CN209852579U - Multi-rotor aircraft - Google Patents
Multi-rotor aircraft Download PDFInfo
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- CN209852579U CN209852579U CN201920595187.2U CN201920595187U CN209852579U CN 209852579 U CN209852579 U CN 209852579U CN 201920595187 U CN201920595187 U CN 201920595187U CN 209852579 U CN209852579 U CN 209852579U
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Abstract
The utility model discloses a many rotor crafts, include: a housing; at least two upper rotary wing assemblies arranged at the upper part of the shell; at least two upper rotor assemblies circumferentially distributed about an outer side of the housing; and at least two lower rotor assemblies arranged at the lower part of the shell; at least two lower rotor assemblies are circumferentially distributed around the outside of the housing; on the horizontal projection plane, each upper rotor assembly of the at least two upper rotor assemblies and each lower rotor assembly of the at least two lower rotor assemblies are alternately arranged. The upper rotor wing assembly and the lower rotor wing assembly are arranged at intervals up and down, and the upper rotor wing assemblies and the lower rotor wing assemblies are alternately arranged, so that the wheelbase is reduced, the mutual interference between the upper rotor wing of the upper rotor wing assembly and the lower rotor wing of the adjacent lower rotor wing assembly is avoided, the overall weight of the rotor craft is reduced, and the endurance time is prolonged; and on the other hand, the processing cost is also reduced.
Description
Technical Field
The utility model relates to an aircraft technical field especially relates to a many rotor crafts.
Background
At present, the multi-rotor aircraft has the characteristics of simple and convenient operation, low cost, strong flexibility and suitability for ultra-low altitude flight, and is more and more widely applied to various industries, and the existing aircraft is mainly used in the fields of aerial photography, agriculture, plant protection, miniature self-timer, express delivery transportation, disaster relief, wild animal observation, infectious disease monitoring, geographical mapping, news reporting and the like.
In order to avoid the rotary wing aircraft body rotating due to the torque generated by the rotation of the rotary wing during flight, the rotary wing aircraft generally uses a plurality of rotary wings with different rotation directions to provide lift. The wheel base of a rotorcraft refers to the distance between the motor shafts that drive the rotors to rotate, located at opposite ends of a diagonal. The existing multi-rotor aircraft with rotors on the same horizontal plane has larger wheel base in order to avoid mutual interference between adjacent rotors, so that the overall weight of the rotor aircraft is increased, and the endurance time is reduced; on the other hand, the processing cost is also increased.
SUMMERY OF THE UTILITY MODEL
The utility model aims at the multi-rotor aircraft with the prior rotors on the same horizontal plane, the wheel base is arranged to be larger in order to avoid the mutual interference between the adjacent rotors, thus the whole weight of the rotor aircraft is increased, and the endurance time is reduced; on the other hand, the processing cost is also increased.
The utility model discloses a following technical scheme realizes: a multi-rotor aircraft comprising:
a housing;
at least two upper rotary wing assemblies arranged at the upper part of the shell; the at least two upper rotor assemblies are circumferentially distributed around the outside of the housing; and
at least two lower rotor assemblies arranged at the lower part of the shell; the at least two lower rotor assemblies are circumferentially distributed around the outside of the housing;
on a horizontal projection plane, each upper rotor assembly of the at least two upper rotor assemblies and each lower rotor assembly of the at least two lower rotor assemblies are alternately arranged;
on the horizontal projection plane, the first rotating surface of the adjacent upper rotor assembly is overlapped with the second rotating surface of the lower rotor assembly.
As a further improvement of the above technical solution, the upper rotor assembly includes a motor and an upper rotor connected to a rotation shaft of the motor in a horizontal direction, the lower rotor assembly includes a motor and a lower rotor connected to a rotation shaft of the motor in a horizontal direction, and a distance between a rotation surface of the upper rotor and a rotation surface of the lower rotor in a vertical direction is at least greater than the upper rotor or twice a width of the lower rotor.
As a further improvement of the above technical solution, an upper connecting arm that is matched with the upper rotor assembly and is used for connecting the upper rotor assembly is arranged on the upper portion of the housing, the upper connecting arm includes a first arm arranged on the upper portion of the housing and a second arm pivotally connected to the first arm, and an end portion of the second arm is provided with the upper rotor assembly.
As a further improvement of the above technical solution, the upper connecting arm may be folded downward, and an angle between the first arm and the second arm ranges from 90 to 180 degrees.
As a further improvement of the above technical solution, the lower portion of the housing is provided with a lower connecting arm which is matched with and used for connecting the lower rotor assembly, the lower connecting arm comprises a third arm arranged at the lower portion of the housing and a fourth arm pivotally connected with the third arm, and the lower rotor assembly is arranged in the end portion of the fourth arm.
As a further improvement of the above technical solution, the lower connecting arm may be folded upward, and an angle between the third arm and the fourth arm ranges from 90 to 180 degrees.
As a further improvement of the above technical solution, a lifting arm is pivotally connected to the fourth arm, and a range between the fourth arm and the lifting arm is 0 to 135 degrees.
As a further improvement of the above technical solution, the number of the upper rotor assemblies is the same as that of the lower rotor assemblies.
Herein, the term "horizontal projection plane" refers to a projection plane viewed from above looking down at an object. In this context, the term "plane of rotation" refers to the circular surface of the area of coverage of the blades of the rotors of a multi-rotor aircraft formed during rotation, on a horizontal plane of projection. Herein, the term "overlapping" two or more geometric figures occupy the same space.
Implement the utility model discloses a beneficial effect includes at least: the upper rotor wing assembly and the lower rotor wing assembly are arranged at intervals up and down, and the upper rotor wing assemblies and the lower rotor wing assemblies are alternately arranged, so that the wheelbase is reduced, the mutual interference between the upper rotor wing of the upper rotor wing assembly and the lower rotor wing of the adjacent lower rotor wing assembly is avoided, the overall weight of the rotor craft is reduced, and the endurance time is prolonged; and on the other hand, the processing cost is also reduced.
Drawings
Fig. 1 is a schematic structural view of an embodiment of the multi-rotor aircraft of the present invention;
fig. 2 is another schematic structural view of an embodiment of the multi-rotor aircraft of the present invention;
figure 3 is a top view of one embodiment of the multi-rotor aircraft of the present invention;
figure 4 is the structural schematic under the fold condition of an embodiment of the multi-rotor aircraft of the present invention.
Reference numerals:
multi-rotor craft-100;
a shell-10;
an upper rotor assembly-20; an upper rotor wing-21; -a motor-22; width-211; a first surface of rotation-23;
a lower rotor assembly-30; a lower rotor-31; a second surface of rotation-32;
the spacing is-40;
an upper connecting arm-50; a first arm-51; a second arm-52;
a lower connecting arm-60; a third arm-61; a fourth arm-62; a connecting plate-621;
a lift arm-70;
overlap region-80.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiment of the present invention, all other embodiments obtained by the person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1, a multi-rotor aircraft 100 includes: a housing 10; three upper rotor assemblies 20 provided at an upper portion of the housing 10; the three upper rotor assemblies 20 are circumferentially distributed around the outside of the casing 10; and three lower rotor assemblies 30 provided at the lower portion of the housing 10; the three lower rotor assemblies 30 are circumferentially distributed around the outside of the casing 10.
In this embodiment, the casing 10 is approximately hexagonal prism in shape, and a controller, an infrared sensing system, a GPS positioning system, a flight battery, and other devices are disposed in the casing 10.
Referring to fig. 3, in the horizontal projection plane, the upper rotor assemblies 20 of the three upper rotor assemblies 20 and the lower rotor assemblies 30 of the three lower rotor assemblies 30 are alternately arranged, and the three upper rotor assemblies 20 and the three lower rotor assemblies 30 are uniformly arranged around the outside of the housing 10.
Referring to fig. 3, on the horizontal projection plane, there is an overlapping area 80 between the first rotation surface 23 of the upper rotor assembly 20 and the second rotation surface 32 of the lower rotor assembly 30.
Referring to fig. 1 and 2, the upper rotor assembly 20 includes a motor 22 and an upper rotor 21 screwed to a vertical rotation shaft of an upper portion of the motor 22, the lower rotor assembly 30 includes a motor and a lower rotor 31 screwed to a vertical rotation shaft of an upper portion of the motor, and a vertical distance 40 between a first rotation surface 23 of the upper rotor 21 and a second rotation surface 32 of the lower rotor 31 is at least two times greater than a width 211 of the upper rotor 21 or the lower rotor 31.
Referring to fig. 1 and 3, since the upper rotor assembly 20 is located at the upper portion of the housing 10 and the lower rotor assembly 30 is located at the lower portion of the housing 10, the upper rotor 21 of the upper rotor assembly 20 and the lower rotor 31 of the adjacent lower rotor assembly 30 do not interfere with each other, so that the distance between the upper rotor assembly 20 located at one end of the diagonal line and the lower rotor assembly 30 located at the other end of the diagonal line on the horizontal projection plane can be shortened, thereby reducing the wheelbase, and reducing the overall weight of the rotorcraft, thereby increasing the endurance time; and on the other hand, the processing cost is also reduced.
In this embodiment, the upper rotor 21 and the lower rotor 31 have the same structure and shape, the upper rotor 21 and the lower rotor 31 are double-bladed paddles, and the distance 40 between the first rotating surface 23 and the second rotating surface 32 is twice the width 211 of the upper rotor 21 or the lower rotor 31, which is beneficial to reducing the interference of the airflow generated when the upper rotor 21 rotates on the lower rotor 31, thereby improving the flight efficiency of the multi-rotor aircraft.
Referring to fig. 1 and 4, the upper portion of the casing 10 is provided with three upper connecting arms 50 matching with the upper rotor assembly 20 and used for connecting the upper rotor assembly 20, the upper connecting arms 50 include a first arm 51 disposed at the upper portion of the casing 10 and a second arm 52 pivotally connected to the first arm 51, and the end of the second arm 52 is provided with the motor 22.
Referring to fig. 1 and 4, the upper connecting arm 50 can be folded downward, and the angle between the first arm 51 and the second arm 52 ranges from 90 to 180 degrees. For example, in this embodiment, in operation, the first arm 51 and the second arm 52 form an angle of 180 degrees, and when a rotorcraft needs to be stored, the second arm 52 is rotated downward by 90 degrees relative to the first arm 51, and the angle between the first arm 51 and the second arm 52 forms an angle of 90 degrees, so that the second arm 52 is close to the side wall of the housing 10.
Referring to fig. 1 and 4, a lower connecting arm 60 matched with the lower rotor assembly 30 and used for connecting the lower rotor assembly 30 is disposed at the lower portion of the housing 10, the lower connecting arm 60 includes a third arm 61 disposed at the lower portion of the housing 10 and a fourth arm 62 pivotally connected to the third arm 61, and the motor 22 is disposed in an end portion of the fourth arm 62.
Referring to fig. 1 and 4, the lower connecting arm 60 can be folded upwards, and the angle between the third arm 61 and the fourth arm 62 ranges from 90 to 180 degrees. For example, in this embodiment, when the aircraft is in operation, the angle between the third arm 61 and the fourth arm 62 is 180 degrees, and when the aircraft needs to be stored, the fourth arm 62 is rotated 90 degrees upward relative to the third arm 61, and the angle between the third arm 61 and the fourth arm 62 is 90 degrees, so that the fourth arm 62 is close to the side wall of the housing 10.
In this embodiment, go up the connecting arm 50 with the quantity of lower connecting arm 60 is three, go up the connecting arm 50 with the length of lower connecting arm 60 is the same, through with it is folding downwards to go up the connecting arm 50, and will the connecting arm 60 is folding upwards can realize taking in folding many rotor crafts 100 for holistic occupation volume reduces, strengthens the portability.
Referring to fig. 1, two parallel connection plates 621 are disposed at the bottom of the fourth arm 62, a lift arm 70 is pivotally connected between the two connection plates 621, an angle between the fourth arm 62 and the lift arm 70 ranges from 0 to 135 degrees, and preferably, an angle between the fourth arm 62 and the lift arm 70 ranges from 0 to 120 degrees.
In this embodiment, when the vehicle rises and falls, the fourth arm 62 and the lift arm 70 rotate relatively, and the angle between the fourth arm 62 and the lift arm 70 is 120 degrees; after the aircraft is raised, the landing arm 70 is pivoted upwardly closer to the fourth arm 62, and finally the angle between the fourth arm 62 and the landing arm 70 is 0 degrees.
The upper rotor assemblies 20 are the same number as the lower rotor assemblies 30. In this embodiment, from last down observation, it is three the last rotor 21 of last rotor subassembly 20 turns to clockwise, and is three the lower rotor 31 of lower rotor subassembly 30 turns to anticlockwise, go up rotor 21 with the rotation of lower rotor 31 is opposite, and the rotational speed is the same, can offset the moment of torsion, has solved the self-rotating problem of aircraft during operation for the aircraft is more steady.
The direction of rotation of the upper rotor 21 of the rotor assembly 20 may also be set to be counter-clockwise and the direction of rotation of the lower rotor 31 of the lower rotor assembly 30 may also be set to be clockwise. The number of the upper rotor assemblies 20 or the lower rotor assemblies 30 is also not limited to 3, and may be set to 2, 4, or the like, for example.
Implement the utility model discloses a beneficial effect includes at least:
1. the upper rotor wing assembly and the lower rotor wing assembly are arranged at intervals up and down, and the upper rotor wing assemblies and the lower rotor wing assemblies are alternately arranged, so that the wheelbase is reduced, the mutual interference between the upper rotor wing of the upper rotor wing assembly and the lower rotor wing of the adjacent lower rotor wing assembly is avoided, the overall weight of the rotor craft is reduced, and the endurance time is prolonged; and on the other hand, the processing cost is also reduced.
2. First rotatory face with interval between the second rotatory face does go up the rotor or the twice of the width of rotor down is favorable to reducing the upper strata the air current that produces when going up the rotor rotates is to the interference of rotor under the lower floor to improve many rotor crafts's flight efficiency.
3. Through will go up the linking arm and fold down, and will the linking arm is folding down and can be realized accomodating the folding of many rotor crafts for holistic occupation volume reduces, strengthens the portability.
In the description of the present invention, it is to be understood that the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art. In addition, in the description of the present invention, "a plurality" means two or more unless otherwise specified.
While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (8)
1. A multi-rotor aerial vehicle (100) comprising:
a housing (10);
at least two upper rotor wing assemblies (20) arranged at the upper part of the shell (10); the at least two upper rotor assemblies (20) are circumferentially distributed around the outside of the casing (10); and
at least two lower rotor assemblies (30) arranged at the lower part of the shell (10); the at least two lower rotor assemblies (30) are circumferentially distributed around the outside of the casing (10);
on a horizontal projection plane, each upper rotor assembly (20) of the at least two upper rotor assemblies (20) and each lower rotor assembly (30) of the at least two lower rotor assemblies (30) are alternately arranged;
on the horizontal projection plane, the first rotating surface (23) of the adjacent upper rotor assembly (20) is overlapped with the second rotating surface (32) of the lower rotor assembly (30).
2. The multi-rotor aerial vehicle (100) according to claim 1, wherein the upper rotor assembly (20) comprises a motor and an upper rotor (21) connected to the motor vertical axis, wherein the lower rotor assembly (30) comprises a motor and a lower rotor (31) connected to the motor vertical axis, and wherein a vertical separation (40) between a first plane of rotation of the upper rotor (21) and a second plane of rotation of the lower rotor (31) is at least two times greater than a width (211) of the upper rotor (21) or the lower rotor (31).
3. The multi-rotor aircraft (100) according to claim 1, wherein the upper portion of the casing (10) is provided with an upper connecting arm (50) matching the upper rotor assembly (20) and used for connecting the upper rotor assembly (20), the upper connecting arm (50) comprises a first arm (51) provided on the upper portion of the casing (10) and a second arm (52) pivotally connected to the first arm (51), and the end of the second arm (52) is provided with the upper rotor assembly (20).
4. The multi-rotor aerial vehicle (100) according to claim 3, wherein the upper connecting arm (50) is foldable downwards, the angle between the first arm (51) and the second arm (52) ranging from 90 to 180 degrees.
5. The multi-rotor aircraft (100) according to claim 1, wherein the lower portion of the casing (10) is provided with a lower connecting arm (60) matching the lower rotor assembly (30) and for connecting the lower rotor assembly (30), the lower connecting arm (60) comprising a third arm (61) provided at the lower portion of the casing (10) and a fourth arm (62) pivotally connected to the third arm (61), the lower rotor assembly (30) being provided in an end portion of the fourth arm (62).
6. Multi-rotor aerial vehicle (100) according to claim 5, wherein the lower connecting arm (60) is foldable upwards, the angle between the third arm (61) and the fourth arm (62) ranging from 90 to 180 degrees.
7. The multi-rotor aerial vehicle (100) of claim 5, wherein a landing arm (70) is pivotally connected to the fourth arm (62), and an angle between the fourth arm (62) and the landing arm (70) ranges from 0 to 135 degrees.
8. The multi-rotor aerial vehicle (100) of claim 1, wherein the upper rotor assemblies (20) are the same number as the lower rotor assemblies (30).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920595187.2U CN209852579U (en) | 2019-04-25 | 2019-04-25 | Multi-rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920595187.2U CN209852579U (en) | 2019-04-25 | 2019-04-25 | Multi-rotor aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN209852579U true CN209852579U (en) | 2019-12-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201920595187.2U Active CN209852579U (en) | 2019-04-25 | 2019-04-25 | Multi-rotor aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112224396A (en) * | 2020-10-20 | 2021-01-15 | 北京理工大学 | Six-rotor unmanned aerial vehicle with double-layer staggered arms and capable of being folded transversely |
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2019
- 2019-04-25 CN CN201920595187.2U patent/CN209852579U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112224396A (en) * | 2020-10-20 | 2021-01-15 | 北京理工大学 | Six-rotor unmanned aerial vehicle with double-layer staggered arms and capable of being folded transversely |
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