CN220764717U - Articulated multi-rotor unmanned aerial vehicle - Google Patents
Articulated multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN220764717U CN220764717U CN202322657917.6U CN202322657917U CN220764717U CN 220764717 U CN220764717 U CN 220764717U CN 202322657917 U CN202322657917 U CN 202322657917U CN 220764717 U CN220764717 U CN 220764717U
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Abstract
The utility model belongs to the technical field of multi-rotor unmanned aerial vehicles, and particularly relates to a hinged multi-rotor unmanned aerial vehicle. The utility model provides a hinged multi-rotor unmanned aerial vehicle, and aims to solve the problem that in the prior art, a rotor system of the multi-rotor unmanned aerial vehicle is rigidly connected with a machine body, so that the stability of the machine body structure is poor. The hinged multi-rotor unmanned aerial vehicle comprises a propeller system and a fuselage, wherein a universal hinge for enabling the fuselage to be in a horizontal state is arranged between the propeller system and the fuselage; the propeller system of the articulated multi-rotor unmanned aerial vehicle can enable the articulated multi-rotor unmanned aerial vehicle to reduce or even eliminate the inclination of the unmanned aerial vehicle caused by the posture adjustment of the articulated multi-rotor unmanned aerial vehicle when the articulated multi-rotor unmanned aerial vehicle flies in the air through the articulated form of the universal hinge structure and the fuselage, so that the stability of the fuselage during high-speed flying or maneuvering flying is ensured, some equipment with higher requirements on stability can be carried on the system, and the functionality and the universality of the multi-rotor unmanned aerial vehicle are improved.
Description
Technical Field
The utility model belongs to the technical field of multi-rotor unmanned aerial vehicles, and particularly relates to a hinged multi-rotor unmanned aerial vehicle.
Background
The transmission integrated multi-rotor unmanned aerial vehicle has certain limitation on the types of equipment which can be mounted due to the integrated design of the transmission integrated multi-rotor unmanned aerial vehicle. Because the rotor system and the fuselage of the integrated multi-rotor unmanned aerial vehicle are mainly rigidly and fixedly connected, the rotor system can drive the fuselage to do a large-scale tilting and rolling action in the high-speed flight and rapid turning process of the traditional integrated multi-rotor unmanned aerial vehicle, the attitude adjustment angle is too large, the stability of the whole system of the multi-rotor unmanned aerial vehicle cannot be well maintained, and the system cannot be well qualified in certain occasions such as carrying high-precision sensors to execute flight tasks.
The wind resistance of the integrated multi-rotor unmanned aerial vehicle is weak. The transmission integrated multi-rotor unmanned aerial vehicle can keep stable under the windy disturbance condition, and the following two conditions are required to be met simultaneously: the vertical component of lift equals to pass many rotor unmanned aerial vehicle self weight of unification, and the side direction component size of lift equals to pass many rotor unmanned aerial vehicle of unification and receive the side direction wind-force. The traditional wind-resistant mode of the integrated multi-rotor unmanned aerial vehicle is that the rotor system drives the whole machine to incline to generate lateral component force, but the lifting force is required to be separated from the whole machine to incline so as to keep the incline state of the integrated multi-rotor unmanned aerial vehicle, and the component occupies motor power, so that the lateral component force which can be provided by the traditional integrated multi-rotor unmanned aerial vehicle during wind resistance is reduced.
The aerodynamic efficiency and pitching rolling moment efficiency of the propeller system can be reduced when the transmission integrated multi-rotor unmanned aerial vehicle does pitching rolling action in the air, so that the transmission integrated multi-rotor unmanned aerial vehicle can only keep the posture balance of the body by increasing the output power of the motor, the power consumption of the transmission integrated multi-rotor unmanned aerial vehicle in the posture adjustment process is greatly increased, and the total endurance time is shortened.
The vibration of the rotor system self can be directly transmitted to the fuselage and the mounting equipment connected with the fuselage during flight operation of the integrated multi-rotor unmanned aerial vehicle, so that the structural stability of the fuselage and the vibration working condition of the mounting equipment can be greatly influenced, and the operation safety of the integrated multi-rotor unmanned aerial vehicle and the high-precision quality output of the mounting equipment are greatly reduced.
The integrated design of the integrated multi-rotor unmanned aerial vehicle makes the moment of inertia of the integrated multi-rotor unmanned aerial vehicle in the air when the integrated multi-rotor unmanned aerial vehicle performs pitching and rolling actions, so that the maneuvering performance of the integrated multi-rotor unmanned aerial vehicle in the rolling and pitching directions is weaker, and the response time of gesture adjustment is relatively longer.
The integrated structure of the integrated multi-rotor unmanned aerial vehicle results in some large-sized multi-rotor unmanned aerial vehicles being more inconvenient to transport and carry when performing flight tasks.
Disclosure of Invention
The utility model provides a hinged multi-rotor unmanned aerial vehicle, and aims to solve the problem that in the prior art, a rotor system of the multi-rotor unmanned aerial vehicle is rigidly connected with a machine body, so that the stability of the machine body structure is poor.
In order to solve the technical problems, the utility model adopts the following technical scheme:
the hinged multi-rotor unmanned aerial vehicle comprises a propeller system and a fuselage, wherein a universal hinge for enabling the fuselage to be in a horizontal state is arranged between the propeller system and the fuselage;
the universal hinge comprises an upper hinge seat arranged on the propeller system, a lower hinge seat arranged on the machine body and a middle hinge arranged between the upper hinge seat and the lower hinge seat;
the middle hinge is rotatably connected around a first horizontal shaft relative to the upper hinge support, the lower hinge support is rotatably connected around a second horizontal shaft relative to the middle hinge, and the first horizontal shaft is perpendicular to the second horizontal shaft.
The further improved scheme is as follows: the lower side of the upper hinged support is provided with an upper connecting sheet, and the upper end of the middle hinge is rotatably connected to the upper connecting sheet.
Based on the technical scheme: by arranging the upper connecting sheet, the upper hinge support and the middle hinge are easy to connect.
The further improved scheme is as follows: the upper connecting pieces are two, an upper connecting cavity is formed between the two upper connecting pieces, a part of the middle hinge is positioned in the upper connecting cavity, and the middle hinge is rotationally connected in the upper connecting cavity through an upper rotating shaft.
Based on the technical scheme: by arranging two upper connecting sheets, the middle hinge and the upper hinge support have more stable connection performance. By arranging the upper rotating shaft, the middle hinge can flexibly rotate relative to the upper hinge support.
The further improved scheme is as follows: the middle hinge is provided with an upper shaft hole matched with the upper rotating shaft, a copper bush is arranged in the upper shaft hole, and the copper bush arranged in the upper shaft hole is positioned between the upper shaft hole and the upper rotating shaft.
Based on the technical scheme: through setting up the copper bush, go up pivot and last shaft hole indirect contact to make the difficult wearing and tearing of last pivot, last shaft hole.
The further improved scheme is as follows: the lower end of the middle hinge is provided with a lower connecting sheet, and the lower hinge seat is rotatably connected to the lower connecting sheet.
Based on the technical scheme: by arranging the lower connecting sheet, the middle hinge and the lower hinge support are easy to assemble.
The further improved scheme is as follows: the lower connecting pieces are two, a lower connecting cavity is formed between the two lower connecting pieces, a part of the lower hinged support is positioned in the lower connecting cavity, and the lower hinged support is rotationally connected in the lower connecting cavity through a lower rotating shaft.
Based on the technical scheme: by arranging two lower connecting sheets, the lower hinged support is more stable in connection with the middle hinge.
The further improved scheme is as follows: the lower hinge support is provided with a lower shaft hole matched with the lower rotating shaft, a copper bush is arranged in the lower shaft hole, and the copper bush arranged in the lower shaft hole is positioned between the lower shaft hole and the lower rotating shaft.
Based on the technical scheme: through setting up the copper bush, lower pivot and lower shaft hole do not direct contact to make lower pivot and lower shaft hole be difficult for wearing and tearing.
The further improved scheme is as follows: an elastic rubber pad is arranged between the lower hinged support and the machine body, and an elastic rubber pad is arranged between the upper hinged support and the propeller system.
Based on the technical scheme: through setting up elastic rubber pad, lower hinge support does not contact with fuselage direct contact to make the not fragile fuselage of lower hinge support. Meanwhile, the elastic rubber pad can effectively absorb vibration brought by the propeller system to the machine body in the middle of flight.
The further improved scheme is as follows: the propeller system comprises four propellers.
The further improved scheme is as follows: the underside of the fuselage is provided with landing gear.
The beneficial effects of the utility model are as follows:
1. the rotor system of the integrated multi-rotor unmanned aerial vehicle is directly and rigidly connected with the main body through the main rod, so that the body posture of the integrated multi-rotor unmanned aerial vehicle can be integrally inclined when the integrated multi-rotor unmanned aerial vehicle flies in the air or maneuvers, and the connecting mode can not keep the stability of the load during the flying. The propeller system of the articulated multi-rotor unmanned aerial vehicle can reduce or even eliminate the inclination of the unmanned aerial vehicle caused by the posture adjustment of the articulated multi-rotor unmanned aerial vehicle when the articulated multi-rotor unmanned aerial vehicle flies in the air through the articulated form of the universal hinge structure and the fuselage, thereby ensuring the stability of the fuselage when the fuselage flies in the air at a high speed or maneuvers, enabling the propeller system to carry some equipment with higher requirements on stability, and increasing the functionality and the universality of the multi-rotor unmanned aerial vehicle.
2. Compared with the traditional wind-resistant mode that the whole machine is driven by the propeller system to generate lateral component force by the whole machine tilting of the integrated multi-rotor unmanned aerial vehicle, the hinged multi-rotor unmanned aerial vehicle provided by the utility model can generate lateral component force against wind force by independently tilting the propeller system while keeping the stability of the body when flying in windy weather, without driving the whole machine to tilt, thereby saving the power of a motor, increasing the lateral component force which can be provided by the hinged multi-rotor unmanned aerial vehicle when resisting wind, and improving the wind-resistant capability of the hinged multi-rotor unmanned aerial vehicle.
3. The universal hinge structure can enable a movable space with a certain angle between the hinged multi-rotor unmanned aerial vehicle body and the propeller system, and the propeller system is only required to be inclined by controlling the rotating speed of the motor instead of driving the whole body to finish rapid maneuver when the hinged multi-rotor unmanned aerial vehicle is in maneuver accelerating flight, so that the pneumatic efficiency of the hinged multi-rotor unmanned aerial vehicle propeller system is improved, the power consumption is reduced, and the cruising ability of the hinged multi-rotor unmanned aerial vehicle is improved.
4. The transmission integrated multi-rotor unmanned aerial vehicle propeller system is rigidly fixedly connected with the machine body, so that vibration generated by motor work can directly act on the whole machine body, load can be influenced, and service life of the machine body structure can be reduced. According to the hinged multi-rotor unmanned aerial vehicle, when the universal hinge structure is installed, a layer of elastic rubber pad can be installed between the propeller system and the upper hinge seat and between the body and the lower hinge seat to play a role in vibration reduction and buffering, the influence on the structural stability of the body and mounting equipment when the hinged multi-rotor unmanned aerial vehicle flies can be effectively reduced, and the operation safety of the hinged multi-rotor unmanned aerial vehicle and the high-precision quality output of the equipment are greatly improved.
5. The integrated design of the integrated multi-rotor unmanned aerial vehicle makes the moment of inertia of the integrated multi-rotor unmanned aerial vehicle in the air when the integrated multi-rotor unmanned aerial vehicle performs pitching and rolling actions, so that the maneuvering performance of the integrated multi-rotor unmanned aerial vehicle in the rolling and pitching directions is weaker. According to the propeller system of the articulated multi-rotor unmanned aerial vehicle, through the articulated form of the universal hinge structure and the fuselage, the rotational inertia of the articulated multi-rotor unmanned aerial vehicle in rolling and pitching actions can be reduced when the articulated multi-rotor unmanned aerial vehicle flies in the air, the maneuvering performance of the articulated multi-rotor unmanned aerial vehicle in rolling and pitching directions is enhanced, and meanwhile, the response time of gesture adjustment is shortened.
6. The integral structure of the integrated multi-rotor unmanned aerial vehicle leads to inconvenience in transportation and carrying of some large-size multi-rotor unmanned aerial vehicles, and the universal hinge of the hinged multi-rotor unmanned aerial vehicle is a detachable structure, so that the hinged multi-rotor unmanned aerial vehicle is split into two parts by only dismantling one connecting bolt when a flight task is executed, and is convenient to transport and carry.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present utility model and should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for the users of the art.
Fig. 1 is a schematic view of an articulated multi-rotor unmanned aerial vehicle of the present utility model.
Fig. 2 is an exploded view of a gimbaled hinge in a hinged multi-rotor unmanned aerial vehicle of the present utility model.
Fig. 3 is a front view of a gimbaled hinge in an articulated multi-rotor unmanned aerial vehicle of the present utility model.
Fig. 4 is a left side view of a gimbaled hinge in an articulating multi-rotor unmanned aerial vehicle of the present utility model.
Fig. 5 is a schematic diagram of the attitude of the complete machine when the conventional integrated multi-rotor unmanned aerial vehicle is in the air and resistant to wind.
Fig. 6 is a schematic diagram of the attitude of the whole machine of the hinged multi-rotor unmanned aerial vehicle in the air during wind resistance.
The reference numerals in the figures illustrate:
1-a propeller system; 2-universal hinges; 3-fuselage; 4-landing gear; a 5-elastic rubber pad; 6-upper hinge support; 7-middle hinge; 8-copper bushing; 9-a lower hinge support; 10-hexagon socket head cap screw; 11-self-locking nuts; 12-washers; 13-connecting bolts.
Detailed Description
The technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the utility model. All other embodiments, which can be obtained by the user of the field without creative efforts, are included in the protection scope of the present utility model based on the embodiments of the present utility model.
Embodiment one:
referring to fig. 1 to 4, an articulated multi-rotor unmanned aerial vehicle comprises a rotor system 1 and a fuselage 3, wherein a universal hinge 2 for keeping the fuselage 3 in a horizontal state is arranged between the rotor system 1 and the fuselage 3;
the universal hinge 2 comprises an upper hinge seat 6 mounted on the propeller system 1, a lower hinge seat 9 mounted on the fuselage 3, and a middle hinge 7 arranged between the upper hinge seat 6 and the lower hinge seat 9;
the intermediate hinge 7 is rotatably connected with respect to the upper hinge 6 about a first horizontal axis, and the lower hinge 9 is rotatably connected with respect to the intermediate hinge 7 about a second horizontal axis, the first horizontal axis being perpendicular to the second horizontal axis.
Embodiment two:
referring to fig. 1 to 4, in order to make the universal hinge 2 have higher stability, the universal hinge 2 is not easily damaged during use, and the above embodiments are based on: an upper connecting sheet is arranged on the lower side of the upper hinged support 6, and the upper end of the middle hinge 7 is rotatably connected to the upper connecting sheet.
The upper connecting pieces are two, an upper connecting cavity is formed between the two upper connecting pieces, a part of the middle hinge 7 is positioned in the upper connecting cavity, and the middle hinge 7 is rotatably connected in the upper connecting cavity through an upper rotating shaft.
The middle hinge 7 is provided with an upper shaft hole matched with the upper rotating shaft, a copper bush 8 is arranged in the upper shaft hole, and the copper bush 8 arranged in the upper shaft hole is positioned between the upper shaft hole and the upper rotating shaft.
The lower end of the middle hinge 7 is provided with a lower connecting sheet, and the lower hinge support 9 is rotatably connected to the lower connecting sheet.
The lower connecting pieces are two, a lower connecting cavity is formed between the two lower connecting pieces, a part of the lower hinged support 9 is positioned in the lower connecting cavity, and the lower hinged support 9 is rotatably connected in the lower connecting cavity through a lower rotating shaft.
The lower hinge support 9 is provided with a lower shaft hole matched with the lower rotating shaft, a copper bush 8 is arranged in the lower shaft hole, and the copper bush 8 arranged in the lower shaft hole is positioned between the lower shaft hole and the lower rotating shaft.
Embodiment III:
referring to fig. 1 to 4, in order to alleviate the vibration of the fuselage 3 caused by the propeller system 1, the above embodiments are based on: an elastic rubber pad 5 is arranged between the lower hinge seat 9 and the main body 3, and an elastic rubber pad 5 is arranged between the upper hinge seat 6 and the propeller system 1. The movable hinge structure plays a role in buffering an elastic rubber pad 5 which can be installed at the installation joint of the movable hinge structure and the propeller system 1 and the machine body 3, so that vibration brought to the machine body 3 and equipment in the machine body 3 during the flight of the unmanned aerial vehicle can be effectively reduced, and the service life of the unmanned aerial vehicle is prolonged.
The propeller system 1 comprises four propellers. The underside of the fuselage 3 is provided with landing gear 4. The landing gear 4 is a landing gear 4 as is conventional in the art.
The multi-rotor arrangement of the propeller system hinged to the fuselage comprises: the rotor system 1 of the upper half; a universal hinge 2 in the middle part; the fuselage 3 of the lower half and the landing gear 4. The universal hinge 2 is composed of an elastic rubber pad 5, an upper hinge seat 6, a middle hinge 7, a copper bush 8, a lower hinge seat 9, a hexagon socket head cap screw 10, a self-locking nut 11, a gasket 12 and a connecting bolt 13, and the universal hinge 2 has the advantages of simple structure, large steering angle, smooth steering, strong bearing capacity, compact structure, convenient disassembly and assembly and the like. Compared with the traditional integrated multi-rotor unmanned aerial vehicle, the hinged multi-rotor unmanned aerial vehicle has the advantages that a set of universal hinge 2 structure is additionally arranged between the propeller system and the machine body when the propeller system moves upwards, so that the propeller system and the machine body form a hinged structure.
Compared with the traditional unmanned aerial vehicle layout mode, the utility model adopts the propeller system 1 to be connected with the airframe 3 through the universal hinge 2, so that the hinged multi-rotor unmanned aerial vehicle can maintain the airframe 3 to be stable through the dead weight when doing course action in the air. The structure of the universal hinge 2 of the propeller system 1 and the fuselage 3 can enable the articulated multi-rotor unmanned aerial vehicle to turn more flexibly in the air. The articulated multi-rotor unmanned aerial vehicle can complete steering only by tilting the rotor system 1 when rapidly maneuvering in the air, so that the rotor system 1 of the articulated multi-rotor unmanned aerial vehicle has the advantages of increasing the pneumatic and gesture rolling moment efficiency, reducing the power consumption and increasing the cruising ability.
When the propeller system 1 and the universal hinge 2 are installed, a layer of elastic rubber pad 5 can be installed between the propeller system 1 and the upper hinge seat 6 and between the machine body 3 and the lower hinge seat 9 to play a role in vibration reduction and buffering, vibration brought to the machine body 3 and mounting when the hinged multi-rotor unmanned aerial vehicle flies can be effectively reduced, the service life of the hinged multi-rotor unmanned aerial vehicle is prolonged, and the operation safety of the hinged multi-rotor unmanned aerial vehicle and the high-precision quality output of equipment are improved. The articulated multi-rotor unmanned aerial vehicle is of a two-section detachable structure, and can be detached during transportation to separate the propeller system 1 from the machine body 3 so as to facilitate transportation.
The joint of the propeller system 1 and the machine body 3 of the articulated multi-rotor unmanned aerial vehicle is of a quick-dismantling structure, and the load or the part of the propeller system 1 can be quickly replaced according to different task demands.
The universal joint 2 is provided with a certain angular limitation. In a static state, the gravity center of the articulated multi-rotor unmanned aerial vehicle can be prevented from changing due to the inclination of the propeller system 1, so that the articulated multi-rotor unmanned aerial vehicle can be inclined; it is also possible to prevent the fuselage 3 from colliding with the propeller system 1 during this wide-angle maneuver.
The universal hinge 2 has a certain damping sense, so that the propeller system 1 can keep a stable state during take-off and landing, the operation difficulty of pilots is reduced, and the safety usability of the hinged multi-rotor unmanned aerial vehicle is improved.
The working principle of the utility model is as follows:
referring to fig. 5 to 6, when performing a flight mission, the upper hinge 6, the middle hinge 7, the copper bush 8, the lower hinge 9, the self-locking nut 11, the washer 12, and the connecting bolt 13 form a universal hinge 2 structure, and the assembly of the articulated multi-rotor unmanned aerial vehicle can be completed by fixing the upper hinge 6 on the lower surface of the rotor system 1 and the lower hinge 9 on the upper surface of the fuselage 3 by installing the hexagon socket head cap screw 10. The universal hinge 2 is of a detachable structure; the multi-rotor unmanned aerial vehicle can be divided into two parts by removing one of two connecting bolts of the universal hinge 2 structure in the transportation process, and if the connecting bolt 13 between the upper hinge seat 6 and the middle hinge 7 is removed, the hinged multi-rotor unmanned aerial vehicle can be divided into a first part of propeller system 1, an upper hinge seat 6 and a second part of airframe 3, a landing gear 4, a middle hinge 7 and a lower hinge seat 9; if the connecting bolts 13 between the intermediate hinge 7 and the lower hinge support 9 are removed, the first part comprises the rotor system 1, the upper hinge support 6 and the intermediate hinge 7. And when the multi-rotor unmanned aerial vehicle arrives at a destination and needs to be executed, the multi-rotor unmanned aerial vehicle can be assembled only by reinstalling and connecting the dismantled connecting bolts.
The assembled propeller system 1 and the machine body 3 can enable the hinged multi-rotor unmanned aerial vehicle to obtain free tilting capability in a certain angle in the vertical direction through the universal hinge 2 structure, when the multi-rotor unmanned aerial vehicle flies in the air to do pitching rolling motion, the universal hinge 2 can enable the upper half part and the lower half part of the multi-rotor unmanned aerial vehicle to have tilting capability in a certain angle in operation, namely the upper half part of the multi-rotor unmanned aerial vehicle can tilt in a certain angle in pitching rolling motion, and at the moment, the lower half part of the multi-rotor unmanned aerial vehicle can keep stable in the vertical direction through dead weight, so that the defect that the machine body and the propeller system need to tilt simultaneously in pitching rolling motion of the traditional integrated multi-rotor unmanned aerial vehicle is avoided.
And because the connecting bolts 13 in the universal hinge 2 play a limiting role, the relative positions of the machine body 3 and the propeller system 1 of the multi-rotor unmanned aerial vehicle can be kept unchanged to act together when the multi-rotor unmanned aerial vehicle performs pivoting or steering actions.
Meanwhile, when the articulated multi-rotor unmanned aerial vehicle is assembled, a layer of elastic rubber pad 5 can be arranged between the propeller system 1 and the upper hinged support 6 and between the machine body 3 and the lower hinged support 9, so that the vibration brought to the machine body 3 during the operation of the propeller system 1 in the middle of flight can be effectively absorbed.
The utility model is not limited to the above-mentioned alternative embodiments, on the premise of not contradicting each other, can combine arbitrarily between every scheme; any person who is in the light of the present utility model can obtain other products in various forms, however, any changes in shape or structure are within the scope of the present utility model as defined by the claims.
Claims (10)
1. The utility model provides a many rotor unmanned aerial vehicle of articulated, its characterized in that: the device comprises a propeller system and a machine body, wherein a universal hinge for keeping the machine body in a horizontal state is arranged between the propeller system and the machine body;
the universal hinge comprises an upper hinge seat arranged on the propeller system, a lower hinge seat arranged on the machine body and a middle hinge arranged between the upper hinge seat and the lower hinge seat;
the middle hinge is rotatably connected around a first horizontal shaft relative to the upper hinge support, the lower hinge support is rotatably connected around a second horizontal shaft relative to the middle hinge, and the first horizontal shaft is perpendicular to the second horizontal shaft.
2. The articulated multi-rotor unmanned aerial vehicle of claim 1, wherein: the lower side of the upper hinged support is provided with an upper connecting sheet, and the upper end of the middle hinge is rotatably connected to the upper connecting sheet.
3. The articulated multi-rotor unmanned aerial vehicle of claim 2, wherein: the upper connecting pieces are two, an upper connecting cavity is formed between the two upper connecting pieces, a part of the middle hinge is positioned in the upper connecting cavity, and the middle hinge is rotationally connected in the upper connecting cavity through an upper rotating shaft.
4. A hinged multi-rotor unmanned aerial vehicle according to claim 3, wherein: the middle hinge is provided with an upper shaft hole matched with the upper rotating shaft, a copper bush is arranged in the upper shaft hole, and the copper bush arranged in the upper shaft hole is positioned between the upper shaft hole and the upper rotating shaft.
5. The articulated multi-rotor unmanned aerial vehicle of claim 1, wherein: the lower end of the middle hinge is provided with a lower connecting sheet, and the lower hinge seat is rotatably connected to the lower connecting sheet.
6. The articulated multi-rotor unmanned aerial vehicle of claim 5, wherein: the lower connecting pieces are two, a lower connecting cavity is formed between the two lower connecting pieces, a part of the lower hinged support is positioned in the lower connecting cavity, and the lower hinged support is rotationally connected in the lower connecting cavity through a lower rotating shaft.
7. The articulated multi-rotor unmanned aerial vehicle of claim 6, wherein: the lower hinge support is provided with a lower shaft hole matched with the lower rotating shaft, a copper bush is arranged in the lower shaft hole, and the copper bush arranged in the lower shaft hole is positioned between the lower shaft hole and the lower rotating shaft.
8. The articulated multi-rotor unmanned aerial vehicle of claim 1, wherein: an elastic rubber pad is arranged between the lower hinged support and the machine body, and an elastic rubber pad is arranged between the upper hinged support and the propeller system.
9. The articulated multi-rotor unmanned aerial vehicle of claim 1, wherein: the rotor system includes four rotors.
10. The articulated multi-rotor unmanned aerial vehicle of claim 1, wherein: the underside of the fuselage is provided with landing gear.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322657917.6U CN220764717U (en) | 2023-09-28 | 2023-09-28 | Articulated multi-rotor unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322657917.6U CN220764717U (en) | 2023-09-28 | 2023-09-28 | Articulated multi-rotor unmanned aerial vehicle |
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| CN220764717U true CN220764717U (en) | 2024-04-12 |
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| CN202322657917.6U Active CN220764717U (en) | 2023-09-28 | 2023-09-28 | Articulated multi-rotor unmanned aerial vehicle |
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| Country | Link |
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| CN (1) | CN220764717U (en) |
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- 2023-09-28 CN CN202322657917.6U patent/CN220764717U/en active Active
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