CN214930595U

CN214930595U - Multi-rotor aircraft

Info

Publication number: CN214930595U
Application number: CN202120548428.5U
Authority: CN
Inventors: 郭盛家; 吴琼伟; 熊荣明
Original assignee: SZ DJI Technology Co Ltd
Current assignee: SZ DJI Technology Co Ltd
Priority date: 2021-03-16
Filing date: 2021-03-16
Publication date: 2021-11-30
Anticipated expiration: 2031-03-16

Abstract

The utility model discloses a multi-rotor aircraft, which comprises an aircraft body, an aircraft arm, a first rotor power device and a second rotor power device, wherein the aircraft body comprises an aircraft nose and a tail opposite to the aircraft nose, the aircraft arm is mechanically coupled with the aircraft body, the first rotor power device is arranged on the aircraft arm, the first rotor power device is positioned on both sides of the aircraft nose or both sides of the tail of the aircraft body, the first rotor power device comprises a first propeller and a first motor for driving the first propeller to rotate, the first propeller rotates to form a first paddle disk, the second rotor power device is arranged on the aircraft arm, the second rotor power device is positioned on both sides of the aircraft nose of the aircraft body or both sides or the rear part of the tail, the second rotor power device comprises a second propeller and a second motor for driving the second propeller to rotate, the second propeller rotates to form a second paddle disk, wherein, the projections of the first paddle disk and the second paddle disk in the yaw axis direction of the multi-rotor aircraft are not overlapped, and the diameter of the first paddle disk is different from the diameter of the second paddle disk.

Description

Multi-rotor aircraft

Technical Field

The utility model relates to an aircraft technical field especially relates to many rotor crafts.

Background

Existing multi-rotor aircraft, such as quad-rotor aircraft, typically increase overall efficiency by increasing the rotor disc area as the fuselage weight increases. However, when the area of the propeller disks of the propellers is increased, the overlapping of the propeller disks of the propellers positioned at the nose and the tail of the aircraft body is large, and the problems of increased noise, increased power efficiency loss and the like are caused.

SUMMERY OF THE UTILITY MODEL

In view of this, the utility model provides a many rotor crafts.

The utility model provides a many rotor crafts, include:

the machine body comprises a machine head and a machine tail opposite to the machine head;

a horn mechanically coupled to the fuselage;

the first rotor wing power device is arranged on the horn and is positioned on two sides of the nose or two sides of the tail of the fuselage, the first rotor wing power device comprises a first propeller and a first motor for driving the first propeller to rotate, and the first propeller rotates to form a first propeller disc;

the second rotor wing power device is arranged on the horn and is positioned on two sides of the nose or two sides or the rear of the tail of the fuselage, the second rotor wing power device comprises a second propeller and a second motor for driving the second propeller to rotate, and the second propeller rotates to form a second propeller disc;

wherein the first and second disks do not overlap in their projections in the direction of the yaw axis of the multi-rotor aircraft, and the first disk has a diameter different from the second disk.

According to the above technical scheme, the utility model provides a many rotor crafts, the diameter through setting up first oar dish is greater than the diameter of second oar dish, for the same mode of setting of first oar dish diameter and second oar dish diameter, under the non-overlapping condition of first oar dish and second oar dish, can effectively increase total oar dish area to promote whole machine power and effect. Moreover, the first paddle disk and the second paddle disk are not overlapped, so that the problems of noise and power efficiency loss caused by the overlapping of the first paddle disk and the second paddle disk can be solved.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without any creative effort.

Fig. 1 is a schematic top view of a quad-rotor aircraft according to an embodiment of the present invention;

FIG. 2 is an isometric schematic view of the quad-rotor aircraft shown in FIG. 1;

FIG. 3 is a schematic illustration of the attachment of the fuselage to the horn of the quad-rotor aircraft shown in FIG. 1;

fig. 4 is a schematic top view of a quad-rotor aircraft according to another embodiment of the present disclosure;

FIG. 5 is an isometric schematic view of the quad-rotor aircraft shown in FIG. 4;

fig. 6 is a schematic top view of a quad-rotor aircraft according to another embodiment of the present disclosure;

FIG. 7 is an isometric schematic view of the quad-rotor aircraft shown in FIG. 6;

FIG. 8 is a schematic side view of the quad-rotor aircraft shown in FIG. 6;

fig. 9 is a schematic top view of a three-rotor aircraft according to another embodiment of the present invention;

FIG. 10 is an isometric schematic view of the triple-rotor aircraft shown in FIG. 9;

figure 11 is a schematic side view of the triple-rotor aircraft shown in figure 9.

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 some, not all, of the embodiments of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

It is also to be understood that the terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in the specification and the appended claims, the singular forms "a", "an", and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.

It should be further understood that the term "and/or" as used in the specification and the appended claims refers to any and all possible combinations of one or more of the associated listed items, and includes such combinations.

As shown in fig. 1 and 2, an embodiment of the present invention provides a quad-rotor aircraft 10 including a fuselage 11, a horn 12, two first rotor power units 13, and two second rotor power units 14. The body 11 includes a head 11a and a tail 11b opposite to the head 11 a. The horn 12 is mechanically coupled to the body 11. Two first rotor power units 13 are mounted on the horn 12 and located on both sides of the nose 11a of the fuselage 11, respectively, and the first rotor power units 13 include a first propeller 131 and a first motor 132 for driving the first propeller 131 to rotate, and the first propeller 131 rotates to form a first propeller disk 133. Two second rotor power units 14 are mounted on the horn 12 and located on both sides of the tail 11b of the fuselage 11, respectively, and the second rotor power unit 14 includes a second propeller 141 and a second motor 142 for driving the second propeller 141 to rotate, and the second propeller 141 rotates to form a second propeller disk 143. Wherein, the projection of the first paddle disk 133 and the second paddle disk 143 in the direction of the yaw axis Z of the four-rotor aircraft 10 is not overlapped, and the diameter of the first paddle disk 133 is larger than that of the second paddle disk 143.

Compared with the existing arrangement mode that the diameter of the first paddle disk is the same as that of the second paddle disk, the diameter of the first paddle disk 133 is larger than that of the second paddle disk 143, and under the condition that the first paddle disk 133 is not overlapped with the second paddle disk 143, the total paddle disk area can be effectively increased in a fixed area through reasonable arrangement, so that the whole mechanical efficiency is improved, and the problems of noise and loss of mechanical efficiency caused by overlapping of the first paddle disk 133 and the second paddle disk 143 can be avoided due to the fact that the first paddle disk 133 is not overlapped with the second paddle disk 143. The total paddle area refers to the sum of the areas of the two first paddles 133 and the two second paddles 143.

As shown in fig. 2, optionally, the projection of the center of gravity of the quad-rotor aircraft 10 on the roll axis X of the quad-rotor aircraft 10 is B₁The projection of the power center of the quad-rotor aircraft 10 on the roll axis X is B₂，B₁To B₂Is a distance S₁Center E of first paddle disk 133₁Projection on the roll axis X is C₁Center E of second paddle 143₂Projection on the roll axis X is C₂，C₁To C₂A distance of M₁Wherein S is₁≤0.08M₁. In general, the power center of the four-rotor aircraft is at the intersection of the lines of the propeller motors, and in the present embodiment, the power center of the four-rotor aircraft 10 is determined by the intersection of the line connecting the first motor 132 located at the front left and the second motor 142 located at the rear right and the line connecting the first motor 132 located at the front right and the second motor 142 located at the rear left.

The four-rotor aircraft 10 proposed in the present embodiment is provided by setting S₁≤0.08M₁The gravity center and the power center of the four-rotor aircraft 10 can be overlapped as much as possible, the stability of flight control of the four-rotor aircraft 10 is facilitated, and the four-rotor aircraft 10 has better balance and maneuverability.

Optionally, the diameter ratio of the second paddle 143 to the first paddle 133 is any one of 0.3 to 0.7. Further, the diameter ratio of the second paddle 143 to the first paddle 133 may be any one of 0.4 to 0.6. Further, the diameter ratio of the second paddle 143 to the first paddle 133 may be 0.4, 0.45, 0.5, 0.55, 0.6. By controlling the diameter ratio of second paddle 143 to first paddle 133 to be within a suitable range of values, the center of gravity and the center of power of quad-rotor vehicle 10 are made to coincide as much as possible, which is beneficial to the stability of flight control of quad-rotor vehicle 10, and makes quad-rotor vehicle 10 have better balance and maneuverability.

Alternatively, the two first propellers 131 are symmetrically arranged with respect to the fuselage 11, and the two first disks 133 have the same diameter. Through setting up that two first screw 131 diameters are the same and for fuselage 11 symmetry setting, during the operation, two first screw 131 power effects are unanimous, are favorable to the stability of flight control. Of course, the two first propellers 131 may also be disposed asymmetrically with respect to the fuselage 11, and the diameters of the two first propellers 131 may also be disposed differently, specifically according to the actual design requirement.

Alternatively, the two second propellers 141 are symmetrically arranged with respect to the fuselage 11, and the two second discs 143 have the same diameter. Through setting up that two second screw 141 diameters are the same and for fuselage 11 symmetry setting, during the operation, two second screw 141 power effects are unanimous, are favorable to the stability of flight control. Of course, the two second propellers 141 may also be disposed asymmetrically with respect to the fuselage 11, and the diameters of the two second propellers 141 may also be disposed differently, specifically according to the actual design requirement.

Optionally, the center of second paddle 143 is proximate to fuselage 11 relative to the center of first paddle 133. That is, the smaller area of second paddle 143 is located close to fuselage 11, which contributes to the overall compactness, compactness and aesthetics of quad-rotor vehicle 10. Of course, the center of the second paddle 143 may also be located away from the fuselage 11 relative to the center of the first paddle 133, depending on the actual design requirements.

Alternatively, the boom 12 includes a first boom 12a disposed on both sides of a nose 11a and both sides of a tail 11b of the fuselage 11, the first rotor power unit 13 and the second rotor power unit 14 are mounted to the first boom 12a, and the first boom 12a is movably connected to the fuselage 11 so that the first boom 12a is foldable with respect to the fuselage 11. Through setting up first horn 12a collapsible for fuselage 11, when four rotor craft 10 do not use, can fold first horn 12a, folding back, four rotor craft 10 small in size is convenient for accomodate and carry.

As shown in fig. 3, the quad-rotor aircraft 10 further illustratively includes a pivot assembly 15, the pivot assembly 15 being mounted to the fuselage 11, the horn 12 being mounted to the pivot assembly 15, the horn 12 being rotatable about the pivot assembly 15 between an extended position and a collapsed position. Illustratively, the rotating shaft assembly 15 includes a base 151, a rotating shaft 152, a sleeve 153 and a spring 154, the base 151 is mounted on the body 11, the rotating shaft 152 is rotatably connected to the base 151, the sleeve 153 is sleeved on the rotating shaft 151, the spring 154 is sleeved on the rotating shaft 151 and is accommodated inside the sleeve 154, the spring 154 is used for providing a friction force between the rotating shaft 152 and the base 151, and the horn 12 is sleeved outside the rotating shaft assembly 15 and is connected to the rotating shaft 152. In use, the user rotates the arm 12 to the extended position against the friction between the shaft 152 and the base 151, and conversely, when not in use, rotates the arm 12 to the folded position. Alternatively, the rotating shaft 152 is provided as a hollow structure, and a cable inside the body 11 may pass through the rotating shaft 152 and extend along the horn 12 to the motor and be connected to the motor.

As shown in fig. 2, the quadrotor aircraft 10 further optionally includes a cradle head 16, the cradle head 16 is used for carrying the shooting device 17, the cradle head 16 is mounted on the nose 11a of the fuselage 11, and the first paddle 133 is located outside the field angle range of the shooting device 17. The first paddle 133 is located outside the field angle range of the imaging device 17, and does not block the imaging device 17, thereby facilitating the imaging of the imaging device 17.

As shown in fig. 4 and 5, another embodiment of the present invention provides a quad-rotor aircraft 20 that includes a fuselage 21, an arm 22, two first rotor power units 23, and two second rotor power units 24. The body 21 includes a head 21a and a tail 21b opposite to the head 21a, and the horn 22 is mechanically coupled to the body 21. Two first rotor power units 23 are mounted on the horn 22 and located on two sides of the nose 21a of the fuselage 21, respectively, the first rotor power units 23 include a first propeller 231 and a first motor 232 driving the first propeller 231 to rotate, and the first propeller 231 rotates to form a first paddle disk 233. Two second rotor power units 24 are mounted on the horn 22 and located on both sides of the tail 21b of the fuselage 21, respectively, and the second rotor power units 24 include a second propeller 241 and a second motor 242 for driving the second propeller 241 to rotate, and the second propeller 241 rotates to form a second disk 243. Wherein, the projections of the first and

second paddles

233, 243 on the yaw axis Z direction of the quad-rotor craft 20 do not overlap, and the diameter of the first paddle 233 is smaller than the diameter of the second paddle 243.

Compared with the existing arrangement mode that the diameter of the first paddle disk 233 is the same as that of the second paddle disk, the diameter of the first paddle disk 233 is smaller than that of the second paddle disk 243, and when the first paddle disk 233 is not overlapped with the second paddle disk 243, the total paddle disk area can be effectively increased in a fixed area through reasonable arrangement, so that the whole mechanical efficiency is improved, and the problems of noise and loss of mechanical efficiency caused by overlapping of the first paddle disk 233 and the second paddle disk 243 can be avoided because the first paddle disk 233 is not overlapped with the second paddle disk 243.

Optionally, the projection of the center of gravity of quad-rotor aircraft 20 on roll axis X of quad-rotor aircraft 20 is B₁The projection of the power center of the four-rotor aircraft 20 on the roll axis X is B₂，B₁To B₂Is a distance S₁Center E of the first paddle 233₁Projection on the roll axis X is C₁Center E of the second paddle 243₂Projection on the roll axis X is C₂，C₁To C₂A distance of M₁Wherein S is₁≤0.08M₁. By setting S₁≤0.08M₁The gravity center and the power center of the four-rotor aircraft 20 can be coincided as much as possible, the stability of flight control of the four-rotor aircraft 20 is facilitated, and the four-rotor aircraft 20 has better balance and maneuverability.

Alternatively, the diameter ratio of the second paddle 243 to the first paddle 233 is any one of 0.3 to 0.7. Further, the diameter ratio of the second paddle 243 to the first paddle 233 may be any one of 0.4 to 0.6. Further, the diameter ratio of the second paddle 243 to the first paddle 233 may be 0.4, 0.45, 0.5, 0.55, 0.6. By controlling the diameter ratio of the second paddle 243 to the first paddle 233 to be within a suitable range, the center of gravity and the center of power of the four-rotor aircraft 20 are made to coincide as much as possible, which is beneficial to the stability of flight control of the four-rotor aircraft 20, and the four-rotor aircraft 20 has better balance and maneuverability.

Alternatively, the two first propellers 231 are symmetrically arranged with respect to the fuselage 21, and the two first disks 233 are of the same diameter. Through setting up that two first screw 231 diameters are the same and for fuselage 21 symmetry setting, during operation, two first screw 231 power effects are unanimous, are favorable to flying the stability of accuse. Of course, the two first propellers 231 may also be disposed asymmetrically with respect to the fuselage 21, and the diameters of the two first propellers 231 may also be disposed differently, depending on the actual design requirements.

Alternatively, the two second propellers 241 are symmetrically arranged with respect to the fuselage 21, and the two second discs 243 are the same diameter. Through setting up that two second screw propellers 241 diameter is the same and for fuselage 21 symmetry setting, during the operation, two second screw propellers 241 power effect are unanimous, are favorable to the stability of flight control. Of course, the two second propellers 241 may also be disposed asymmetrically with respect to the fuselage 21, and the diameters of the two second propellers 241 may also be disposed differently, which is determined according to the actual design requirement.

Optionally, the center of the second propeller 241 is close to the body 21 with respect to the center of the first propeller 231. That is, the smaller area of second paddle 243 is located close to fuselage 21, which is advantageous for the overall compactness, compactness and aesthetics of quad-rotor aircraft 20. Of course, the center of the second paddle disk 243 may also be disposed away from the fuselage 21 relative to the center of the first paddle disk 233, depending on the actual design requirements.

Alternatively, the boom 22 includes a first boom 22a disposed on both sides of the nose 21a and both sides of the tail 21b of the body 21, the first rotor power unit 23 and the second rotor power unit 24 are mounted to the first boom 22a, and the first boom 22a is movably connected to the body 21 so that the first boom 22a is foldable with respect to the body 21. Through setting up first horn 22a collapsible for fuselage 21, when four rotor craft 20 did not use, can fold first horn 22a, after folding, four rotor craft 20 small in size is convenient for accomodate and carry. The foldable arrangement of the first arm 22a and the body 21 can refer to the above embodiments, and will not be described herein.

Optionally, the quad-rotor aircraft 20 further includes a cradle head 25, the cradle head 25 is used for carrying the shooting device 26, the cradle head 25 is mounted on the nose 21a of the fuselage 21, and the first paddle 233 is located outside the field angle range of the shooting device 26. The first paddle 233 is located outside the field angle range of the imaging device 26, and does not obstruct the imaging device 26, facilitating the imaging of the imaging device 26.

As shown in fig. 6-8, another embodiment of the present invention provides a quad-rotor aircraft 30 that includes a fuselage 31, a horn 32, two first rotor power units 33, and two second rotor power units 34. The body 31 includes a head 31a and a tail 31b opposite to the head 31a, and the horn 32 is mechanically coupled to the body 31. Two first rotor power units 33 are mounted on the horn 32 and located on both sides of the nose 31a of the fuselage 31, respectively, the first rotor power units 33 include a first propeller 331 and a first motor 332 for driving the first propeller 331 to rotate, and the first propeller 331 rotates to form a first rotor disk 333. Two second rotor power plants 34 are arranged side by side behind fuselage 31 along a roll axis X of quad-rotor craft 30, second rotor power plant 34 includes a second propeller 341 and a second motor 342 driving second propeller 341 in rotation, and second propeller 341 is rotated to form a second paddle 343. Wherein, the first paddle disk 333 does not overlap with the second paddle disk 343 in the projection in the yaw axis Z direction of the quad-rotor aircraft 30, and the diameter of the first paddle disk 333 is larger than the diameter of the second paddle disk 343.

Compared with the existing arrangement mode that the diameter of the first paddle disk 333 is the same as that of the second paddle disk, the diameter of the first paddle disk 333 is larger than that of the second paddle disk 343, and under the condition that the first paddle disk 333 is not overlapped with the second paddle disk 343, the total paddle disk area can be effectively increased in a fixed area through reasonable arrangement, so that the whole mechanical efficiency is improved, and the problems of noise and loss of mechanical efficiency caused by overlapping of the first paddle disk 333 and the second paddle disk 343 can be avoided.

Optionally, the projection of the center of gravity of the quad-rotor 30 onto the roll axis X of the quad-rotor 30 is B₁The projection of the power center of the four-rotor aircraft 30 on the roll axis X is B₂，B₁To B₂Is a distance S₁Center E of the first paddle disk 333₁Projection on the roll axis X is C₁Center E of second paddle 343₂Projection on the roll axis X is C₂，C₁To C₂A distance of M₁Wherein S is₁≤0.08M₁。

The four-rotor aircraft 30 proposed in the present embodiment is constructed by providing S₁≤0.08M₁The gravity center and the power center of the four-rotor aircraft 30 can be coincided as much as possible, the stability of flight control of the four-rotor aircraft 30 is facilitated, and the four-rotor aircraft 10 has better balance and maneuverability.

Optionally, the diameter ratio of the second paddle 343 to the first paddle 333 is any value from 0.3 to 0.7. Further, the diameter ratio of the second paddle 343 to the first paddle 333 may be any one of 0.4 to 0.6. Further, the diameter ratio of the second paddle 343 to the first paddle 333 may be 0.4, 0.45, 0.5, 0.55, 0.6. By controlling the diameter ratio of the second paddle 343 to the first paddle 333 to be within a suitable range, the center of gravity and the center of power of the quad-rotor 30 are made to coincide as much as possible, which is beneficial to the stability of flight control of the quad-rotor 30, and the quad-rotor 30 has better balance and maneuverability.

Alternatively, the boom 32 includes a first boom 32a disposed on both sides of the nose 31a of the fuselage 31, the first rotor power unit 33 is mounted to the first boom 32a, and the first boom 32a is movably connected to the fuselage 31 so that the first boom 32a is foldable relative to the fuselage 31. Through setting up first horn 32a collapsible for fuselage 31, when four rotor craft 30 do not use, can fold first horn 32a, folding back, four rotor craft 30 small in size is convenient for accomodate and carry. The foldable arrangement of the first arm 32a and the body 31 can refer to the above embodiments, and will not be described herein.

Optionally, the second propeller 341 further from the fuselage 31 is higher than the second propeller 341 closer to the fuselage 31. This embodiment does benefit to the advancing of fuselage 31 and retreats, makes things convenient for the change of the instant gesture of four rotor crafts 30, and maneuverability is better, and does benefit to the stability of flight.

Optionally, the horn 32 comprises a second horn 32b mounted behind the fuselage 31, the second horn 32b extending along the roll axis X of the quad-rotor vehicle 30, and two second propellers 341 mounted side by side to the second horn 32 b. It should be noted that the position between the two second propellers 341 and between the second propeller 341 close to the fuselage 31 and the fuselage 31 should be as compact as possible, so that the power centre is moved forward, coinciding as much as possible with the centre of gravity. Optionally, two second paddles 343 are tangent, the second propeller 341, which is close to the fuselage 31, being tangent to the tail 31b of the fuselage 31.

Optionally, second horn 32b includes a coupled end 32b1 and a free end 32b2, coupled end 32b1 coupled to fuselage 31, free end 32b2 is higher than coupled end 32b1, and second rotary wing power unit 34, remote from fuselage 31, is mounted to free end 32b 2. Of course, the second propeller 341 far from the main body 31 is higher than the second propeller 341 near the main body 31, and the above manner is not limited, for example, the second arm 32b may be horizontally extended, but the installation height of the second propeller 341 far from the main body 31 is higher than that of the second propeller 341 near the main body 31 by adding the support portion.

Optionally, the second horn 32b is a stationary horn 32. The second arm 32b is formed integrally with the body 31, but the second arm 32b may be mounted to the body 31 by fastening with bolts.

Optionally, the diameters of the two second paddles 343 are the same, which reduces the control difficulty of the quad-rotor aircraft 30 and improves the stability of flight control. Of course, the diameters of the two second paddle disks 343 may also be set to be different, which is determined according to the actual design requirement.

Alternatively, two first rotor power units 33 are included, the first disks 333 of the two first rotor power units 33 being symmetrically arranged with respect to fuselage 31 and having the same diameter. Through setting up that two first screw 331 diameters are the same and for fuselage 31 symmetry setting, during the operation, two first screw 331 power effects are unanimous, are favorable to the stability of flight control. Of course, the two first propellers 331 may also be disposed asymmetrically with respect to the fuselage 31, and the diameters of the two first propellers 331 may also be disposed differently, which is determined according to the actual design requirement.

Optionally, the second propeller 341, which is close to the fuselage 31, is higher than the first propeller 331. Similarly, this mode of setting up does benefit to advancing of fuselage 31 and retreats, makes things convenient for the change of the instant gesture of four rotor crafts 30, and maneuverability is better, and does benefit to the stability of flight.

Optionally, the quadrotor 30 further includes a cradle head 35, the cradle head 35 is used for carrying the shooting device 36, the cradle head 35 is mounted on the nose 31a of the fuselage 31, and the first paddle 333 is located outside the field angle range of the shooting device 36. The first paddle 333 is located outside the field angle range of the image capturing device 36, and does not block the image capturing device 36, thereby facilitating the image capturing of the image capturing device 36.

As shown in fig. 9-11, another embodiment of the present invention provides a triple-rotor aircraft 40 that includes a fuselage 41, an arm 42, two first rotor power units 43, and two second rotor power units 44. The body 41 includes a head 41a and a tail 41b opposite to the head 41a, and the horn 42 is mechanically coupled to the body 41. Two first rotor power units 43 are mounted on the horn 42 and located on both sides of the nose 41a of the fuselage 41, respectively, and the first rotor power units 43 include a first propeller 431 and a first motor 432 that drives the first propeller 431 to rotate, and the first propeller 431 rotates to form a first propeller disc 433. The second rotor power plant 44 is disposed behind the fuselage 41 along the roll axis X of the third rotary-wing aircraft 40, the second rotor power plant 44 includes a second propeller 441 and a second motor 442 driving the second propeller 441 to rotate, the second propeller 441 rotates to form a second paddle disk 443, wherein the first paddle disk 433 and the second paddle disk 443 do not overlap in projection in the direction of the yaw axis Z of the third rotary-wing aircraft 40, and the diameter of the first paddle disk 433 is larger than the diameter of the second paddle disk 443.

Compared with the existing arrangement mode that the diameter of the first paddle disk 433 is larger than that of the second paddle disk 443, and under the condition that the first paddle disk 433 is not overlapped with the second paddle disk 443, the total paddle disk area can be effectively increased in a fixed area through reasonable arrangement, so that the whole mechanical efficiency is improved, and the problems of noise and loss of mechanical efficiency caused by overlapping of the first paddle disk 433 and the second paddle disk 443 can be avoided due to the fact that the first paddle disk 433 is not overlapped with the second paddle disk 443. The total paddle disk area refers to the sum of the areas of the two first paddle disks 433 and the one second paddle disk 443.

Alternatively, the projection of the center of gravity of tri-rotor aircraft 40 on the roll axis X of tri-rotor aircraft 40 is B₁The projection of the power center of the three-rotor aircraft 40 on the roll axis X is B₂，B₁To B₂Is a distance S₁Center E of the first paddle disk 433₁Projection on the roll axis X is C₁Center E of the second paddle disk 443₂Projection on the roll axis X is C₂，C₁To C₂A distance of M₁Wherein S is₁≤0.08M₁。

The three-rotor aircraft 40 proposed in the present embodiment is constructed by providing S₁≤0.08M₁The gravity center and the power center of the three-rotor aircraft 40 can be overlapped as much as possible, the stability of flight control of the three-rotor aircraft 40 is facilitated, and the three-rotor aircraft 40 has better balance and maneuverability.

Optionally, the diameter ratio of the second paddle disk 443 to the first paddle disk 433 is any value from 0.3 to 0.7. Further, the diameter ratio of the second paddle disk 443 to the first paddle disk 433 may be any one of 0.4 to 0.6. Further, the diameter ratio of the second paddle disk 443 to the first paddle disk 433 may be 0.4, 0.45, 0.5, 0.55, 0.6. By controlling the diameter ratio of the second paddle disk 443 to the first paddle disk 433 to be within a proper range of values, the center of gravity and the power center of the three-rotor aircraft 40 are coincident as much as possible, stability of flight control of the three-rotor aircraft 40 is facilitated, and the three-rotor aircraft 40 has better balance and maneuverability.

Alternatively, the boom 42 includes a first boom 42a disposed on both sides of the nose 41a of the fuselage 41, the first rotor power device 43 is mounted on the first boom 42a, and the first boom 42a is movably connected to the fuselage 41 so that the first boom 42a is foldable relative to the fuselage 41. Through setting up first horn 42a collapsible for fuselage 41, when three rotor crafts 40 do not use, can fold first horn 42a, after folding, three rotor crafts 40 small in size are convenient for accomodate and carry. The foldable arrangement of the first arm 42a and the body 41 can refer to the above embodiments, and will not be described herein.

Optionally, the second propeller 441 is higher than the first propeller 431. With this arrangement, the advancing and retreating of the airframe 41 are facilitated, the change of the instant posture of the three-rotor aircraft 40 is facilitated, the maneuverability is better, and the stability of the flight is facilitated.

Optionally, horn 42 includes a second horn 42b mounted rearward of fuselage 41, second horn 42b extending along roll axis X of triple-rotor aircraft 40, second horn 42b including a coupled end 42b1 and a free end 42b2, coupled end 42b1 coupled to fuselage 41, free end 42b2 higher than coupled end 42b1, and second rotor power plant 44 mounted at free end 42b 2. Of course, the second screw 441 far from the body 41 is higher than the second screw 441 close to the body 41, and the above-mentioned manner is not limited, for example, the second arm 42b may be horizontally extended, but the mounting height of the second screw 441 far from the body 41 is higher than that of the second screw 441 close to the body 41 by adding a support portion.

Optionally, the second horn 42b is a stationary horn 42.

Alternatively, the number of first rotor power units 43 is two, and the first paddles 433 of the two first rotor power units 43 are symmetrically arranged with respect to the fuselage 41 and have the same diameter. By arranging the two first propellers 431 with the same diameter and symmetrically arranged relative to the fuselage 41, the two first propellers 431 have the same force effect during operation, and the stability of flight control is facilitated. Of course, the two first propellers 431 may also be disposed asymmetrically with respect to the fuselage 41, and the diameters of the two first propellers 431 may also be disposed differently, depending on the actual design requirements.

Optionally, the camera module further comprises a pan-tilt 45, the pan-tilt 45 is used for carrying the shooting device 46, the pan-tilt 45 is mounted on the nose 41a of the body 41, and the first paddle disk 433 or the second paddle disk 443 is located outside the field angle range of the shooting device 46. The first paddle 433 is located outside the field angle range of the photographing device 46, so that the photographing device 46 is not blocked, and photographing by the photographing device 46 is facilitated.

It should be noted that the proposed aircraft is not limited to the three-rotor or four-rotor aircraft described above, and may also be a multi-rotor aircraft with more than four rotors, and the layout and connection relationship of each component of the multi-rotor aircraft may refer to the above embodiments, which are not described herein again.

The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily think of various equivalent modifications or replacements within the technical scope of the present invention, and these modifications or replacements should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. A multi-rotor aircraft, comprising:

a horn mechanically coupled to the fuselage;

2. The multi-rotor aerial vehicle of claim 1, wherein a projection of a center of gravity of the multi-rotor aerial vehicle onto a roll axis of the multi-rotor aerial vehicle is B₁The projection of the power center of the multi-rotor aircraft on the transverse rolling shaft is B₂，B₁To B₂Is a distance S₁The projection of the center of the first paddle disk on the transverse rolling shaft is C₁The projection of the center of the second paddle disk on the transverse rolling shaft is C₂，C₁To C₂A distance of M₁Wherein S is₁≤0.08M₁。

3. The multi-rotor aerial vehicle of claim 1, wherein a diameter ratio of the second disk to the first disk is any one of 0.3 to 0.7.

4. A multi-rotor aerial vehicle as recited in claim 1, comprising two of said first rotor power plant and two of said second rotor power plant, one of said first rotor power plant and said second rotor power plant being located on each side of said fuselage nose, the other of said first rotor power plant and said second rotor power plant being located on each side of said fuselage tail.

5. The rotary wing aircraft of claim 4, wherein the two first propellers are symmetrically disposed with respect to the fuselage and the two first disks are the same diameter.

6. The rotary wing aircraft of claim 4, wherein the two second propellers are symmetrically disposed with respect to the fuselage and the two second disks are the same diameter.

7. The multi-rotor aerial vehicle of claim 4, wherein a diameter of the first paddle disk is greater than a diameter of the second paddle disk, a center of the second paddle disk being proximate the fuselage relative to a center of the first paddle disk.

8. The multi-rotor aerial vehicle of claim 4, wherein the horn comprises a first horn disposed on both sides of the fuselage nose and both sides of the fuselage tail, the first and second rotor power plants being mounted to the first horn, the first horn being movably coupled to the fuselage such that the first horn is foldable relative to the fuselage.

9. The multi-rotor aerial vehicle of claim 1, comprising two of the first rotor power plants and two of the second rotor power plants, the two first rotor power plants being located on opposite sides of the fuselage nose, the two second rotor power plants being located side-by-side behind the fuselage along a roll axis of the multi-rotor aerial vehicle, the first rotor disk having a diameter greater than a diameter of the second rotor disk.

10. The multi-rotor aerial vehicle of claim 9, wherein the horn comprises a first horn disposed on each side of the fuselage nose, the first rotor power plant being mounted to the first horn, the first horn being movably coupled to the fuselage such that the first horn is foldable relative to the fuselage.

11. The multi-rotor aerial vehicle of claim 9, wherein the second propeller distal to the fuselage is higher than the second propeller proximal to the fuselage.

12. The multi-rotor aerial vehicle of claim 11, wherein the horn comprises a second horn mounted rearward of the fuselage, the second horn extending along a roll axis of the multi-rotor aerial vehicle, and two of the second propellers mounted side-by-side to the second horn.

13. The multi-rotor aerial vehicle of claim 12, wherein the second horn includes a connecting end and a free end, the connecting end being connected to the fuselage, the free end being higher than the connecting end, a second rotor power plant remote from the fuselage being mounted to the free end.

14. The multi-rotor aerial vehicle of claim 12, wherein the second horn is a stationary horn.

15. The multi-rotor aerial vehicle of claim 9, wherein the diameters of the two second disks are the same.

16. The multi-rotor aerial vehicle of claim 9, wherein the first paddles of both of the first rotor power plants are symmetrically disposed with respect to the fuselage and are the same diameter.

17. The rotary wing aircraft of claim 9, wherein the second propeller is higher than the first propeller near the fuselage.

18. The multi-rotor aerial vehicle of claim 1, comprising two of the first rotor power plants and one of the second rotor power plants, the two first rotor power plants being disposed on opposite sides of the fuselage nose, the second rotor power plant being disposed rearward of the fuselage along a roll axis of the multi-rotor aerial vehicle, the first rotor disk having a diameter greater than a diameter of the second rotor disk.

19. The multi-rotor aerial vehicle of claim 18, wherein the horn comprises a first horn disposed on each side of the fuselage nose, the first rotor power plant being mounted to the first horn, the first horn being movably coupled to the fuselage such that the first horn is foldable relative to the fuselage.

20. The multi-rotor aerial vehicle of claim 18, wherein the second propeller is higher than the first propeller.

21. The multi-rotor aerial vehicle of claim 19, wherein the horn comprises a second horn mounted rearward of the fuselage, the second horn extending along a roll axis of the multi-rotor aerial vehicle, the second horn comprising a connected end and a free end, the connected end being connected to the fuselage, the free end being higher than the connected end, the second rotor power plant being mounted at the free end.

22. The multi-rotor aerial vehicle of claim 21, wherein the second horn is a stationary horn.

23. The multi-rotor aerial vehicle of claim 18, wherein the first paddles of both of the first rotor power plants are symmetrically disposed with respect to the fuselage and are the same diameter.

24. The multi-rotor aerial vehicle of claim 1, further comprising a pan head for carrying a camera, the pan head being mounted to a nose of the fuselage, the first or second paddle disk being positioned outside a field angle range of the camera.