CN114514172A

CN114514172A - Unmanned plane

Info

Publication number: CN114514172A
Application number: CN202080069593.0A
Authority: CN
Inventors: 周炜翔; 刘以奋; 韩杰星
Original assignee: SZ DJI Technology Co Ltd
Current assignee: SZ DJI Technology Co Ltd
Priority date: 2020-12-31
Filing date: 2020-12-31
Publication date: 2022-05-17
Also published as: WO2022141572A1

Abstract

An unmanned aerial vehicle (1000). Unmanned aerial vehicle (1000) includes motor (200) and motor cabinet (100). Motor cabinet (100) include base (10) and bulge (20), and base (10) are used for installing motor (200), and bulge (20) extend the protrusion from base (10), and under the flight state of unmanned aerial vehicle (1000), bulge (20) are at least partly towards the rear side of unmanned aerial vehicle (1000) convergent extension.

Description

Unmanned plane

Technical Field

The application relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle.

Background

At present, in the design of the unmanned aerial vehicle, the appearance, the structural characteristics and the producibility characteristics of each part of the unmanned aerial vehicle are mainly considered, and the aerodynamic characteristics of each part of the unmanned aerial vehicle are not considered. In the process of flying before the complete machine, the components on the unmanned aerial vehicle can produce great resistance, and the resistance can bring the flight burden for flying before giving the complete machine level.

Disclosure of Invention

The embodiment of the application provides an unmanned aerial vehicle.

The unmanned aerial vehicle of this application embodiment includes motor and motor cabinet. The motor cabinet includes base and bulge, and the base is used for installing the motor, and the bulge extends the protrusion from the base, and under unmanned aerial vehicle's flight state, the bulge extends towards unmanned aerial vehicle's rear side convergent at least part.

The utility model provides an unmanned aerial vehicle's motor cabinet of embodiment includes base and bulge, under unmanned aerial vehicle's flight state, the bulge is at least partly towards unmanned aerial vehicle's rear side convergent extension, makes the surface flow that the incoming flow can attach the bulge to reduce the disengagement zone that the incoming flow formed in motor cabinet rear side, play the rectification effect, can show the flow resistance that receives when flying before reducing unmanned aerial vehicle, and then reduce unmanned aerial vehicle's flight burden.

The embodiment of the application provides another unmanned aerial vehicle. Unmanned aerial vehicle includes fuselage and horn, and the root and the fuselage of horn are connected, and the horn is including the root that is used for being connected with unmanned aerial vehicle's fuselage and the tip relative with the root, along root to tip direction, the angle of erection of a plurality of wing section of horn crescent, and the angle of erection is the contained angle between the chord length of the wing section of horn and unmanned aerial vehicle's the normal plane of driftage axle.

In the unmanned aerial vehicle of this application embodiment, chord length, thickness and the angle of erection through setting up the horn wing section can make the horn have good rectification effect, reduce the resistance that the horn receives when unmanned aerial vehicle flies to can reduce unmanned aerial vehicle's flight consumption, improve unmanned aerial vehicle's duration.

Embodiments of the present application provide yet another drone. Unmanned aerial vehicle includes fuselage, horn, and foot rest. The foot rest sets up in one side of horn, and the foot rest is used for supporting unmanned aerial vehicle when unmanned aerial vehicle takes off and land, and the foot rest is flat column structure.

In the unmanned aerial vehicle of this application embodiment, through the foot rest that sets up flat column structure, make the resistance of foot rest department can reduce when unmanned aerial vehicle flies to can reduce unmanned aerial vehicle's flight consumption, improve unmanned aerial vehicle's duration.

Additional aspects and advantages of embodiments of the present application will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of embodiments of the present application.

Drawings

The above and/or additional aspects and advantages of the present application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:

fig. 1 is a schematic perspective view of a drone according to certain embodiments of the present application;

fig. 2 is a schematic plan view of a drone according to certain embodiments of the present application;

fig. 3 is a schematic perspective view of a motor, a motor base, and a first indicator light according to some embodiments of the present disclosure, and a schematic view of an inclination angle of a center line of a fuselage of the unmanned aerial vehicle with respect to a horizontal plane in a cruising state;

FIG. 4 is a schematic view of fluid flowing through a motor mount with a projection and fluid flowing through a motor mount without a projection;

FIG. 5 is a schematic view of fluid flow through the motor mount of the present application and fluid flow through a prior art motor mount;

fig. 6 is a schematic view of a motor mount and a projection of the motor mount of certain embodiments of the present application onto a normal plane of a yaw axis of a drone;

fig. 7 is a schematic view of a motor mount and a projection of the motor mount of certain embodiments of the present application onto a normal plane of a yaw axis of a drone;

FIG. 8 is a schematic view of a motor and motor mount according to certain embodiments of the present application;

FIG. 9 is a schematic illustration of the structure of a horn according to certain embodiments of the present application;

FIGS. 10-13 are cross-sectional views of airfoils of certain embodiments of the present application;

FIG. 14 is a schematic illustration of the structure of a horn according to certain embodiments of the present application;

FIGS. 15-17 are cross-sectional views of airfoils of certain embodiments of the present application;

fig. 18 is a schematic view of a blockage in flight of a drone according to certain embodiments of the present application;

FIG. 19 is a schematic view of a motor, motor mount, foot rest, and third indicator light of certain embodiments of the present application;

FIG. 20 is a cross-sectional view of a foot rest according to certain embodiments of the present application;

fig. 21 is a schematic view of a blockage in flight of a drone according to certain embodiments of the present application.

Detailed Description

Reference will now be made in detail to embodiments of the present application, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative and are only for the purpose of explaining the present application and are not to be construed as limiting the present application.

In the description of the present application, it is to be understood that the terms "thickness," "upper," "top," "bottom," "inner," "outer," etc. indicate orientations or positional relationships based on those shown in the drawings, which are merely for convenience in describing the present application and simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present application. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more features. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.

In the description of the present application, it should be noted that, unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, a fixed connection, a detachable connection, or an integral connection; may be mechanically connected, may be electrically connected or may be in communication with each other; either directly or indirectly through intervening media, either internally or in any other relationship.

The following disclosure provides many different embodiments or examples for implementing different features of the application. In order to simplify the disclosure of the present application, specific example components and arrangements are described below. Of course, they are merely examples and are not intended to limit the present application. Moreover, the present application may repeat reference numerals and/or letters in the various examples, such repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. In addition, examples of various specific processes and materials are provided herein, but one of ordinary skill in the art may recognize applications of other processes and/or use of other materials.

Referring to fig. 1 to 3, the present application provides a drone 1000, where the drone 1000 includes a motor 200 and a motor base 100. Motor cabinet 100 includes base 10 and bulge 20, and base 10 is used for installing motor 200, and bulge 20 extends the protrusion from base 10, and under unmanned aerial vehicle 1000's flight condition, bulge 20 is at least partly towards the rear side of unmanned aerial vehicle 1000 convergent extension.

The drone 1000 shown in fig. 1 is merely an example, and the drone 1000 provided by the present application may be a multi-rotor drone 1000 such as a dual-rotor drone 1000, a quad-rotor drone 1000, a hexa-rotor drone 1000, an octa-rotor drone 1000, and so on, and is not limited herein.

The rear side of the drone 1000 is a direction from the nose 301 to the tail 303 when the drone 1000 is flying, the extending direction of the protruding portion 20 is toward the rear side of the drone 1000, and the width of the protruding portion 20 gradually narrows along the extending direction of the protruding portion 20, as shown in fig. 4 (b). It is understood that the width of the protrusion 20 may be constant along the extending direction of the protrusion 20, and the height of the protrusion 20 is gradually narrowed, as shown in fig. 5 (b). It is understood that, in the present embodiment, the width and the height of the projection 20 are gradually narrowed in the extending direction of the projection 20.

Referring to fig. 4, (a) of fig. 4 illustrates a flight state of the drone 1000 without the protrusion 20 of the motor base 100, and (b) of fig. 4 illustrates a flight state of the drone 1000 with the protrusion 20 of the motor base 100 according to the embodiment of the present disclosure. Wherein, P0 is a separation point of the airflow at the motor base 100 of the drone 1000 illustrated in (a), and D0 is a separation area formed by the airflow at the rear side of the motor base 100 of the drone 1000 illustrated in (a); p1 is a separation point of the airflow at the motor base 100 of the drone 1000 illustrated in (b), and D1 is a separation zone formed by the airflow at the rear side of the motor base 100 of the drone 1000 illustrated in (b). The pressure in separation region department is less, consequently receives the pressure to be greater than the rear side in the front side of motor cabinet 100, forms the wake resistance of backward side, hinders unmanned aerial vehicle 1000 forward flight.

Compared with the unmanned aerial vehicle 1000 illustrated in fig. 4 (a), the separation area D1 formed at the rear side of the motor base 100 of the unmanned aerial vehicle 1000 illustrated in fig. b is greatly reduced in size. Specifically, compare in the unmanned aerial vehicle 1000 of (a) diagram illustration, (b) the unmanned aerial vehicle 1000 of diagram illustration, the surface that comes to flow and can attach base 10 and bulge 20 flows, because along the extending direction of bulge 20, the width of bulge 20 narrows down gradually, makes the in-process that comes to flow and can be attached bulge 20 surface flow and inwards draw close gradually (draw close to the direction that is close to motor cabinet 100 center promptly, and is the same down), makes the scope of separation region D1 reduce. Meanwhile, the separation point P1 moves to the rear side of the motor base 100 compared with the separation point P0, so that the initial position of the separation area moves backward, and the range of the separation area D1 is further reduced. So, unmanned aerial vehicle 1000 of this application embodiment is when flying forward, and the disengagement zone that motor cabinet 100 rear side formed is less, can show the flow resistance that receives when flying forward that reduces unmanned aerial vehicle 1000 to reduce unmanned aerial vehicle 1000's flight burden, and then can reduce unmanned aerial vehicle 1000's flight consumption, play the important role to improving unmanned aerial vehicle 1000's duration.

In conclusion, the motor cabinet 100 of unmanned aerial vehicle 1000 of the embodiment of the present application includes base 10 and bulge 20, under unmanned aerial vehicle 1000's flight state, bulge 20 at least part extends towards unmanned aerial vehicle 1000's rear side convergent, make the surface flow that comes the attached bulge 20, in order to reduce the disengagement zone that comes the flow and form in motor cabinet 100 rear side, play the rectification effect, can show the flow resistance that receives when reducing unmanned aerial vehicle 1000 and fly, and then reduce unmanned aerial vehicle 1000's flight burden.

This is further explained below with reference to the drawings.

Referring to fig. 1 and 2, the drone 1000 further includes a fuselage 300 and a boom 400. One end of the horn 400 is connected to the body 300, and the other end is connected to the motor base 100. Motor cabinet 100 is installed in horn 400, and motor 200 is installed in motor cabinet 100, and motor 200 can load the rotor (not shown in the figure) of various models in order to drive the rotor and rotate, provides power for unmanned aerial vehicle 1000's flight.

When the unmanned aerial vehicle 1000 is in a normal flight state, the motor base 100 can be above the motor 200, and the rotor can be installed below the motor 200; alternatively, motor mount 100 is below motor 200, and the rotor may be mounted above motor 200, without limitation.

Referring to fig. 3, when the drone 1000 is in a cruising state, the fuselage 300 (with the center line L1 of the fuselage 300) has a predetermined inclination angle β with respect to the horizontal plane S0, so that the torques of the arms 400 of the drone 1000 in the cruising state can be balanced, and the gravity, the aerodynamic force, and the pulling force of the rotor wing can be balanced to maintain stable flight of the drone 1000. The tilt angle β may be in a range of [20 °, 30 ° ], for example, the tilt angle β may be 20.0 °, 21.5 °, 22.8 °, 23.2 °, 24.4 °, 25.0 °, 26.1 °, 27.5 °, 28.4 °, 29.3 °, or 30.0 °, which is not listed here.

Referring to fig. 3 and 8, the base 10 includes a first surface 11, the base 10 has a receiving cavity 13 formed on the first surface 11, and the motor 200 is partially received in the receiving cavity 13, such that the motor 200 is mounted on the base 10. The protrusion 20 extends and protrudes from the base 10, and the surface of the protrusion 20 is curved so that the air flow can move attached to the surface of the protrusion 20. The motor base 100 may further include an extension 30, the extension 30 extends from the protrusion 20 toward a side of the base 10 where the first surface 11 is located, and the extension 30 surrounds at least a partial region of the motor 200.

Taking the example that the motor base 100 is below the motor 200 and the rotor is installed above the motor 200 when the drone 1000 is in a normal flight state as an example, the motor base 100 specifically includes a base 10, a protrusion 20, and an extension 30.

The first face 11 of the base 10 may be planar. The base 10 further comprises a second face 12, the second face 12 of the base 10 may be an arc face and is connected with the first face 11 of the base 10, and the second face 12 of the base 10 is located in front to make first contact with incoming flow when the unmanned aerial vehicle 1000 flies forward. The second face 12 of base 10 is the cambered surface to make the air current can attach the second face 12 flow at the base, the second face 12 of base 10 can play the rectification effect equally, can make the separation point of the incoming flow of the second face 12 flow of attached base 10 remove to the rear side of motor cabinet 100, so that the initial position of disengagement zone shifts backward, reduces the scope of disengagement zone, thereby reduces the resistance that motor cabinet 100 receives.

Referring to fig. 3, in some embodiments, an angle α is formed between a local tangent of the trailing edge point 122 of the profile of the second surface 12 of the base 10 and a normal plane S1 of the yaw axis of the drone 1000, and the difference between the angle α and the inclination angle β of the fuselage 300 of the drone 1000 during cruising flight is within a first predetermined range, so as to define the curvature of the second surface 12 and to guide the incoming flow flowing against the second surface 12 to close, further reducing the range of the separation zone, and thus reducing the resistance experienced by the motor mount 100. Wherein the first predetermined range may be [1 °, 15 ° ] and the like, without limitation. Specifically, the included angle α and the inclination angle β satisfy the relation: α - β -10 ° to provide the second face with a predetermined arc. For example, when the inclination angle β is 30 °, the included angle α is 30 ° -10 ° -20 °.

It should be noted that the yaw axis is defined in the machine body axis system, in the present application, the machine body coordinate system is a right-hand system, the X axis is defined as the front-back direction of the machine body, the Z axis is the up-down direction of the machine body, the down-up direction is the up-down direction, and the Y axis is the left-right direction of the machine body, and the specific direction is obtained according to the XZ plane. Herein, the yaw axis of the unmanned aerial vehicle 1000 is a Z axis in a body coordinate system, the normal plane S1 of the yaw axis of the unmanned aerial vehicle 1000 is an XY plane perpendicular to the Z axis, and the body axis is fixedly connected with the body and does not change with the flight state. When the drone 1000 is in the windless hovering state, the gravity direction of the drone 1000 coincides with the yaw axis direction of the drone 1000 and the Z axis direction in the body coordinate system, and the XY plane is parallel to the horizontal plane S0, that is, when the drone 1000 is in the windless hovering state, the normal plane S1 of the yaw axis of the drone 1000 is parallel to the horizontal plane S0, and when the drone 1000 is in the cruise flight state, the normal plane S1 of the yaw axis of the drone 1000 may have an inclination angle β with respect to the horizontal plane S0. In addition, when unmanned aerial vehicle 1000 is in the state of hovering without wind, there is certain contained angle between the plane (the normal plane of motor shaft) and the horizontal plane of motor to gravity, aerodynamic force and the pulling force of rotor can keep balanced when satisfying the state of hovering without wind, with the hover that keeps unmanned aerial vehicle 1000. It will be appreciated that the windless hovering state of the drone referred to herein may be approximately equivalent to a takeoff or landing state of the drone on level ground.

With continued reference to fig. 3, when the drone 1000 is flying in cruise mode, the portion of the second face 12 of the base 10 below the reference plane S2 is mainly rectified, the reference plane S2 being parallel to the horizontal plane S0. The highest point 121 of the profile of the second face 12 of the base 10 is the point on the second face 12 that is farthest from the reference plane S2. In some embodiments, the angle θ between the tangent to the highest point 121 of the profile of the second face 12 of the base 10 and the normal plane S1 of the yaw axis of the drone 1000 is in the range of [30 °, 35 ° ], for example, the angle θ between the tangent to the highest point 121 of the profile of the second face 12 of the base 10 and the normal plane S1 of the yaw axis of the drone 1000 may be 30.0 °, 30.5 °, 31.0 °, 31.4 °, 32.0 °, 32.8 °, 33.0 °, 33.6 °, 34.0 °, 34.9 °, or 35.0 °, to name but a few. When the range of the included angle θ between the tangent line of the highest point 121 of the profile of the second surface 12 of the base 10 and the normal plane S1 of the yaw axis of the unmanned aerial vehicle 1000 is [30 °, 35 ° ], the incoming flow direction when the unmanned aerial vehicle 1000 makes a cruise with the inclination angle β can be close to the tangent line direction of the highest point 121 of the profile of the second surface 12 of the base 10, so that the incoming flow when the unmanned aerial vehicle 1000 makes a cruise with the inclination angle β easily adheres to the surface of the second surface 12 of the base 10 to flow, and the range of the separation area is further reduced, thereby reducing the resistance borne by the motor base 100. The protrusion 20 extends and protrudes from the base 10, and the surface of the protrusion 20 is a curved surface and forms a smooth curved surface continuously with the second surface 12, so that the air flow can flow attached to the surface of the protrusion 20.

Referring to fig. 5, fig. 5 (a) illustrates a schematic diagram of a motor base with a fluid flowing through a prior art, and fig. 5(b) illustrates a schematic diagram of a motor base 100 with a fluid flowing through an embodiment of the present application. Wherein, P0 is a separation point of the airflow at the motor base 100 of the drone 1000 illustrated in (a), D0 is a separation area formed by the airflow at the rear side of the motor base 100 of the drone 1000 illustrated in (a); p1 is a separation point of the airflow at the motor base 100 of the drone 1000 illustrated in (b), and D1 is a separation zone formed by the airflow at the rear side of the motor base 100 of the drone 1000 illustrated in (b).

The extension portion 30 has a certain slope toward the rear side of the drone 1000 so as to guide the airflow passing through the motor 200 to flow along the surface of the extension portion 30, so that the separation point P1 on the extension portion 30 side moves toward the rear side of the motor base 100, so that the initial position of the separation region D1 moves backward, and the range of the separation region D1 is reduced.

Specifically, one side (front side) of the extension 30 close to the motor 200 is far away from the plane where the first surface 11 of the base 10 is located, and one side (rear side) of the extension 30 far away from the motor 200 is near to the plane where the first surface 11 of the base 10 is located, so as to form a downward slope, so that the incoming flow flowing on the surface of the attached extension 30 gradually draws close inwards, the range of the separation area D1 is further reduced, and the resistance received by the motor base 100 is reduced.

Referring to fig. 3, in some embodiments, the extension 30 may include a first surface 31 and a second surface 32, the first surface 31 of the extension 30 surrounds at least a partial region of the motor 200, the second surface 32 of the extension 30 is connected to the first surface 31 of the extension 30, an included angle γ is formed between a tangent of a highest point 321 of a profile of the second surface 32 of the extension 30 and a normal plane S1 of a yaw axis of the drone 1000, and a difference between the included angle γ and an inclination angle β of the body 300 of the drone 1000 during cruising is within a second predetermined range, so as to limit a slope of the extension 30 toward a rear side of the drone 1000, so that an incoming flow moving on a surface of the extension 30 gradually draws closer inward. Wherein the second predetermined range may be [1 °, 15 ° ] and the like, without limitation. Specifically, the included angle γ and the inclination angle β satisfy the relation: γ +10 ° so that the second surface 32 has a predetermined slope. For example, when the inclination angle β is 30 °, the included angle γ is 30 ° +10 ° -40 °. The second predetermined range may be the same as or different from the first predetermined range.

In some embodiments, an angle γ between a tangent line of the highest point 321 of the profile of the second face 32 of the extension 30 and the normal plane S1 of the yaw axis of the drone 1000 is [30 °, 40 ° ], for example, an angle γ between a tangent line of the highest point 321 of the profile of the second face 32 of the extension 30 and the normal plane S1 of the yaw axis of the drone 1000 may be 30.0 °, 30.5 °, 31.0 °, 31.4 °, 32.0 °, 32.8 °, 33.0 °, 33.6 °, 34.0 °, 34.9 °, 35.0 °, 36.5 °, 37.0 °, 38.4 °, 39.0 °, or 40.0 °, to name but a few, so that an incoming flow direction when the drone 1000 makes a cruise at the tilt angle β can approach a tangent line direction of the highest point 321 of the profile of the second face 32 of the extension 30, so that the second face 32 of the extension 30 easily attaches to reduce the separation zone, thereby further reducing the resistance of the motor base 100.

Referring to fig. 1, 2, and 6, in some embodiments, a projection profile of the motor base 100 in a normal plane S1 of a yaw axis of the drone 1000 is in a shape of a droplet, so that a surface of the motor base 100 can be streamlined, and drag on the drone 1000 during flying is further reduced.

Specifically, the projection profile of the motor base 100 in the normal plane S1 of the yaw axis of the drone 1000 includes an arc-shaped housing section 14 and a rectifying section 33 connected to the housing section 14. The receiving section 14 corresponds to a head portion of a water droplet when the water droplet freely falls, and the rectifying section 33 corresponds to a tail portion of the water droplet when the water droplet freely falls, and the rectifying section 33 is tapered in a direction away from the receiving section 14. The base 10 has a part of a projection profile in a normal plane S1 of the yaw axis of the drone 1000 corresponding to the housing segment 14, and at least a part of the extension 30 has a projection profile in a normal plane S1 of the yaw axis of the drone 1000 corresponding to the rectifying segment 33.

Referring to fig. 3 and 6, in some embodiments, a projection profile of the extension 30 in a normal plane S1 of the yaw axis of the drone 1000 is trapezoidal, that is, a profile of the fairing section 33 is trapezoidal, and tapers away from the housing section 14. Similar to the effect of the protrusion 20, the portion of the extension 30 corresponding to the rectifying section 33 also has a rectifying effect, so that the incoming flow at two sides of the motor base 100 can flow along the rectifying section 33, the incoming flow rectified by the rectifying section 33 is drawn close to the rear side of the motor base 100, and the separation point of the incoming flow moves backward, thereby reducing the range of the separation area and the resistance borne by the motor base 100.

Referring to fig. 1, 2, 7, and 8, in some embodiments, when the drone 1000 is in a normal flight state, the motor base 100 is above the motor 200, and the rotor is installed below the motor 200, at this time, a projection profile of the motor base 100 in a normal plane S1 of a yaw axis of the drone 1000 is in a spindle shape, so that a surface of the motor base 100 can be in a streamline shape, and resistance received by the drone 1000 during flight is further reduced.

Specifically, the projection profile of the drone 1000 in the normal plane S1 of the yaw axis of the drone 1000 may further include a flow guiding section 41, and the flow guiding section 41 and the rectifying section 33 are respectively located on two sides of the accommodating section 14. The guide section 41 is located at the head of the spindle, the accommodating section 14 is located at the middle of the spindle, the rectifying section 33 is located at the tail of the spindle, and the guide section 41 and the rectifying section 33 are both gradually reduced along the direction far away from the accommodating section 14. The base 10 includes a flow guide part 40 and a rectifying part 50, a projection profile of at least a part of the flow guide part 40 in a normal plane S1 of a yaw axis of the drone 1000 corresponds to the flow guide section 41, a projection profile of at least a part of the rectifying part 50 in a normal plane S1 of the yaw axis of the drone 1000 corresponds to the housing section 14, and the protrusion 20 corresponds to the rectifying section 33.

The diversion section 41 corresponding to the diversion part 40 plays a role in diversion in a normal plane S1 of a yaw axis of the unmanned aerial vehicle 1000, so that incoming flow in the front side direction of the motor base 100 can flow through the diversion section 41, the accommodating section 14 and the rectifying section 33 in sequence by being attached to the surface of the diversion part 40 under the guidance of the diversion section 41 when the unmanned aerial vehicle 1000 flies, and a rectifying effect is achieved. Specifically, the flow guiding section 41 gradually expands in a direction approaching the accommodating section 14 to have a certain gradient, and the gradient is suitable in size, so that when an incoming flow flows along the flow guiding section 41 with the gradient, the incoming flow is easily attached to the surface of the flow guiding section 41, so as to smoothly guide the incoming flow to the accommodating section 14 and the rectifying section 33, and the incoming flow is not guided to a direction away from the surface of the motor base 100 due to an excessive gradient. That is, an included angle between the direction of the incoming flow, in which the flow direction is changed by the guide section 41, and the initial direction of the incoming flow when the incoming flow passes through the guide portion 40 is small, so that the flow resistance in the front direction of the motor base 100 can be reduced when the unmanned aerial vehicle 1000 flies.

The rectifying effect of the accommodating section 14 and the rectifying section 33 on the incoming flow is similar to the rectifying effect of the accommodating section 14 and the rectifying section 33 on the incoming flow in fig. 4 and 6, and is not described herein again.

In certain embodiments, the projected profile of the flow guide 40 in the normal plane S1 of the yaw axis of the drone 1000 is triangular, i.e., the flow guide section 41 is triangular, tapering in a direction away from the housing section 14. The angle of the diversion section 41 towards the front side direction of the motor base 100 is a preset angle, so that the diversion section 41 has a preset gradient along the direction close to the accommodating section 14, the incoming flow is not guided to the direction far away from the surface of the motor base 100 because of too large gradient, and the diversion part 40 does not need to be made very long to increase the resistance in front of the motor base 100 because of too small gradient.

Referring to fig. 8, in some embodiments, an included angle Φ is formed between a tangent of the highest point 51 of the outer contour of the fairing part 50 and a normal plane S1 of the yaw axis of the unmanned aerial vehicle 1000, and the included angle Φ is the same as an inclination angle β of the unmanned aerial vehicle 1000 when the unmanned aerial vehicle 1000 is cruising, so that the tangent of the highest point 51 of the outer contour of the fairing part 50 is as close to the incoming flow direction as possible when the unmanned aerial vehicle 1000 is flying, the incoming flow is more easily attached to the surface of the fairing part 50 to flow, and the fairing effect is optimal.

Specifically, the range of an angle Φ between the tangent to the highest point 51 of the outer contour of the fairing part 50 and the normal plane S1 of the yaw axis of the drone 1000 is [30 °, 40 ° ], for example, the angle Φ between the tangent to the highest point 51 of the outer contour of the fairing part 50 and the normal plane S1 of the yaw axis of the drone 1000 may be 30.0 °, 30.5 °, 31.0 °, 31.4 °, 32.0 °, 32.8 °, 33.0 °, 33.6 °, 34.0 °, 34.9 °, 35.0 °, 36.5 °, 37.0 °, 38.4 °, 39.0 °, or 40.0 °, which is not listed here. When the fuselage 300 of the unmanned aerial vehicle 1000 is cruising at the inclination angle β, the tangent to the highest point 51 of the outer contour of the fairing section 50 can be as close as possible to the incoming flow direction, so that the fairing effect is optimal.

To sum up, in the unmanned aerial vehicle 1000's of this application motor cabinet 100, the second face 12 of base 10, rectification portion 50, bulge 20 and water conservancy diversion portion 40 homoenergetic play the rectification effect respectively to motor cabinet 100's flow resistance when reducing unmanned aerial vehicle 1000 flight jointly reduces unmanned aerial vehicle 1000's flight burden, increases unmanned aerial vehicle 1000's duration.

Referring to fig. 1, 2, 9 and 14, in some embodiments, the horn 400 includes a root portion 410 for connecting to the body 300 of the drone 1000 and a tip portion 420 opposite to the root portion 410, and an installation angle ω of the plurality of wing profiles 430 of the horn 400 increases gradually along a direction from the root portion 410 to the tip portion 420, where the installation angle ω is an angle between a chord length L of the wing profile 430 of the horn 400 and a normal plane S1 of the yaw axis of the drone 1000.

It should be noted that the yaw axis is defined in the machine body axis system, in the present application, the machine body coordinate system is a right-hand system, the X axis is defined as the front-back direction of the machine body, the Z axis is the up-down direction of the machine body, the down-up direction is the up-down direction, and the Y axis is the left-right direction of the machine body, and the specific direction is obtained according to the XZ plane. Herein, the yaw axis of the unmanned aerial vehicle 1000 is a Z axis in a body coordinate system, the normal plane S1 of the yaw axis of the unmanned aerial vehicle 1000 is an XY plane perpendicular to the Z axis, and the body axis is fixedly connected with the body and does not change with the flight state. When the unmanned aerial vehicle 1000 is in a windless hovering state, the gravity direction of the unmanned aerial vehicle 1000 coincides with the yaw axis direction of the unmanned aerial vehicle 1000 and the Z axis direction in the body coordinate system. That is, the normal plane S1 of the yaw axis of the drone 1000 in the windless hover state is parallel to the horizontal plane S0. It will be appreciated that the windless hovering state of the drone referred to herein may be approximately equivalent to a takeoff or landing state of the drone on level ground.

Considering the influence of rotor blade slipstream on the free incoming flow when the unmanned aerial vehicle 1000 flies, the gradually increased installation angle of the plurality of airfoils 430 of the horn 400 along the direction from the root portion 410 to the tip portion 420 can play a certain rectifying effect on the free incoming flow, so as to reduce the flow resistance at the horn 400, reduce the flight burden of the unmanned aerial vehicle 1000, and increase the cruising ability of the unmanned aerial vehicle 1000.

Specifically, the incoming flow direction at different locations from the root 410 to the tip 420 of the horn 400 varies as a result of the rotor rotation. The wing profiles 430 at different cross-sectional positions of the horn 400 correspond to different mounting angles omega, so that a tangent line of a highest point of an outer contour at different cross-sectional positions of the horn 400 can be as close to an incoming flow direction at the position as possible when the unmanned aerial vehicle 1000 flies, and the rectification effect is optimal.

The following is further described with reference to the accompanying drawings.

Referring to FIG. 10, in some embodiments, the maximum thickness of each airfoil 430 is 47.7% of the chord length of the airfoil 430 to meet the structural strength and stiffness requirements of the airfoil 430.

Further, the airfoil 430 may be spindle-shaped, so that the horn 400 has a streamlined surface, further reducing the flow resistance of the drone 1000 during flight.

Referring to fig. 9 and 14, in some embodiments, the projection of the horn 400 on the normal plane S1 of the yaw axis of the drone 1000 is a trapezoid, and the side length of the trapezoid corresponding to the root 410 is greater than the side length of the trapezoid corresponding to the tip 420, so as to meet the requirements of the structural strength and rigidity of the horn 400.

In some embodiments, the chord length L of the airfoil 430 is inversely related to the stagger angle ω in a direction along the root 410 to the tip 420. That is, the longer the chord length of the airfoil 430 is, the smaller the corresponding mount angle ω is; the shorter the chord length L of the airfoil 430, the greater the corresponding stagger angle ω.

Specifically, the tip 420 is provided with a motor base 100, the motor base 100 has a mounting center 60 coinciding with the rotation axis of the motor 200, the body 300 has a symmetry plane 310, and the mounting center 60 has a reference distance from the symmetry plane 310.

In the following, the horn 400 is taken as the front horn of the drone 1000, wherein the front horn is the horn 400 close to the head 301 of the drone 1000. Referring to fig. 9, in the horn 400 shown in fig. 9, the extension direction of the protrusion 20 of the motor base 100 is toward the longer side of the projection of the horn 400 on the normal plane S1 of the yaw axis of the drone 1000.

Referring to fig. 11, at a position a1 29.2% of the reference distance from the symmetry plane 310, the installation angle ω f1 of the wing 430 is 33.24 ° ± 2.5 ° to play a role in rectification, so as to reduce the drag on the horn 400 when the drone 1000 flies. For example, the mounting angle ω f1 may be 30.74 °, 33.24 °, or 35.74 °; or any angle between 30.74 ° and 35.74 °, such as 30.75 °, 31.24 °, 32.56 °, 33.69 °, 34.11 °, 35.72 °, not to mention here.

Referring to fig. 12, at a position a2 that is 57.6% of the reference distance from the symmetry plane 310, the installation angle ω f2 of the wing profile 430 is 37.83 ° ± 2.5 °, so as to play a role in rectification and reduce the drag on the horn 400 when the drone 1000 flies. For example, the mounting angle ω f2 may be 35.33 °, 37.83 °, or 40.33 °; or any angle between 35.33 ° and 40.33 °, such as 35.75 °, 36.24 °, 37.56 °, 38.69 °, 39.11 °, 40.12 °, not to mention here.

Referring to fig. 13, at a position a3 that is 84.0% of the reference distance from the symmetry plane 310, the installation angle ω f3 of the wing profile 430 is 43.12 ° ± 2.5 ° to play a role in rectification, so as to reduce the drag on the horn 400 when the drone 1000 flies. For example, the mounting angle ω f3 may be 40.62 °, 43.12 °, or 45.62 °; or any angle between 40.62 ° and 45.62 °, such as 40.75 °, 41.24 °, 42.56 °, 43.69 °, 44.11 °, 45.12 °, not to mention here.

Referring to fig. 9, in some embodiments, the reference distance is 105.99mm ± 10.60mm, for example, the reference distance may be 95.39mm, 105.99mm, or 116.59 mm; or any distance between 95.39mm and 116.59mm, such as 96.77mm, 97.51mm, 98.47mm, 99.89mm, 100.21mm, 102.58mm, 104.78mm, 107.68mm, 109.23mm, 113.72mm, 115.99mm, and the like, which are not enumerated herein.

Referring to fig. 11, correspondingly, at a position a1 which is 29.2% of the reference distance from the symmetry plane 310, the chord length Lf1 of the airfoil 430 is 37.85mm ± 3.79mm, so as to meet the requirements of structural strength and rigidity of the airfoil 430. For example, the chord length Lf1 of the airfoil 430 may be 34.06mm, 37.85mm, or 41.64 mm; or any distance between 34.06mm and 41.64mm, such as 34.18mm, 35.77mm, 36.51mm, 37.47mm, 38.89mm, 39.21mm, 40.58mm, 41.18mm, etc., which are not listed herein.

Referring to fig. 12, correspondingly, at a position a2 which is 57.6% of the reference distance from the symmetry plane 310, the chord length Lf2 of the airfoil 430 is 30.76mm ± 3.08mm, so as to meet the requirements of structural strength and rigidity of the airfoil 430. For example, the chord length Lf2 of the airfoil 430 may be 27.68mm, 30.76mm, or 33.84 mm; or 27.88mm, 28.77mm, 29.51mm, 30.47mm, 31.89mm, 32.21mm, 33.58mm and the like, which are any distances between 27.68mm and 33.84mm, and are not listed here.

Referring to fig. 13, correspondingly, at a position a3 which is 84.0% of the reference distance from the symmetry plane 310, the chord length Lf3 of the airfoil 430 is 24.33mm ± 2.43mm, so as to meet the requirements of structural strength and rigidity of the airfoil 430. For example, the chord length Lf3 of the airfoil 430 may be 21.90mm, 24.33mm, or 26.76 mm; or any distance between 21.90mm and 26.76mm, such as 21.98mm, 22.77mm, 23.51mm, 24.47mm, 25.89mm, 26.21mm, etc., which are not listed herein.

In the examples of the present application, the reference distance is 105.99 mm. At 31mm from the symmetry plane 310, the stagger angle ω f1 of the airfoil 430 is 33.24 °, and the chord length Lf1 of the airfoil 430 is 37.85 mm. At a distance of 61mm from the symmetry plane 310, the stagger angle ω f2 of the airfoil 430 is 37.83 °, and the chord length Lf2 of the airfoil 430 is 30.76 mm. At 89mm from the plane of symmetry 310, the stagger angle ω f3 of the airfoil 430 is 43.12 °, and the chord length Lf3 of the airfoil 430 is 24.33 mm. So, can satisfy the requirement of the structural strength and the rigidity of wing section 430 to can play certain rectification effect, reduce the resistance that horn 400 received when unmanned aerial vehicle 1000 flies.

Referring to fig. 14, in some embodiments, the drone 1000 further includes another horn 400, the horn 400 being a rear horn of the drone 1000, wherein the rear horn is the horn 400 near the tail 303 of the drone 1000. As shown in fig. 14.

Referring to fig. 14 and 15, at a position B1 that is 27.1% of the reference distance from the symmetry plane 310, the installation angle ω B1 of the wing profile 430 is 27.19 ° ± 2.5 ° to play a role in rectification, so as to reduce the drag on the horn 400 when the drone 1000 flies. For example, the mounting angle ω b1 may be 24.69 °, 27.19 °, or 29.69 °; or any angle between 24.69 ° and 29.69 °, such as 24.75 °, 25.24 °, 26.56 °, 27.69 °, 28.11 °, 29.72 °, to name but a few.

Referring to fig. 16, at a position B2 that is 57.3% of the reference distance from the symmetry plane 310, the installation angle ω B2 of the wing profile 430 is 28.74 ° ± 2.5 °, so as to play a role in rectification and reduce the drag on the horn 400 when the drone 1000 flies. For example, the mounting angle ω b2 may be 26.24 °, 28.74 °, or 31.24 °; or any angle between 26.75 °, 27.24 °, 28.56 °, 29.69 °, 30.11 °, 31.12 °, etc., not to mention here.

Referring to fig. 17, at a position B3 85.4% of the reference distance from the symmetry plane 310, the installation angle ω B3 of the wing profile 430 is 31.80 ° ± 2.5 °, so as to play a role in rectification and reduce the drag on the horn 400 when the drone 1000 flies. For example, the mounting angle ω b3 may be 29.30 °, 31.80 °, or 34.30 °; or any angle between 29.30 ° and 34.30 °, such as 29.75 °, 30.24 °, 31.56 °, 32.69 °, 33.11 °, 34.12 °, not to mention here.

Referring to fig. 14, in some embodiments, the reference distance is 99.49mm ± 9.95mm, for example, the reference distance may be 89.54mm, 99.49mm, or 109.44 mm; or any distance between 89.54mm and 109.44mm, such as 90.77mm, 93.51mm, 95.47mm, 98.89mm, 100.21mm, 102.58mm, 104.78mm, 107.68mm, 109.23mm, which are not listed herein.

Referring to fig. 15, correspondingly, at a position B1 27.1% of the reference distance from the symmetry plane 310, the chord length Lb1 of the airfoil 430 is 33.90mm ± 3.39mm, so as to meet the requirements of structural strength and rigidity of the airfoil 430. For example, the chord length Lb1 of the airfoil 430 may be 30.51mm, 33.90mm, or 37.29 mm; or any distance between 30.51mm and 37.29mm, such as 30.08mm, 31.18mm, 32.77mm, 33.51mm, 34.47mm, 35.89mm, 36.21mm, 37.18mm, etc., which are not listed herein.

Referring to fig. 16, correspondingly, at a position B2 that is 57.3% of the reference distance from the symmetry plane 310, the chord length Lb2 of the airfoil 430 is 27.96mm ± 2.80mm, so as to meet the requirements of structural strength and rigidity of the airfoil 430. For example, the chord length Lb2 of the airfoil 430 may be 25.16mm, 27.96mm, or 30.76 mm; or any distance between 25.16mm and 30.76mm, such as 25.88mm, 26.77mm, 27.51mm, 28.47mm, 29.89mm, 30.21mm, etc., which are not listed herein.

Referring to fig. 17, correspondingly, at a position B3 85.4% of the reference distance from the symmetry plane 310, the chord length Lb3 of the airfoil 430 is 22.96mm ± 2.30mm, so as to meet the requirements of structural strength and rigidity of the airfoil 430. For example, the chord length Lb2 of the airfoil 430 may be 20.66mm, 22.96mm, or 25.26 mm; or any distance between 22.66mm and 25.26mm, such as 20.98mm, 20.77mm, 21.51mm, 22.47mm, 23.89mm, 24.21mm, etc., which are not listed herein. So, can be in order to satisfy the requirement of the structural strength and the rigidity of wing section 430 to can play certain rectification effect, reduce the resistance that horn 400 received when unmanned aerial vehicle 1000 flies.

In an embodiment of the application, the reference distance of the horn 400 near the tail 303 of the drone 1000 is 99.49 mm. At a distance of 27mm from the plane of symmetry 310, the stagger angle ω b1 of the airfoil 430 is 27.19 °, and the chord length Lb1 of the airfoil 430 is 33.90 mm. At a distance of 57mm from the plane of symmetry 310, the stagger angle ω b2 of the airfoil 430 is 28.74 °, and the chord length Lb2 of the airfoil 430 is 27.96 mm. At 85mm from the symmetry plane 310, the stagger angle ω b3 of the airfoil 430 is 31.80 °, and the chord length Lb2 of the airfoil 430 is 22.96 mm. So, can be in order to satisfy the requirement of the structural strength and the rigidity of wing section 430 to can play certain rectification effect, reduce the resistance that horn 400 received when unmanned aerial vehicle 1000 flies.

In conclusion, in the unmanned aerial vehicle 1000 of the embodiment of the present application, through chord length, thickness and the installation angle that set up horn 400 wing section 430, can make horn 400 play certain rectification effect, reduce the resistance that horn 400 receives when unmanned aerial vehicle 1000 flies to can reduce unmanned aerial vehicle 1000's flight consumption, improve unmanned aerial vehicle 1000's duration.

Referring to fig. 1 to 18, in the unmanned aerial vehicle 1000 according to the embodiment of the present application, the motor base 100 and the horn 400 are optimized respectively to improve the rectification effect of the motor base 100 and the horn 400, reduce the flow resistance of the motor base 100 when the unmanned aerial vehicle 1000 flies, reduce the flight burden of the unmanned aerial vehicle 1000, and increase the cruising ability of the unmanned aerial vehicle 1000. As shown in fig. 18, fig. 18 is a schematic diagram of the resistance experienced by the drone 1000 during flight, the ordinate of fig. 18 represents the distribution of the resistance of the drone 1000, the abscissa represents the spanwise position extending from the symmetry plane 310 of the fuselage 300 to the tip of the horn 400, and the position of the spanwise position 0.1m is approximately the position of the motor 200. It can be seen that compared with the non-optimized drone 1000, the drone 1000 with the optimized horn 400 has the advantages that the resistance applied to the horn 400 is significantly reduced, the resistance applied to the middle section of the horn 400 is reduced by approximately 50%, but the resistance applied to the motor 200 is not significantly reduced. Compared with the unmanned aerial vehicle 1000 which is not optimized, the unmanned aerial vehicle 1000 which is optimized as described above is adopted for both the horn 400 and the motor base 100, the resistance borne by the horn 400 is obviously reduced, the resistance borne by the middle section of the horn 400 is reduced by nearly 50%, the resistance borne by the motor 200 is also reduced by nearly 50%, and the resistance borne by the unmanned aerial vehicle 1000 during flying is greatly reduced.

Referring to fig. 19, in some embodiments, the drone 1000 may further include a foot stand 500, where the foot stand 500 is disposed on a side of the motor base 100 facing away from the motor 200, and the foot stand 500 is used to support the drone 1000 when the drone 1000 takes off and lands.

The foot rest 500 may be mounted on the horn 400 near the nose 301 of the drone 1000 as shown in fig. 9, or may be mounted on the horn 400 near the tail 303 of the drone 1000 as shown in fig. 14, without limitation.

Referring to fig. 20, the stand 500 is a flat structure. The longitudinal direction of the foot rest 500 is the direction away from the base 10 along the lower side of the base 10, the width direction of the foot rest 500 is the direction parallel to the axis from the head 301 to the tail 303, and the thickness direction of the foot rest 500 is the direction perpendicular to the width direction in the normal plane S1 of the yaw axis of the unmanned aerial vehicle 1000 for the foot rest 500. The length of the foot rest 500 is greater than the width and thickness of the foot rest 500, and the width of the foot rest 500 is greater than the thickness of the foot rest 500, so that the foot rest 500 forms a flat structure to have a good rectification effect.

In some embodiments, the width of the foot rest 500 is gradually decreased in a length direction extending from the lower side of the base 10 to a direction away from the base 10, so as to have a certain rectification function, so that an incoming flow can flow along the surface of the foot rest 500 to reduce the fluid resistance at the foot rest 500.

In some embodiments, the surface of the foot rest 500 in the width direction is streamlined to facilitate the flow attached to the surface of the foot rest 500, thereby reducing the fluid resistance at the foot rest 500. Specifically, in one embodiment, the cross section of the foot rest 500 taken by the normal plane S1 of the yaw axis of the drone 1000 is spindle-shaped to facilitate the flow of incoming current against the surface of the foot rest 500, thereby reducing the fluid resistance at the foot rest 500.

In some embodiments, the drone 1000 further includes an antenna (not shown), and the thickness of the foot stand 500 is greater than the width of the antenna. Specifically, the maximum thickness of the cross section of the foot rest 500 taken by the normal plane S1 of the yaw axis of the drone 1000 is 47.7% of the chord length of the cross section, so that the antenna can be housed in the foot rest 500.

To sum up, in the unmanned aerial vehicle 1000 of this application embodiment, through the foot rest 500 that sets up flat column structure, make the resistance that foot rest 500 department received can reduce when unmanned aerial vehicle 1000 flies to can reduce unmanned aerial vehicle 1000's flight consumption, improve unmanned aerial vehicle 1000's duration.

Referring to fig. 1 to 21, in the unmanned aerial vehicle 1000 according to the embodiment of the present application, the motor base 100, the horn 400, and the foot rest 500 are optimized respectively to improve the rectification effect of the motor base 100, the horn 400, and the foot rest 500, reduce the flow resistance at the motor base 100, the horn 400, and the foot rest 500 when the unmanned aerial vehicle 1000 flies, reduce the flight burden of the unmanned aerial vehicle 1000, and increase the cruising ability of the unmanned aerial vehicle 1000. As shown in fig. 21, fig. 21 is a schematic diagram of the resistance experienced by the drone 1000 during flight, the ordinate of fig. 21 represents the distribution of the resistance of the drone 1000, the abscissa represents the spanwise position extending from the symmetry plane 310 of the fuselage 300 to the tip of the horn 400, and the position of the motor 200 is approximately near the 0.1m spanwise position. It can be seen that, compared with the non-optimized unmanned aerial vehicle 1000, the resistance of the unmanned aerial vehicle 1000 subjected to the optimization on the motor base 100, the horn 400 and the foot rest 500 is significantly reduced at the horn 400, the resistance of the middle section of the horn 400 is reduced by approximately 50%, the resistance of the motor 200 is also significantly reduced by approximately 50%, and the resistance of the unmanned aerial vehicle 1000 during flying is greatly reduced.

Referring to fig. 1 to 3, in some embodiments, the drone 1000 may further include a first indicator light 600, and the first indicator light 600 is mounted to the protruding portion 20 and exposed from a rear side of the drone 1000. Specifically, the first indicator light 600 is oriented to cross the extending direction of the horn 400.

The number of the first indicator lamps 600 may be one or more, for example, 1, 2, 3, 4, 5, etc. of the first indicator lamps 600 may be mounted on the protrusion 20, which is not limited herein. The first indicator light 600 may emit one or more colored light signals to indicate status information of the drone 1000. For example, 1, 2, 3, 4, 5, etc. optical signals are emitted, but not limited thereto.

For example, the first indicator light 600 includes 3, which are capable of emitting a red light signal, a green light signal, and a yellow light signal, respectively. Different status information of the drone 1000 may be indicated according to the light signal of the first indicator light 600. For example, a green light slow flash indicates that the drone 1000 may fly safely; the yellow light flash signals the interruption of the remote controller signal; the red light flashes slowly to indicate low power alarm, the red light lights normally to indicate a serious error, etc., without limitation.

Referring to fig. 1 and fig. 2, in some embodiments, the unmanned aerial vehicle 1000 may further include a second indicator light 700 disposed on the arm 400, and an extending direction of a light emitting surface of the second indicator light 700 is parallel to an extending direction of the arm 400.

The number of the second indicator lights 700 may be one or more, for example, 1, 2, 3, 4, 5, etc. of the second indicator lights 700 may be mounted on each horn 400, which is not limited herein. The second indicator light 700 may emit one or more colored light signals to indicate status information of the drone 1000. For example, 1, 2, 3, 4, 5, etc. optical signals are emitted, but not limited thereto.

For example, the second indicator light 700 includes 3, which are capable of emitting red, green, and yellow light signals, respectively. Different status information of the drone 1000 may be indicated according to the light signal of the second indicator light 700. For example, a green light slow flash indicates that the drone 1000 may fly safely; the yellow light flash signals the interruption of the remote controller signal; the red light is slowly flashed to indicate low power alarm, the red light is normally on to indicate a serious error, etc., without limitation.

Referring to fig. 19, in some embodiments, the drone 1000 may further include a third indicator light 800, the third indicator light 800 being mounted to the foot stand 500. Specifically, the third indicator light 800 is oriented to cross the extending direction of the horn 400.

The number of the third indicator lamps 800 may be one or more, for example, 1, 2, 3, 4, 5, etc. of the third indicator lamps 800 may be mounted on the foot stand 500, which is not limited herein. The third indicator light 800 may emit one or more colored light signals to indicate status information of the drone 1000. For example, 1, 2, 3, 4, 5, etc. optical signals are emitted, but not limited thereto.

For example, the third indicator light 800 includes 3, which are capable of emitting red light signals, green light signals, and yellow light signals, respectively. Different status information of the drone 1000 may be indicated according to the light signal of the third indicator light 800. For example, a green slow flash indicates that the drone 1000 may fly safely; the yellow light flash signals the interruption of the remote controller signal; the red light is slowly flashed to indicate low power alarm, the red light is normally on to indicate a serious error, etc., without limitation.

Referring to fig. 1, 2, 9, and 19, in some embodiments, the drone 1000 includes at least one of a first indicator light 600, a second indicator light 700, and a third indicator light 800. For example, the drone 1000 includes only the first indicator light 600; the drone 1000 includes only the second indicator light 700; the drone 1000 includes only the third indicator light 800; the drone 1000 includes only the first indicator light 600 and the second indicator light 700; the drone 1000 includes only the first indicator light 600 and the third indicator light 800; the drone 1000 includes only the second indicator light 700 and the third indicator light 800; and the unmanned aerial vehicle 1000 simultaneously comprises one of the schemes of the first indicator light 600, the second indicator light 700, the third indicator light 800 and the like. When the drone 1000 includes at least two of the at least first indicator light 600, the second indicator light 700, and the third indicator light 800, the combination of the light signals emitted by the at least two indicator lights can indicate the status information of the drone 1000 together.

For example, the unmanned aerial vehicle 1000 includes the first indicator light 600, the second indicator light 700, and the third indicator light 800 at the same time, wherein the first indicator light 600 can emit a red light signal, the second indicator light 700 can emit a yellow light signal, and the third indicator light 800 can emit a green light signal, and different status information of the unmanned aerial vehicle 1000 can be indicated according to the light signals of the first indicator light 600, the second indicator light 700, and the third indicator light 800. For example, the first indicator light 600 and the second indicator light 700 flash alternately, that is, when the red light and the yellow light flash alternately, it indicates that the compass data is wrong; for another example, when the second indicator light 700 and the third indicator light 800 alternately flash, that is, the yellow-green light alternately flashes, it indicates that the system of the unmanned aerial vehicle 1000 is in the self-checking state.

Referring to fig. 1, 2, 9, and 14, the present application further provides an unmanned aerial vehicle 2000, where the unmanned aerial vehicle 2000 includes a body 300 and a horn 400, a root 410 of the horn 400 is connected to the body 300, the horn 400 includes a root 410 for connecting to the body 300 of the unmanned aerial vehicle 2000 and a tip 420 opposite to the root 410, and an installation angle ω of a plurality of airfoils 430 of the horn 400 gradually increases along a direction from the root 410 to the tip 420, and the installation angle ω is an included angle between a chord length L of the airfoil 430 of the horn 400 and a plane S1 perpendicular to a yaw axis of the unmanned aerial vehicle 2000.

The specific structure of the horn 400 is the same as the horn 400 of fig. 9 and 14, and the detailed description thereof is omitted. The tip 420 of the horn 400 may be mounted to the motor mount 100 of fig. 5 and/or 8, as previously described, without limitation.

In the unmanned aerial vehicle 2000 of this application embodiment, chord length, thickness and the angle of erection through setting up horn 400 wing section 430 can make horn 400 play certain rectification effect, reduce the resistance that horn 400 received when unmanned aerial vehicle 2000 flies to can reduce unmanned aerial vehicle 2000's flight consumption, improve unmanned aerial vehicle 2000's duration. Referring to fig. 18, compared with the non-optimized drone, the resistance of the drone 2000 with the optimized horn 400 at the horn 400 is significantly reduced, and the resistance at the middle section of the horn 400 is reduced by approximately 50%, which has a significant effect on reducing the resistance of the drone 2000 in the flying state.

Referring to fig. 1, 2, 19, and 20, the present application further provides an unmanned aerial vehicle 3000, where the unmanned aerial vehicle 3000 includes a fuselage 300, a horn 400, and a foot stand 500. Foot rest 500 sets up in one side of horn 400, and foot rest 500 is used for supporting unmanned aerial vehicle 3000 when unmanned aerial vehicle 3000 takes off and land, and foot rest 500 is flat column structure.

The specific structure of the foot rest 500 is the same as that of the foot rest 500 shown in fig. 19 and 20, and the detailed description thereof is omitted. The drone 3000 may include the motor mount 100 of fig. 5 and/or 8 described above, and mount a foot stand 500 under the motor mount 100 of fig. 5 and/or 8 described above; the drone 3000 may further include the horn 400 of fig. 9 and/or 14, as previously described, and a foot stand 500 may be mounted to one side of the horn 400 of fig. 9 and/or 14, as previously described, without limitation.

In the unmanned aerial vehicle 3000 of this application embodiment, through the foot rest 500 that sets up flat structure, make the resistance that foot rest 500 department received can reduce when unmanned aerial vehicle 3000 flies to can reduce unmanned aerial vehicle 3000's flight consumption, improve unmanned aerial vehicle 3000's duration. Referring to fig. 21, compared with the non-optimized unmanned aerial vehicle 3000, the resistance of the unmanned aerial vehicle 3000 optimized for the motor base 100, the horn 400, and the foot rest 500 at the horn 400 is significantly reduced, the resistance at the middle section of the horn 400 is reduced by approximately 50%, the resistance at the motor 200 is also significantly reduced by approximately 50%, and the resistance of the unmanned aerial vehicle 3000 during flight is greatly reduced.

In the description herein, references to the description of the terms "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples" or the like mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present application. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

Claims

1. An unmanned aerial vehicle, comprising:

a motor; and

the motor cabinet, the motor cabinet includes base and bulge, the base is used for the installation the motor, the bulge is followed the base extends the protrusion unmanned aerial vehicle's flight state is down, the bulge is at least partial to face unmanned aerial vehicle's rear side convergent extension.

2. The drone of claim 1, wherein the surface of the projection is curved.

3. The drone of claim 1, further comprising a first indicator light mounted to the projection and exposed from a rear side of the drone.

4. The unmanned aerial vehicle of claim 3, further comprising a horn, the motor mount being mounted to the horn, the first indicator light being oriented to intersect a direction of extension of the horn.

5. The drone of claim 1, wherein a projected profile of the motor mount in a normal plane to a yaw axis of the drone is drop-shaped or spindle-shaped.

6. The unmanned aerial vehicle of claim 1, wherein the base comprises a first surface, the base defines a receiving cavity on the first surface, and the motor is partially received in the receiving cavity; the motor base further comprises an extension portion, the extension portion extends from the protruding portion to one side where the first face of the base is located, and the extension portion surrounds at least part of the area of the motor.

7. The drone of claim 6, wherein a projected profile of the motor mount in a normal plane to a yaw axis of the drone includes an arcuate receptacle section and a fairing section connected to the receptacle section, the fairing section tapering in a direction away from the receptacle section.

8. The drone of claim 7, wherein a portion of a projected contour of the base in the plane corresponds to the housing section, and at least a portion of a projected contour of the extension in the plane corresponds to the fairing section.

9. A drone according to claim 7, wherein the projection profile of the extension in the plane is trapezoidal.

10. A drone according to claim 6, wherein the base comprises a second face connected to the first face of the base and distant from the extension, the second face being an arc face, the difference between the angle a between the plane and the local tangent to the trailing edge point of the profile of the second face of the base and the angle of inclination β of the body of the drone at cruise being within a first predetermined range.

11. The unmanned aerial vehicle of claim 6, wherein the base includes a second face, the second face is connected with the first face of the base and is far away from the extension portion, the second face is an arc face, and an included angle θ between a tangent of a highest point of a profile of the second face of the base and the plane has a value range of [30 °, 35 ° ].

12. The drone of claim 6, wherein the extension includes a first face and a second face, the first face of the extension surrounds at least a partial area of the motor, the second face of the extension meets the first face of the extension, and a difference between an angle γ between a tangent to a highest point of a profile of the second face of the extension and the plane and an angle β of inclination of the body of the drone while cruising is within a second predetermined range.

13. The unmanned aerial vehicle of claim 6, wherein the extension comprises a first surface and a second surface, the first surface of the extension surrounds at least a partial region of the motor, the second surface of the extension is contiguous with the first surface of the extension, and an included angle between a tangent of a highest point of a profile of the second surface of the extension and the plane has a value in a range of [30 °, 40 ° ].

14. The unmanned aerial vehicle of claim 7, wherein a projected profile of the unmanned aerial vehicle in the plane further comprises a flow guide section, the flow guide section and the flow rectification section are respectively located at two sides of the accommodating section, and the flow guide section is tapered along a direction away from the accommodating section.

15. The drone of claim 14, wherein the base includes a flow guide portion and a flow straightening portion, at least a portion of a projection profile of the flow guide portion in the plane corresponds to the flow guide section, at least a portion of a projection profile of the flow straightening portion in the plane corresponds to the receiving section, and the protrusion corresponds to the flow straightening section.

16. The drone of claim 15, wherein the fairing section is trapezoidal and the inducer section is triangular.

17. The unmanned aerial vehicle of claim 14, wherein an angle between a tangent line of a highest point of an outer contour of the fairing portion and the plane is the same as an inclination angle of the unmanned aerial vehicle body in cruising.

18. An unmanned aerial vehicle according to claim 14, wherein an angle Φ between a tangent to a highest point of the outer contour of the fairing portion and the plane is in a range of [30 °, 40 ° ].

19. The unmanned aerial vehicle of any one of claims 1-18, wherein the horn comprises a root portion for connecting with a fuselage of the unmanned aerial vehicle and a tip portion opposite to the root portion, and an installation angle of a plurality of wing profiles of the horn gradually increases along the direction from the root portion to the tip portion, and the installation angle is an included angle between a chord length of the wing profile of the horn and a normal plane of a yaw axis of the unmanned aerial vehicle.

20. The drone of claim 19, wherein the maximum thickness of each of the airfoils is 47.7% of a chord length of the airfoil.

21. A drone according to claim 19, wherein the aerofoil is spindle shaped.

22. The drone of claim 19, wherein the horn projects on a normal plane to a yaw axis of the drone in a trapezoid shape having a greater side length corresponding to the root than the tip.

23. An unmanned aerial vehicle as defined in claim 19, wherein the motor mount is disposed at the tip and has a mounting center coincident with the motor shaft, the fuselage has a plane of symmetry, the mounting center has a reference distance to the plane of symmetry, and a chord length of the airfoil is inversely related to the mounting angle in a direction along the root to the tip.

24. A drone according to claim 23, characterized in that the mounting angle of the wing profile is 33.24 ° ± 2.5 ° at 29.2% of the reference distance from the symmetry plane.

25. A drone according to claim 23, wherein the reference distance is 105.99mm ± 10.60mm, and the chord length of the airfoil is 37.85mm ± 3.79mm at 29.2% of the reference distance from the plane of symmetry.

26. A drone according to claim 23, wherein the reference distance is 105.99mm, and the aerofoil has a stagger angle of 33.24 ° and a chord length of 37.85mm at a distance of 31mm from the plane of symmetry.

27. A drone according to claim 23, characterised in that the mounting angle of the wing profile is 37.83 ° ± 2.5 ° at 57.6% of the reference distance from the symmetry plane.

28. A drone according to claim 23, wherein the reference distance is 105.99mm ± 10.60mm, and the chord length of the airfoil is 30.76mm ± 3.08mm at a distance of 57.6% of the reference distance from the plane of symmetry.

29. A drone according to claim 23, wherein the reference distance is 105.99mm, and the aerofoil has a stagger angle of 37.83 ° at a distance of 61mm from the plane of symmetry, and a chord length of 30.76 mm.

30. A drone according to claim 23, characterised in that the mounting angle of the wing profile is 43.12 ° ± 2.5 ° at 84.0% of the reference distance from the symmetry plane.

31. A drone according to claim 23, wherein the reference distance is 105.99mm ± 10.60mm, and the chord length of the airfoil is 24.33mm ± 2.43mm at 84.0% of the reference distance from the plane of symmetry.

32. A drone according to claim 23, wherein the reference distance is 105.99mm, the stagger angle of the aerofoil is 43.12 ° at 89mm from the plane of symmetry, and the chord length of the aerofoil is 24.33 mm.

33. A drone according to any of claims 19 to 32, wherein the horn is a horn close to the nose of the drone.

34. A drone according to claim 23, characterised in that the mounting angle of the wing profile is 27.19 ° ± 2.5 ° at a distance of 27.1% of the reference distance from the symmetry plane.

35. A drone according to claim 23, wherein the reference distance is 99.49mm ± 9.95mm, and the chord length of the airfoil is 33.90mm ± 3.39mm at 27.1% of the reference distance from the plane of symmetry.

36. A drone according to claim 23, wherein the reference distance is 99.49mm, and the aerofoil has a stagger angle of 27.19 ° at a distance of 27mm from the plane of symmetry, and a chord length of 33.90 mm.

37. A drone according to claim 23, characterized in that the mounting angle of the wing profile is 28.74 ° ± 2.5 ° at 57.3% of the reference distance from the symmetry plane.

38. A drone according to claim 23, wherein the reference distance is 99.49mm ± 9.95mm, and the chord length of the airfoil is 27.96mm ± 2.80mm at 57.3% of the reference distance from the plane of symmetry.

39. A drone according to claim 23, wherein the reference distance is 99.49mm, and the aerofoil has a stagger angle of 28.74 ° at 57mm from the plane of symmetry, and a chord length of 27.96 mm.

40. A drone according to claim 23, characterized in that the mounting angle of the wing profile is 31.80 ° ± 2.5 ° at a distance from the symmetry plane of 85.4% of the reference distance.

41. A drone according to claim 23, wherein the reference distance is 99.49mm ± 9.95mm, and the chord length of the airfoil is 22.96mm ± 2.30mm at 85.4% of the reference distance from the plane of symmetry.

42. A drone according to claim 23, wherein the reference distance is 99.49mm, the stagger angle of the aerofoil is 31.80 ° at 85mm from the plane of symmetry, and the chord length of the aerofoil is 22.96 mm.

43. A drone according to any of claims 19 to 23 and 34 to 42, wherein the horn is a horn near the tail of the drone.

44. The unmanned aerial vehicle of claim 19, further comprising a second indicator light disposed on the arm, wherein a light emitting surface of the second indicator light extends in a direction parallel to the arm.

45. The unmanned aerial vehicle of claim 1, further comprising a foot rest disposed on a side of the motor mount facing away from the motor, the foot rest configured to support the unmanned aerial vehicle when the unmanned aerial vehicle is taking off and landing.

46. A drone according to claim 45, wherein the maximum thickness of the cross-section of the foot rest taken by the normal plane to the yaw axis of the drone is 47.7% of the chord length of the cross-section.

47. A drone according to claim 45, wherein the foot rests are spindle-shaped in cross-section taken by a plane normal to the yaw axis of the drone.

48. A drone according to claim 45, wherein the foot rests are of progressively smaller width in a lengthwise direction extending from the underside of the base away from the base.

49. The drone of claim 45, wherein the foot rests are streamlined in their width-wise surface.

50. A drone according to claim 45, further comprising an antenna, the foot rest having a thickness greater than a width of the antenna.

51. An unmanned aerial vehicle as claimed in claim 45, wherein the foot rests are flat structures.

52. A drone according to claim 45, further including a third indicator light mounted to the foot rest.

53. A drone according to claim 52, further comprising a horn, the third indicator light being oriented crosswise to the direction of extension of the horn.

54. The utility model provides an unmanned aerial vehicle, its characterized in that, including fuselage and horn, the root of horn with the fuselage is connected, the horn including be used for with the root that unmanned aerial vehicle's fuselage is connected and with the root is relative tip, edge the root extremely in the tip direction, the erection angle of a plurality of wing types of horn crescent, the erection angle does the chord length of the wing type of horn with contained angle between the normal plane of unmanned aerial vehicle's driftage axle.

55. A drone according to claim 54, wherein the maximum thickness of each aerofoil is 47.7% of the chord length of the aerofoil.

56. A drone according to claim 54, wherein the aerofoil is spindle shaped.

57. A drone according to claim 54, wherein the arm projects in a trapezium on a normal plane to the yaw axis of the drone, the trapezium having a greater length of a side corresponding to the root than a length of a side corresponding to the tip.

58. An unmanned aerial vehicle according to claim 54, wherein the motor mount is provided at the tip and has a mounting center coincident with the motor shaft, the fuselage has a plane of symmetry, the mounting center has a reference distance to the plane of symmetry, and the chord length of the airfoil is inversely related to the mounting angle in a direction along the root to the tip.

59. A drone according to claim 58, characterised in that the mounting angle of the wing profile is 33.24 ° ± 2.5 ° at a distance of 29.2% of the reference distance from the plane of symmetry.

60. A drone according to claim 58, wherein the reference distance is 105.99mm ± 10.60mm, and the chord length of the aerofoil is 37.85mm ± 3.79mm at 29.2% of the reference distance from the plane of symmetry.

61. A drone according to claim 58, wherein the reference distance is 105.99mm at 31mm from the plane of symmetry, the angle of incidence of the aerofoil is 33.24 °, and the chord length of the aerofoil is 37.85 mm.

62. A drone according to claim 58, characterised in that the mounting angle of the wing profile is 37.83 ° ± 2.5 ° at 57.6% from the symmetry plane of the reference distance.

63. A drone according to claim 58, wherein the reference distance is 105.99mm ± 10.60mm, and the chord length of the airfoil is 30.76mm ± 3.08mm at a distance of 57.6% of the reference distance from the plane of symmetry.

64. A drone according to claim 58, wherein the reference distance is 105.99mm at 61mm from the plane of symmetry, the angle of incidence of the aerofoil is 37.83 °, and the chord length of the aerofoil is 30.76 mm.

65. A drone according to claim 58, characterised in that the mounting angle of the wing profile is 43.12 ° ± 2.5 ° at 84.0% from the symmetry plane of the reference distance.

66. A drone according to claim 58, wherein the reference distance is 105.99mm ± 10.60mm, and the chord length of the airfoil is 24.33mm ± 2.43mm at 84.0% of the reference distance from the plane of symmetry.

67. A drone according to claim 58, wherein the reference distance is 105.99mm at 89mm from the plane of symmetry, the stagger angle of the aerofoil is 43.12 °, and the chord length of the aerofoil is 24.33 mm.

68. A drone according to any of claims 54 to 67, wherein the horn is a horn close to the nose of the drone.

69. A drone according to claim 58, characterised in that the mounting angle of the wing profile is 27.19 ° ± 2.5 ° at a distance of 27.1% of the reference distance from the plane of symmetry.

70. A drone according to claim 58, wherein the reference distance is 99.49mm ± 9.95mm, and the chord length of the airfoil is 33.90mm ± 3.71mm at 27.1% of the reference distance from the plane of symmetry.

71. A drone according to claim 58, wherein the reference distance is 99.49mm, and the aerofoil has a stagger angle of 27.19 ° at a distance of 27mm from the plane of symmetry, and a chord length of 33.90 mm.

72. A drone according to claim 58, characterised in that the mounting angle of the aerofoil is 60.74 ° ± 2.5 ° at 57.3% of the reference distance from the plane of symmetry.

73. A drone according to claim 58, wherein the reference distance is 99.49mm ± 9.95mm, and the chord length of the airfoil is 59.96mm ± 2.80mm at 57.3% of the reference distance from the plane of symmetry.

74. A drone according to claim 58, wherein the reference distance is 99.49mm, and the aerofoil has a stagger angle of 60.74 ° at a distance of 61mm from the plane of symmetry, and a chord length of 59.96 mm.

75. A drone according to claim 58, characterised in that the mounting angle of the aerofoil is 63.80 ° ± 2.5 ° at 85.4% of the reference distance from the plane of symmetry.

76. A drone according to claim 58, wherein the reference distance is 99.49mm ± 9.95mm, and the chord length of the airfoil is 22.96mm ± 2.62mm at 85.4% of the reference distance from the plane of symmetry.

77. A drone according to claim 58, wherein the reference distance is 99.49mm, the stagger angle of the aerofoil is 63.80 ° at 89mm from the plane of symmetry, and the chord length of the aerofoil is 22.96 mm.

78. A drone according to any of claims 54 to 77, wherein the horn is a horn near the tail of the drone.

79. An unmanned aerial vehicle, comprising:

a fuselage and a horn; and

the foot rest, the foot rest sets up one side of horn, the foot rest is used for unmanned aerial vehicle supports when taking off and land unmanned aerial vehicle, the foot rest is flat column structure.

80. A drone as claimed in claim 79, wherein the maximum thickness of the cross-section of the foot rest taken by the normal plane to the yaw axis of the drone is 47.7% of the chord length of the cross-section.

81. A drone as claimed in claim 79, wherein the foot rests are spindle-shaped in cross-section taken by a plane normal to a yaw axis of the drone.

82. An unmanned aerial vehicle according to claim 79, further comprising an indicator light arranged on the foot rest, wherein the extending direction of the light emitting surface of the indicator light intersects with the extending direction of the horn.

83. A drone as claimed in claim 79, wherein the maximum thickness of the cross-section of the foot rest taken by a normal plane to the yaw axis of the drone is 47.7% of the chord length of the cross-section.

84. A drone as claimed in claim 79, wherein the foot rests are spindle-shaped in cross-section taken by a plane normal to a yaw axis of the drone.

85. A drone as claimed in claim 79, further comprising a motor mount extending in the length of the flat structure from the underside of the motor mount towards a direction away from the motor mount, the foot prop being of progressively smaller width.

86. A drone as claimed in claim 79, wherein the width-wise surface of the foot rests is streamlined.

87. A drone as claimed in claim 79, further comprising an antenna, the foot rest having a thickness greater than a width of the antenna.