CN113978710A - Many rotor unmanned aerial vehicle of power moduleization - Google Patents
Many rotor unmanned aerial vehicle of power moduleization Download PDFInfo
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- CN113978710A CN113978710A CN202111251413.3A CN202111251413A CN113978710A CN 113978710 A CN113978710 A CN 113978710A CN 202111251413 A CN202111251413 A CN 202111251413A CN 113978710 A CN113978710 A CN 113978710A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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Abstract
The application discloses a power modularized multi-rotor unmanned aerial vehicle, which relates to the technical field of unmanned aerial vehicles, in particular to a power modularized multi-rotor unmanned aerial vehicle, wherein an even number of rotor fixing rod positioning holes are uniformly and symmetrically formed in the periphery of a machine body on the basis of the conventional multi-rotor unmanned aerial vehicle, and rotor fixing rods are detachably and fixedly arranged in the rotor fixing rod positioning holes; the rotor wing fixing rod is of a long rod-shaped structure, one end of the rotor wing fixing rod is inserted into the rotor wing fixing rod positioning hole, and the other end of the rotor wing fixing rod is fixedly provided with the motor fixing frame; the motor is fixedly arranged in the motor fixing frame, and the output rotating shaft of the motor is fixedly provided with a propeller. Such structure can be according to the different weight of unmanned aerial vehicle organism, selects the motor of different motor quantity and rotatory different power, realizes that an organism corresponds the rotor that multiple power is different, can reduce the cost of preparation, also can reduce the inconvenience that unmanned aerial vehicle that needs purchase, storage, carry a large amount of different models brought when carrying out the task.
Description
Technical Field
The application relates to the technical field of unmanned aerial vehicles, especially, relate to a many rotor unmanned aerial vehicle of power moduleization.
Background
An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. Drones tend to be more suitable for tasks that are too "fool, dirty, or dangerous" than are manned aircraft. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle + the industry application is really just needed by the unmanned aerial vehicle; the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand the industrial application and develop the unmanned aerial vehicle technology.
Present many rotor unmanned aerial vehicle mostly is organism and wing design with one body, and organism and rotor are unable selection or change promptly, but when in actual use, often need choose unmanned aerial vehicle of different volumes, different power for use according to the work task of difference, has consequently increased the expenditure cost of machine purchase.
Disclosure of Invention
In order to solve the above problems, the present application is implemented by the following technical solutions:
a power modularized multi-rotor unmanned aerial vehicle comprises a body, a rotor fixing rod and a motor;
the machine body is of a cylindrical structure, even rotor wing fixing rod positioning holes are uniformly and symmetrically formed in the periphery of the machine body, and the rotor wing fixing rods are detachably and fixedly arranged in the rotor wing fixing rod positioning holes;
the rotor wing fixing rod is of a long rod-shaped structure, one end of the rotor wing fixing rod is inserted into the rotor wing fixing rod positioning hole, and the other end of the rotor wing fixing rod is fixedly provided with a motor fixing frame;
the motor fixing frame is internally and fixedly provided with a motor, and an output rotating shaft of the motor is fixedly provided with a propeller. Such structure can be according to the different weight of unmanned aerial vehicle organism, selects the motor of different motor quantity and rotatory different power. When normal use, if the unmanned aerial vehicle organism is lighter, perhaps the load is not many, then can select 4 rotor dead levers of symmetry and the motor of less power can as power, when the unmanned aerial vehicle organism is heavier, perhaps when the load is great, then extract from rotor dead lever locating hole on the organism through the motor with less power and the rotor dead lever that corresponds, and it is bigger to change the motor power, the another set of rotor that the screw diameter is longer, just so can realize that a organism corresponds the different rotor of multiple power, can reduce the cost of preparation, need purchase when also can reducing the executive task, save, carry the inconvenience that the unmanned aerial vehicle of a large amount of different models brought. The connection mode of organism and rotor fixed rod here can adopt the most traditional bolt, screw connection, also can adopt convenient buckle mode to connect, and the buckle mode has the multiple, for example adopts two arrow barb cooperations mode etc..
Preferably, the motor is a coreless motor. The hollow cup motor belongs to a direct current permanent magnet servo and control motor, and can also be classified as a micro special motor. The coreless motor mainly has the following characteristics:
1. energy-saving characteristic: the energy conversion efficiency is very high, the maximum efficiency is generally over 70 percent, and partial products can reach over 90 percent.
2. Control characteristics: the starting and the braking are rapid, the response is extremely rapid, the mechanical time constant is less than 28 milliseconds, and partial products can reach within 10 milliseconds; under the high-speed operation state in the recommended operation area, the rotating speed can be flexibly adjusted conveniently.
3. Dragging characteristics: the running stability is very reliable, the fluctuation of the rotating speed is very small, and the fluctuation of the rotating speed of the miniature motor can be easily controlled within 2 percent.
In addition, the energy density of the coreless motor is greatly improved, and compared with an iron core motor with the same power, the weight and the volume of the coreless motor are reduced by 1/3-1/2.
Preferably, the machine body is made by 3D printing and is of a hollow hexagonal filling structure. Can guarantee like this that the colleague of unmanned aerial vehicle organism mechanical strength satisfies the requirement of external dimension to its weight of greatly reduced is favorable to unmanned aerial vehicle's energy-conservation, improves its duration.
Preferably, the cross section of the rotor wing fixing rod is of a rectangular structure; the cross section is rectangular structure and is convenient to install, the stress is better, and the cross section is round bar, so that the device has the advantage of being not easy to rotate.
The rotor dead lever adopts 3D to print and makes.
Preferably, the other end of the rotor fixing rod is fixedly provided with a motor fixing frame, the motor fixing frame is of a cylindrical container structure with an open top, and the motor is detachably arranged in the motor fixing frame. Rotor dead lever on the current most unmanned aerial vehicle is usually made motor an organic whole, though can save certain material cost like this, but the motor is electric element, breaks down for static part more easily, when the motor breaks down, the form of integrative structure just can't be changed the motor alone, must the complete machine or whole rotor dead lever change together, has just so increased the cost of changing the maintenance. Adopt can dismantle in the motor mount to be provided with the mode of motor can only change the motor that breaks down when the motor breaks down just can, and the process of changing is very simple and convenient moreover: the fixed omega-shaped clamp spring or screw fixing mode of the motor can be adopted, so that the later maintenance cost of the multi-rotor unmanned aerial vehicle can be reduced.
Preferably, a plug is arranged at one end of the rotor fixing rod, and the plug is electrically connected with the motor;
and a socket corresponding to the plug is arranged in the rotor wing fixing rod positioning hole, and the socket is electrically connected with a control circuit arranged on the machine body. The purpose of design plug and socket is when dismouting rotor dead lever, also can realize the switch-on or the disconnection to motor control circuit simultaneously when the plug, just so can further increase the efficiency of changing the rotor dead lever.
Preferably, the plug is disposed at the center of one end of the rotor fixing rod. A groove is formed in the end face of one end of the rotor wing fixing rod, and an electrode is arranged in the groove, so that collision of the electrode can be reduced when the rotor wing fixing rod is stored and transported, and the electrode is effectively protected.
Preferably, one end of the rotor wing fixing rod is further provided with a screw positioning hole, and the screw positioning hole penetrates through the rotor wing fixing rod from top to bottom;
the bottom of the machine body is provided with threaded holes corresponding to the screw positioning holes from bottom to top, and the threaded holes correspond to the rotor wing fixing rod positioning holes one to one;
and the internal thread of the threaded hole is provided with a fixing screw. Relatively light unmanned aerial vehicle only adopts buckle connected mode can realize fixing, but heavier unmanned aerial vehicle is in order to guarantee safety, when inserting the rotor dead lever, in order to fix better, passes screw hole, rotor dead lever locating hole and screw locating hole through utilizing the screw and can fix the rotor dead lever well.
On the basis of the existing multi-rotor unmanned aerial vehicle, an even number of rotor wing fixing rod positioning holes are uniformly and symmetrically formed in the periphery of a machine body, and the rotor wing fixing rods are detachably and fixedly arranged in the rotor wing fixing rod positioning holes; the rotor wing fixing rod is of a long rod-shaped structure, one end of the rotor wing fixing rod is inserted into the rotor wing fixing rod positioning hole, and the other end of the rotor wing fixing rod is fixedly provided with a motor fixing frame; the motor fixing frame is internally and fixedly provided with a motor, and an output rotating shaft of the motor is fixedly provided with a propeller. Such structure can be according to the different weight of unmanned aerial vehicle organism, selects the motor of different motor quantity and rotatory different power, realizes that an organism corresponds the rotor that multiple power is different, can reduce the cost of preparation, also can reduce the inconvenience that unmanned aerial vehicle that needs purchase, storage, carry a large amount of different models brought when carrying out the task.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the embodiment provided in the present application;
FIG. 2 is a front view of an embodiment provided herein;
FIG. 3 is a top view of an embodiment provided herein;
FIG. 4 is a left side view of an embodiment provided herein;
FIG. 5 is a bottom view of an embodiment provided herein;
figure 6 is a schematic view of an embodiment of the present application after the airframe has been separated from a portion of the rotor securing lever.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the embodiments of the present application will be described clearly and completely with reference to fig. 1 to 6 of the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Thus, the following detailed description of the embodiments of the present application, as presented in the figures, is not intended to limit the scope of the claimed application, but is merely representative of selected embodiments of the application. In the description of the present application, it is to be understood that, unless otherwise specifically stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can include, for example, fixed connections, detachable connections, or integral parts; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate. Further, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact of the first and second features, or may comprise direct contact of the first and second features through another feature in between. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
A power modularized multi-rotor unmanned aerial vehicle comprises a body 1, a rotor fixing rod 2 and a motor 3. The aircraft body 1 is of a cylindrical structure, even rotor wing fixing rod positioning holes 10 are uniformly and symmetrically formed in the periphery of the aircraft body 1, and the rotor wing fixing rods 2 are detachably and fixedly arranged in the rotor wing fixing rod positioning holes 10. In this embodiment, the rotor fixing rod positioning holes 10 are provided in 6 numbers, and each is spaced by 60 degrees.
Rotor dead lever 2 is rectangular shaft-like structure, insert the one end of rotor dead lever 2 in rotor dead lever locating hole 10, the other end of rotor dead lever 2 is fixed and is provided with motor mount 22. The motor fixing frame 22 is internally and fixedly provided with a motor 3, and an output rotating shaft of the motor 3 is fixedly provided with a propeller. The motor 3 is a hollow cup motor. The hollow cup motor belongs to a direct current permanent magnet servo and control motor, and can also be classified as a micro special motor. The coreless motor mainly has the following characteristics: 1. energy-saving characteristic: the energy conversion efficiency is very high, the maximum efficiency is generally above 70%, and the iron core motor with the maximum efficiency of above 90% can be generally above 70% for partial products. 2. Control characteristics: the starting and braking are rapid, the response is very quick, the mechanical time constant is less than 28 milliseconds, and the iron core motor can reach more than 100 milliseconds in 10 milliseconds in partial products. Under the high-speed operation state in the recommended operation area, the rotating speed can be flexibly adjusted conveniently. 3. Dragging characteristics: the running stability is very reliable, the fluctuation of the rotating speed is very small, and the fluctuation of the rotating speed of the miniature motor can be easily controlled within 2 percent. In addition, the energy density of the coreless motor is greatly improved, and compared with an iron core motor with the same power, the weight and the volume of the coreless motor are reduced by 1/3-1/2.
A many rotor unmanned aerial vehicle can form a complete set and set up rotor dead lever 2 of multiple different length and different motor power. The length is different, is in order to guarantee that screw length is different, can normally work, can not mutual interference.
Such structure can be according to the different weight of unmanned aerial vehicle organism, selects the motor of different motor quantity and rotatory different power. During normal use, if the unmanned aerial vehicle organism is lighter, perhaps the load is not many, then can select 4 rotor dead levers 2 of symmetry and the motor of less power can as power, when the unmanned aerial vehicle organism is heavier, perhaps when the load is great, then extract in rotor dead lever locating hole 10 on organism 1 through the motor with less power and rotor dead lever 2 that corresponds, and it is bigger to change motor power, the another set of rotor that the screw diameter is longer, just so can realize that a organism corresponds the different rotor of multiple power, can reduce the cost of preparation, also can reduce the inconvenience that the unmanned aerial vehicle that carries a large amount of different models brought when carrying out the task and need purchase, save, carry. The connection mode of the machine body 1 and the rotor wing fixing rod 2 can adopt the most traditional bolt and screw connection, and can also adopt a convenient buckling mode, and the buckling mode has multiple modes, such as a mode of matching two arrow barbs and the like.
In an embodiment, in order to reduce the overall weight and increase the cruising ability of the drone, the body 1 is made by 3D printing, and is in a hollow hexagonal filling structure. Can guarantee like this that the colleague of unmanned aerial vehicle organism mechanical strength satisfies the requirement of external dimension to its weight of greatly reduced is favorable to unmanned aerial vehicle's energy-conservation, improves its duration. The cross section of the rotor wing fixing rod 2 is of a rectangular structure. The cross section is rectangular structure and is convenient to install, the stress is better, and the cross section is round bar, so that the device has the advantage of being not easy to rotate. Rotor dead lever 2 adopts 3D to print and makes.
In an embodiment, a motor fixing frame 22 is fixedly arranged at the other end of the rotor fixing rod 2, the motor fixing frame 22 is a cylindrical container structure with an open top, and the motor 3 is detachably arranged in the motor fixing frame 22. Rotor dead lever 2 on the current majority unmanned aerial vehicle makes motor an organic whole usually, though can save certain material cost like this, but the motor is electric element, breaks down for static part more easily, when the motor breaks down, the form of integrative structure just can't be changed the motor alone, must the complete machine or whole rotor dead lever 2 change together, has just so increased the cost of changing the maintenance. By adopting the mode that the motor 3 is detachably arranged in the motor fixing frame 22, when the motor fails, only the failed motor can be replaced, and the replacement process is very simple and convenient: the fixed omega-shaped clamp spring or screw fixing mode of the motor can be adopted, so that the later maintenance cost of the multi-rotor unmanned aerial vehicle can be reduced. One end of the rotor fixing rod 2 is provided with a plug 20, and the plug 20 is electrically connected with the motor 3. And a socket corresponding to the plug 20 is arranged in the rotor wing fixing rod positioning hole 10, and the socket is electrically connected with a control circuit arranged on the machine body 1. The purpose of designing plug 20 and socket is to facilitate when dismouting rotor dead lever 2, also can realize the switch-on or the disconnection to motor control circuit simultaneously when the plug, just so can further increase the efficiency of changing rotor dead lever 2. The plug 20 is provided at the center of one end of the rotor fixing lever 2. A groove is formed in the end face of one end of the rotor wing fixing rod 2, and an electrode is arranged in the groove, so that collision of the electrode can be reduced when the rotor wing fixing rod 2 is stored and transported, and the electrode is effectively protected.
In an embodiment, one end of the rotor fixing rod 2 is further provided with a screw positioning hole 21, and the screw positioning hole 21 penetrates through the rotor fixing rod 2 from top to bottom. The bottom of the machine body 1 is provided with threaded holes 11 corresponding to the screw positioning holes 21 from bottom to top, and the threaded holes 11 correspond to the rotor wing fixing rod positioning holes 10 one to one. The screw thread of the threaded hole 11 is provided with a fixing screw. Comparatively light unmanned aerial vehicle only adopts buckle connected mode can realize fixing, but heavier unmanned aerial vehicle is in order to guarantee safety, when inserting rotor dead lever 2, for fixing better, can fix rotor dead lever 2 well through utilizing the screw to pass screw hole 11, rotor dead lever locating hole 10 and screw locating hole 21.
On present many rotor unmanned aerial vehicle's basis, even number rotor dead lever locating hole 10 has been seted up with the even symmetry in periphery of organism 1 to this application, can dismantle in rotor dead lever locating hole 10 fixedly be provided with rotor dead lever 2. Rotor dead lever 2 is rectangular shaft-like structure, insert the one end of rotor dead lever 2 in rotor dead lever locating hole 10, the other end of rotor dead lever 2 is fixed and is provided with motor mount 22. The motor fixing frame 22 is internally and fixedly provided with a motor 3, and an output rotating shaft of the motor 3 is fixedly provided with a propeller. Such structure can be according to the different weight of unmanned aerial vehicle organism, selects the motor of different motor quantity and rotatory different power, realizes that an organism corresponds the rotor that multiple power is different, can reduce the cost of preparation, also can reduce the inconvenience that unmanned aerial vehicle that needs purchase, storage, carry a large amount of different models brought when carrying out the task.
Claims (8)
1. A power modularized multi-rotor unmanned aerial vehicle is characterized by comprising a vehicle body (1), a rotor fixing rod (2) and a motor (3);
the machine body (1) is of a cylindrical structure, even rotor wing fixing rod positioning holes (10) are uniformly and symmetrically formed in the periphery of the machine body (1), and the rotor wing fixing rods (2) are detachably and fixedly arranged in the rotor wing fixing rod positioning holes (10);
the rotor wing fixing rod (2) is of a long rod-shaped structure, one end of the rotor wing fixing rod (2) is inserted into the rotor wing fixing rod positioning hole (10), and the other end of the rotor wing fixing rod (2) is fixedly provided with a motor fixing frame (22);
the motor fixing frame (22) is internally and fixedly provided with a motor (3), and an output rotating shaft of the motor (3) is fixedly provided with a propeller.
2. The power modular multi-rotor drone of claim 1, wherein:
the motor (3) is a hollow cup motor.
3. The power modular multi-rotor drone of claim 1, wherein:
the machine body (1) is made by 3D printing and is of a hollow hexagonal filling structure.
4. The power modular multi-rotor drone of claim 1, wherein:
the cross section of the rotor wing fixing rod (2) is of a rectangular structure;
the rotor wing fixing rod (2) is made by 3D printing.
5. The power modular multi-rotor drone of claim 4, wherein:
the other end of rotor dead lever (2) is fixed and is provided with motor mount (22), motor mount (22) are the open cylinder containment structure in top, can dismantle in this motor mount (22) and be provided with motor (3).
6. The power modular multi-rotor drone of claim 5, wherein:
a plug (20) is arranged at one end of the rotor wing fixing rod (2), and the plug (20) is electrically connected with the motor (3);
a socket corresponding to the plug (20) is arranged in the rotor wing fixing rod positioning hole (10), and the socket is electrically connected with a control circuit arranged on the machine body (1).
7. The power modular multi-rotor drone of claim 5, wherein:
the plug (20) is arranged in the center of one end of the rotor wing fixing rod (2).
8. The power modular multi-rotor drone of claim 4, wherein:
one end of the rotor wing fixing rod (2) is also provided with a screw positioning hole (21), and the screw positioning hole (21) penetrates through the rotor wing fixing rod (2) from top to bottom;
the bottom of the machine body (1) is provided with threaded holes (11) corresponding to the screw positioning holes (21) from bottom to top, and the threaded holes (11) correspond to the rotor wing fixing rod positioning holes (10) one by one;
the internal thread of the threaded hole (11) is provided with a fixing screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111251413.3A CN113978710A (en) | 2021-10-27 | 2021-10-27 | Many rotor unmanned aerial vehicle of power moduleization |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111251413.3A CN113978710A (en) | 2021-10-27 | 2021-10-27 | Many rotor unmanned aerial vehicle of power moduleization |
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| Publication Number | Publication Date |
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| CN113978710A true CN113978710A (en) | 2022-01-28 |
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| CN202111251413.3A Pending CN113978710A (en) | 2021-10-27 | 2021-10-27 | Many rotor unmanned aerial vehicle of power moduleization |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114889816A (en) * | 2022-07-13 | 2022-08-12 | 河南正大航空工业股份有限公司 | Big load unmanned aerial vehicle flight platform |
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| CN114889816A (en) * | 2022-07-13 | 2022-08-12 | 河南正大航空工业股份有限公司 | Big load unmanned aerial vehicle flight platform |
| CN114889816B (en) * | 2022-07-13 | 2022-10-28 | 河南正大航空工业股份有限公司 | Big load unmanned aerial vehicle flight platform |
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