with a loop bar, the outer wing is provided with a positioning bar, the loop bar and the positioning bar both penetrate through the tail stay bar, and the positioning bar is inserted into the loop bar.
Further, a third electrical connector is threadably attached to the first side of the outer wing and a fourth electrical connector is threadably attached to the outer side of the tail stay.
Preferably, unmanned aerial vehicle includes third positioning mechanism, and the tail vaulting pole is connected in third positioning mechanism, and the connecting rod butt of fin is in third positioning mechanism.
Furthermore, the third positioning mechanism comprises a screwing sleeve and a positioning sleeve, the screwing sleeve is sleeved on the outer wall of the positioning sleeve, the tail support rod is in threaded connection with the inner wall of the screwing sleeve, and the connecting rod is in interference fit with the inner wall of the positioning sleeve; unmanned aerial vehicle includes that the fifth electricity connects and the sixth electricity connects, and the fifth electricity connects to arrange in the tail vaulting pole, and the sixth electricity connects to arrange in the connecting rod, and third positioning mechanism fixes a position tail vaulting pole and fin and makes the fifth electricity connect to connect in the fourth electricity.
Preferably, the tail wing is arranged in an inverted V shape; the fin includes first alar part and second alar part that fourth positioning mechanism, mutual mirror symmetry arranged, and fourth positioning mechanism's first end threaded connection is in first alar part, and fourth positioning mechanism's second end is connected in second alar part.
Preferably, unmanned aerial vehicle includes fifth positioning mechanism, and the tail vaulting pole includes power cabin body and the body of rod, and power cabin body and the body of rod are connected to fifth positioning mechanism.
Preferably, the load assembly and the horizontal power mechanism are respectively detachably connected to the machine body, and the front end and the rear end of the machine body are respectively provided with at least one horizontal power mechanism; the machine body comprises a first machine body, a second machine body, a control panel, a fuel tank and a power supply cabin, wherein the connecting piece is connected to the first machine body in a threaded mode; the first body is provided with a rotatable sliding cover.
Drawings
The invention is further illustrated by means of the attached drawings, but the embodiments in the drawings do not constitute any limitation to the invention, and for a person skilled in the art, other drawings can be derived on the basis of the following drawings without inventive effort.
Fig. 1 is a structural diagram of an embodiment of an unmanned aerial vehicle according to the present invention.
Fig. 2 is a partial exploded view of an embodiment of the drone of the present invention.
Fig. 3 is a structural diagram of a fuselage of an embodiment of the drone of the present invention.
Fig. 4 is a partial block diagram of the body shown in fig. 3.
Figure 5 is a block diagram of a central wing of an embodiment of a drone according to the invention.
Figure 6 is a block diagram of another perspective of the central wing of an embodiment of the drone of the present invention.
Fig. 7 is a partial enlarged view of the structure shown in fig. 6 at a.
Fig. 8 is a block diagram of an outer wing of an embodiment of a drone according to the invention.
Fig. 9 is a partial structural diagram of an embodiment of the drone of the present invention.
Fig. 10 is a partial enlarged view of the structure shown in fig. 9 at B.
Fig. 11 is an enlarged view of a portion of the structure of fig. 9 with a part of the components hidden at C.
Fig. 12 is an enlarged schematic view of the internal structure when the fifth electrical terminal is connected to the sixth electrical terminal.
Fig. 13 is a partial exploded structural view of the fuselage of an embodiment of a drone according to the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Referring to fig. 1 and 2, the unmanned aerial vehicle 100 convenient to disassemble and assemble provided in this embodiment includes a vehicle body 1, a load assembly 2 is disposed at the front end of the vehicle body 1, at least one horizontal power mechanism 3 is disposed at the rear end of the vehicle body 1, the unmanned aerial vehicle 100 further includes a central wing 4, a tail stay rod 5, an outer wing 6 and a tail wing 7, the tail stay rod 5 is provided with a vertical power mechanism 8, the tail wing 7 is detachably connected to the tail stay rod 5, and the load assembly 2 and the horizontal power mechanism 3 are detachably connected to the vehicle body 1 by using a known connection structure respectively. The front end of the airframe 1 can also be provided with at least one horizontal power mechanism 2, so that the number of the horizontal power mechanisms 2 is two, and the takeoff efficiency of the unmanned aerial vehicle 100 is improved.
In the present embodiment, the number of the tail stay 5 and the outer wing 6 is two, two vertical power mechanisms 8 are arranged on each tail stay 5, and the central wing 4 and the outer wing 6 are arranged between the two vertical power mechanisms 8 of each tail stay 5.
Referring to fig. 1 to 6, the drone 100 comprises a first positioning mechanism 9, a second positioning mechanism 10, a first electrical connector 11 and a second electrical connector 12, the first electrical connector 11 being arranged at the fuselage 1 and the second electrical connector 12 being arranged at the central wing 4.
The first electrical terminal 11 is screwed to a connecting member 13 of the fuselage 1, the second electrical terminal 12 is screwed to the bottom side of the central wing 4, the connecting member 13 being arranged opposite the bottom side of the central wing 4. The fuselage 1 is provided with a first receiving opening 14 between the load assembly 2 and the horizontal power mechanism 3, the connecting member 11 is arranged at the bottom of the receiving opening 14, the first electric connector 11 is screwed to the connecting member 13 by a screw 15, so that the first electric connector is positioned in the fuselage 1, the electric connection part of the first electric connector 11 is positioned in the first receiving opening 14, and the positioning part of the first electric connector 11 passes through the first receiving opening 14 and is positioned in the main cabin of the fuselage 1.
The upper end face of fuselage 1 is equipped with first locating port 16, and the bottom surface of first locating port 16 is equipped with the screw hole, and first locating port 16 is located the top that first electricity connects 11, and first locating port 16 is close to horizontal power unit 3 for first electricity connects 11.
Referring to fig. 1 to 7, a first end of the first positioning mechanism 9 is detachably screwed to the first positioning port 16 of the body 1, and a second end of the first positioning mechanism 9 is detachably screwed to the central wing 4.
The bottom side of the central wing 4 is provided with a second receiving opening 17, the second electric connector 12 is screwed on the bottom surface of the second receiving opening 17, and the second receiving opening 17 is communicated with the first receiving opening 14.
The first positioning mechanism 9 can adopt a known connecting structure, when the unmanned aerial vehicle needs to be assembled, the first positioning mechanism 9 positions the fuselage 1 and the central wing 4 so that the fuselage 1 and the central wing 4 are close to each other and positioned, and the first electric connector 11 and the second electric connector 12 can move in opposite directions along with the mutual close of the fuselage 1 and the central wing 4 and are connected with each other; when unmanned aerial vehicle was dismantled to needs, first positioning mechanism 9 separation fuselage 1 and central wing 4 and make fuselage 1 and central wing 4 keep away from each other when, first electric joint 11 second electric joint 12 can move and separate each other along with keeping away from each other of fuselage 1 and central wing 4 and carrying on the back mutually. Thus, the first positioning means 9 positions the fuselage 1 and the central wing 4 so that the first electrical connector 11 is connected to the second electrical connector 12, making it possible to complete the electrical connection at the same time as the mutual mechanical connection of the fuselage 1 and the central wing 4 is completed.
The second positioning mechanism 10 abuts against the positioning groove of the tail stay bar 5, the first end of the second positioning mechanism 10 is detachably connected to the central wing 4, the second end of the second positioning mechanism 10 is detachably connected to the outer wing 6, the central wing 4 is provided with a loop bar 18, the outer wing 6 is provided with a positioning bar 19, the loop bar 18 and the positioning bar 19 both penetrate through the tail stay bar 5, and the positioning bar 19 is inserted into the loop bar 18.
Referring to fig. 1 to 10, the second positioning mechanism 10 abuts against the positioning groove of the tail stay 5, a first end of the second positioning mechanism 10 is detachably connected to the central wing 4, a second end of the second positioning mechanism 10 is detachably connected to the outer wing 6, the central wing is provided with a loop bar 18, the outer wing 6 is provided with a positioning rod 19, the loop bar 18 and the positioning rod 19 both pass through the tail stay 5, and the positioning rod 19 is inserted into the loop bar 18.
The drone 100 comprises a third electrical connector 20 and a fourth electrical connector 21, the third electrical connector 20 being arranged on the outer wing 6, the fourth electrical connector 21 being arranged on the tail stay 5, the second positioning means 10 positioning the outer wing 6 and the tail stay 5 so that the third electrical connector 20 is connected to the fourth electrical connector 21.
A third electrical connector 20 is screwed to a first side of the outer wing 6 and a fourth electrical connector 21 is screwed to an outer side of the tail stay 5.
The second positioning mechanism 10 can adopt a known connecting structure, when the unmanned aerial vehicle needs to be assembled, the second positioning mechanism 10 positions the outer wing 6 and the central wing 4 so that the outer wing 6 and the central wing 4 are close to each other, and the outer wing 6 is close to the tail stay bar 5, so that the third electric connector 20 and the fourth electric connector 21 can move towards each other and are connected with each other along with the outer wing 6 close to the tail stay bar 5; when the unmanned aerial vehicle needs to be disassembled, the second positioning mechanism 10 separates the outer wing 6 from the central wing 4 to make the fuselage 1 and the central wing 4 away from each other, and the outer wing 6 also keeps away from the tail stay 5, so that the third electrical connector 20 and the fourth electrical connector 21 can move back and forth along with the outer wing 6 keeping away from the tail stay 5 and separate from each other. Therefore, the second positioning mechanism 10 positions the outer wing 6 and the tail stay 5 and connects the third electrical connector 20 to the fourth electrical connector 21, thereby completing the electrical connection while completing the mechanical connection of the tail stay 5, the outer wing 6, and the center wing 4 to each other.
Referring to fig. 1, 9 to 12, the drone 100 includes a third positioning mechanism 22, the tail stay 5 is connected to the third positioning mechanism 22, and the connecting rod 23 of the tail wing 7 abuts against the third positioning mechanism 22.
The drone 100 comprises a fifth electrical connector 27 and a sixth electrical connector 28, the fifth electrical connector 27 being removably fixedly arranged inside the tail stay 5 by screwing, the sixth electrical connector 28 being removably fixedly arranged inside the connecting rod 23 by screwing, the third positioning means 22 positioning the tail stay 5 with the tail 7 so that the fifth electrical connector 27 is connected to the fourth electrical connector 21.
When the unmanned aerial vehicle needs to be assembled, the connecting rod 23 is inserted into the tail stay bar 5, the screwing sleeve is rotated to enable the tail stay bar 5 to be positioned by being connected to the second sleeve part 26 through threads, and the fifth electric connector 27 and the sixth electric connector 2 are connected with the fifth electric connector and the sixth electric connector approaching to each other; when the unmanned aerial vehicle needs to be disassembled, the screwing sleeve is rotated to release the threaded connection between the tail stay 5 and the second sleeve part 26, and the fifth electric connector 27 and the sixth electric connector 2 are disconnected along with the mutual distance between the two.
The tail wing 7 is arranged in an inverted V shape, the tail wing 7 comprises a fourth positioning mechanism 28, a first wing part 29 and a second wing part 30 which are arranged in mirror symmetry, the first wing part 29 and the second wing part 30 form the inverted V shape, a first end of the fourth positioning mechanism 28 is connected to the first wing part 29 in a threaded manner, a second end of the fourth positioning mechanism 28 is connected to the second wing part 30, the fourth positioning mechanism 28 can adopt a known connecting structure, the first wing part 29 and the second wing part 30 can be locked and fixed with each other when the fourth positioning mechanism 28 is closed, and the first wing part 29 and the second wing part 30 can be rotated with each other when the fourth positioning mechanism 28 is opened to fold and detach the new tail wing 7.
The drone 100 includes a fifth positioning mechanism 31, the tail boom 5 includes a power cabin 32 and a rod 33, the fifth positioning mechanism 31 connects the power cabin 32 and the rod 33, the fifth positioning mechanism 31 can be a known connecting structure, and the third positioning mechanism 22 positions the power cabin 32 and the tail 7 so that the fifth electric connector 27 is connected to the fourth electric connector 21. The fifth positioning mechanism 31 can lock the power cabin 32 and the rod 33 to fix each other when closed, and can separate and fold the power cabin 32 and the rod 33 to facilitate boxing and transportation when opened when closed.
The unmanned aerial vehicle 100 is provided with a horizontal power mechanism 3 and a vertical power mechanism, the unmanned aerial vehicle 100 can realize both vertical takeoff and sliding takeoff, moreover, the first positioning mechanism 9 can realize quick assembly and disassembly of the body 1 and the central wing, the first positioning mechanism 9 can enable the body 1 and the central wing to approach each other when connecting the body 1 and the central wing, the first electric connector 11 is enabled to be connected with the second electric connector 12 along with the first electric connector, the second positioning mechanism 10 can realize quick assembly and disassembly of the central wing and the outer wing 6, the second positioning mechanism 10 can enable the outer wing 6 and the central wing to approach each other when connecting the outer wing 6 and the central wing, the third electric connector 20 is enabled to be connected with the fourth electric connector 21 along with the second positioning mechanism, the sleeve rod 18 and the positioning rod 19 both penetrate through the tail stay rod 5 to enable the tail stay rod 5 to be positioned between the central wing and the outer wing 6, so as to facilitate assembly and disassembly of the tail stay rod 5, therefore, make unmanned aerial vehicle 100 realize modularized design and dismouting, the user can customize and adopt each module according to specific in service behavior, optimizes the integration of task load and unmanned aerial vehicle 100.
Adopt high-efficient aerodynamic design such as big aspect ratio wing, high lift wing section, low windage fuselage for the complete machine lift drag is than higher, more combines the better FT70MF piston engine power system of fuel economy type, makes unmanned aerial vehicle 100's the biggest time of navigating be in advanced level in same level, the unmanned aerial vehicle of the same type, moreover, user's optional petrol engine, heavy oil engine are as power, thereby satisfy different application scenarios, wherein, the optional distribution of oil-driven engine starts/generator integrated device.
Referring to fig. 13, the main body 1 includes a first body 34, a second body 35, a control panel 36, a fuel tank 37 and a power supply compartment 38, the connecting member 13 is screwed to the first body 34, the first body 34 is screwed to the second body 35, the control panel 36 is screwed to the first body 34 and the second body 35, the fuel tank 37 is positioned in the second body 35 by one of a snap-fit and a screw-fit, and the power supply compartment 38 is connected to an outer bottom surface of the second body 35. In addition, first organism is equipped with rotatable sliding closure, is convenient for maintain unmanned aerial vehicle 100 inside.
Finally, it should be emphasized that the present invention is not limited to the above-described embodiments, but only the preferred embodiments of the invention have been described above, and the present invention is not limited to the above-described embodiments, and any modifications, equivalent substitutions, improvements, etc. within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The utility model provides an unmanned aerial vehicle convenient to dismouting, includes fuselage, central wing, outer wing, fin and tail vaulting pole, its characterized in that:
the front end of the machine body is provided with a load assembly, the rear end of the machine body is provided with a horizontal power mechanism, and the tail stay bar is provided with a vertical power mechanism;
said drone comprises a first positioning mechanism, a second positioning mechanism, a first electrical connector and a second electrical connector, said first electrical connector being arranged on said fuselage, said second electrical connector being arranged on said central wing, the first electrical connector being connected to a connector of said fuselage, said connector being arranged opposite the bottom side of said central wing, said first positioning mechanism positioning said fuselage and said central wing so that said first electrical connector is connected to said second electrical connector;
the drone includes a third electrical connector disposed to the outer wing and a fourth electrical connector disposed to the tail stay, the second positioning mechanism positioning the outer wing and the tail stay with the third electrical connector connected to the fourth electrical connector;
the tail fin is detachably connected to the tail stay.
2. The unmanned aerial vehicle convenient to dismouting of claim 1, characterized in that:
the first end of the first positioning mechanism is detachably connected to the fuselage, and the second end of the first positioning mechanism is detachably connected to the central wing.
3. The unmanned aerial vehicle convenient to dismouting of claim 2, characterized in that:
the first electrical connector is threadably attached to a connector of the fuselage and the second electrical connector is threadably attached to the center wing.
4. The unmanned aerial vehicle convenient to dismouting of claim 1, characterized in that:
the second positioning mechanism is abutted to the positioning groove of the tail support rod, the first end of the second positioning mechanism is detachably connected to the central wing, the second end of the second positioning mechanism is detachably connected to the outer wing, the central wing is provided with a sleeve rod, the outer wing is provided with a positioning rod, the sleeve rod and the positioning rod both penetrate through the tail support rod, and the positioning rod is inserted into the sleeve rod.
5. The unmanned aerial vehicle convenient to dismouting of claim 4, characterized in that:
the third electrical connector is threadably attached to the first side of the outer wing and the fourth electrical connector is threadably attached to the outer side of the tail stay.
6. The unmanned aerial vehicle convenient to dismouting of claim 1, characterized in that:
unmanned aerial vehicle includes third positioning mechanism, the tail vaulting pole connect in third positioning mechanism, the connecting rod butt of fin in third positioning mechanism.
7. The unmanned aerial vehicle convenient to dismouting of claim 6, characterized in that:
the third positioning mechanism comprises a screwing sleeve and a positioning sleeve, the screwing sleeve is sleeved on the outer wall of the positioning sleeve, the tail support rod is in threaded connection with the inner wall of the screwing sleeve, and the connecting rod is in interference fit with the inner wall of the positioning sleeve;
the unmanned aerial vehicle comprises a fifth electrical connector and a sixth electrical connector, the fifth electrical connector is arranged on the tail stay, the sixth electrical connector is arranged on the connecting rod, and the third positioning mechanism positions the tail stay and the tail wing to enable the fifth electrical connector to be connected with the fourth electrical connector.
8. An unmanned aerial vehicle convenient to dismount and mount according to any one of claims 1 to 7, wherein:
the tail wing is arranged in an inverted V shape;
the fin includes fourth positioning mechanism, first alar part and the second alar part of mutual mirror symmetry arrangement, fourth positioning mechanism's first end threaded connection in first alar part, fourth positioning mechanism's second end connect in the second alar part.
9. An unmanned aerial vehicle convenient to dismount and mount according to any one of claims 1 to 7, wherein:
unmanned aerial vehicle includes fifth positioning mechanism, the tail vaulting pole includes the power cabin body and the body of rod, fifth positioning mechanism connects the power cabin body with the body of rod.
10. An unmanned aerial vehicle convenient to dismount and mount according to any one of claims 1 to 7, wherein:
the load assembly and the horizontal power mechanism are respectively detachably connected to the machine body, and the front end and the rear end of the machine body are respectively provided with at least one horizontal power mechanism;
the machine body comprises a first machine body, a second machine body, a control panel, a fuel tank and a power supply cabin, the connecting piece is connected to the first machine body in a threaded mode, the first machine body is connected to the second machine body in a threaded mode, the control panel is connected to the first machine body and the second machine body in a threaded mode, the fuel tank is located in the second machine body, and the power supply cabin is connected to the bottom face of the outer side of the second machine body;
the first body is provided with a rotatable sliding cover.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110842152.6A CN113386966A (en) | 2021-07-23 | 2021-07-23 | Unmanned aerial vehicle convenient to dismouting |
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| CN202110842152.6A CN113386966A (en) | 2021-07-23 | 2021-07-23 | Unmanned aerial vehicle convenient to dismouting |
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Application publication date: 20210914 |