CN212172567U - Unmanned plane - Google Patents

Abstract

The utility model discloses an unmanned aerial vehicle, unmanned aerial vehicle includes: the device comprises a machine body, wherein a containing cavity is arranged on the machine body and is provided with an open hole positioned on the machine body; the driving assembly is arranged in the accommodating cavity; the functional assembly is connected with the driving assembly, the driving assembly drives the functional assembly to move between a first position and a second position, at least part of the functional assembly is located in the accommodating cavity in the first position, and the functional assembly is located outside the accommodating cavity in the second position. According to the utility model discloses an unmanned aerial vehicle, when the functional unit was out of work, drive assembly drive functional unit moved the first position for at least part of functional unit is located and holds the intracavity, thereby reduces the windage when unmanned aerial vehicle flies, and in addition when unmanned aerial vehicle standby, at least part of functional unit is located and holds the intracavity and also can reduce unmanned aerial vehicle's volume, makes things convenient for unmanned aerial vehicle's transportation and accomodates.

Description

Unmanned plane

Technical Field

The utility model belongs to the technical field of unmanned vehicles, particularly relate to an unmanned aerial vehicle.

Background

With the development of society, both industrial aircrafts and consumer aircrafts have made great progress, and especially small unmanned aircrafts represented by multi-propeller unmanned aircrafts and fixed-wing unmanned aircrafts are widely applied in various application fields, such as the fields of aerial photography, surveying and mapping and the like. Outside the fuselage was located to the function module during operation, the windage increase of unmanned vehicles when flying can be made like this, makes unmanned vehicles's whole volume great simultaneously, is difficult to accept the transportation.

SUMMERY OF THE UTILITY MODEL

The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, the utility model provides an unmanned aerial vehicle, unmanned aerial vehicle can accomodate functional module's at least part in the fuselage to the windage when reducing unmanned aerial vehicle flight.

According to the utility model discloses unmanned aerial vehicle, include: the device comprises a machine body, wherein a containing cavity is arranged on the machine body and is provided with an open hole positioned on the machine body; the driving assembly is arranged in the accommodating cavity; the functional assembly is connected with the driving assembly, the driving assembly drives the functional assembly to move between a first position and a second position, at least part of the functional assembly is located in the accommodating cavity in the first position, and the functional assembly is located outside the accommodating cavity in the second position.

According to the utility model discloses unmanned aerial vehicle, when the functional unit was out of work, drive assembly drive functional unit moved the primary importance for at least part of functional unit is located and holds the intracavity, thereby reduces the windage when unmanned aerial vehicle flies, and in addition when unmanned aerial vehicle standby, at least part of functional unit was located and holds the intracavity and also can reduce unmanned aerial vehicle's volume, makes things convenient for unmanned aerial vehicle's transportation and accomodates. When the functional module worked, drive assembly drive functional component moved to the second position for the functional component is located and holds the chamber outside, reduces the possibility that the fuselage sheltered from to the field of vision of functional component.

Optionally, the drive assembly comprises: the device comprises a fixed frame, a first connecting rod group, a second connecting rod group and a power assembly. The mount is fixed in hold the chamber with open mouthful on the relative wall, the one end of first connecting rod group is rotated with the one end of mount and is connected, the one end of second connecting rod group is rotated with the other end of mount and is connected, the other end of first connecting rod group and the other end of second connecting rod group all rotationally be connected with functional unit. The power assembly is arranged in the accommodating cavity and connected with the second connecting rod group to drive the second connecting rod group to rotate relative to the fixed frame.

Optionally, the power assembly includes a motor, and one end of the second linkage close to the fixed frame is connected to an output shaft of the motor.

Optionally, the method further comprises: the fixing base is connected with the other end of the first connecting rod group and the other end of the second connecting rod group in a rotating mode, and the functional assembly is connected with the fixing base.

Optionally, the method further comprises: the shock-absorbing piece is arranged between the fixed seat and the functional component.

Optionally, the first link group includes two spaced first links, one end of each first link is rotatably connected to the fixing frame, and the other end of each first link is rotatably connected to the fixing base.

Optionally, the second linkage includes two spaced apart second connecting rods, and one end of each second connecting rod all is connected with the mount rotation, and the other end of each second connecting rod all is connected with the fixing base rotation.

Optionally, the plane of the fixing seat is parallel to the plane of the fixing frame.

According to some embodiments of the invention, the open mouth is located on the lower surface of the fuselage.

According to some embodiments of the invention, the functional component comprises: the holder is connected with the driving assembly; the camera is rotationally connected with the holder.

Additional aspects and advantages of the invention 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 the invention.

Drawings

The above and/or additional aspects and advantages of the present invention 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 view of functional components of an unmanned aerial vehicle according to an embodiment of the present invention in a first position;

fig. 2 is a schematic view of functional components of an unmanned aerial vehicle according to an embodiment of the invention in a second position;

fig. 3 is a schematic diagram of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 4 is an enlarged view at a in fig. 3.

Reference numerals:

the unmanned aerial vehicle 1 is provided with a control system,

the body 10, the accommodating cavity 102, the opening 104, the driving assembly 20, the fixing frame 21, the first linkage 22, the first link 222, the second linkage 23, the second link 232, the power assembly 24, the motor 242,

the functional components 30, the pan and tilt head 302, the camera 304,

the length of the fixing base 40, the shock absorbing member 50,

a fixed wing 60, a first wing section 61, a second wing section 62, a wingtip winglet 63, an aileron 64,

a first power mechanism 70, a wing arm 71, a first power unit 72, a first propeller 73,

a tail wing 80, a tail wing plate 81, a tail stay rod 82, a tail stay seat 83,

a second power mechanism 90, a base 91, a second power unit 92 and a second propeller 93.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like 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 drawings are exemplary only for the purpose of explaining the present invention, and should not be construed as limiting the present invention. It should be appreciated that the various concepts and embodiments described above, as well as those described in greater detail below, may be implemented in any of numerous ways, as the disclosed concepts and embodiments are not limited to any implementation. Additionally, some aspects of the present disclosure may be used alone or in any suitable combination with other aspects of the present disclosure.

The following describes the unmanned aerial vehicle 1 according to an embodiment of the present invention with reference to the drawings.

As shown in fig. 1, fig. 3 and fig. 4, according to the utility model discloses unmanned aerial vehicle 1 includes: a body 10, a drive assembly 20, and a functional assembly 30.

Specifically, the main body 10 is provided with a receiving cavity 102, and the receiving cavity 102 has an open opening 104 located on the main body 10, and it is understood that the open opening 104 may be directed to the upper side of the main body 10 or to the lower side of the main body 10. The driving assembly 20 is disposed in the receiving cavity 102, and the functional assembly 30 is connected to the driving assembly 20. The driving assembly 20 drives the functional assembly 30 to move between a first position, as shown in fig. 1, in which at least a portion of the functional assembly 30 is located within the receiving cavity 102, and a second position, as shown in fig. 2, in which the functional assembly 30 is located outside the receiving cavity 102. It should be noted that the "first position" and the "second position" are positions corresponding to the functional component 30 when the functional component 30 does not need to operate and the functional component 30 operates, respectively.

When functional unit 30 was out of work, drive assembly 20 drive functional unit 30 moved to the first position for at least part of functional unit 30 is located and holds chamber 102, thereby reduces the windage when unmanned aerial vehicle 1 flies, and in addition when unmanned aerial vehicle 1 standby, at least part of functional unit 30 is located and holds chamber 102 and also can reduce unmanned aerial vehicle 1's volume, makes things convenient for unmanned aerial vehicle 1's transportation and accomodates. When the functional module works, the driving component 20 drives the functional component 30 to move to the second position, so that the functional component 30 is located outside the accommodating cavity 102, the possibility that the visual field of the functional component 30 is blocked by the machine body 10 is reduced, and the functional component 30 is convenient to work.

Unmanned aerial vehicle 1 can be applied to fields such as aerial photography survey, electric power patrol and survey, environmental monitoring and disaster patrol, and correspondingly, functional module can be the module of carrying out corresponding function, for example, when unmanned aerial vehicle 1 is applied to aerial photography survey field, functional module can be camera 304.

In some embodiments of the present invention, the opening of the opening 104 faces downward, so that the driving assembly 20 is not easily interfered with other components on the unmanned aerial vehicle 1 when in the second position, thereby ensuring the reliability of the operation of the functional assembly 30.

According to the utility model discloses unmanned aerial vehicle 1, when functional unit 30 was out of work, drive assembly 20 drive functional unit 30 moved the first position for at least part of functional unit 30 is located and holds chamber 102, thereby reduces the windage when unmanned aerial vehicle 1 flies, and in addition when unmanned aerial vehicle 1 standby, at least part of functional unit 30 is located and holds chamber 102 and also can reduce unmanned aerial vehicle 1's volume, makes things convenient for unmanned aerial vehicle 1's transportation and accomodate. When the functional module is in operation, the driving component 20 drives the functional component 30 to move to the second position, so that the functional component 30 is located outside the accommodating cavity 102, and the possibility of the visual field of the functional component 30 being blocked by the machine body 10 is reduced.

Alternatively, as shown in fig. 1, the driving assembly 20 includes: a fixed frame 21, a first linkage 22, a second linkage 23 and a power assembly 24.

As shown in fig. 3 and 4, specifically, the fixing frame 21 is fixed to a wall surface of the accommodating chamber 102 opposite to the open opening 104, for example, when the open opening 104 of the accommodating chamber 102 faces upward of the body 10, the fixing frame 21 is fixed to a bottom wall of the accommodating chamber 102, and when the open opening 104 of the accommodating chamber 102 faces downward of the body 10, the fixing frame 21 is fixed to a top wall of the accommodating chamber 102. The fixing frame 21 is used for fixing other components in the driving assembly 20 in the accommodating cavity 102, and increases the stability of the connection of the functional assembly 30 and the body 10. One end of the first link group 22 is rotatably connected with one end of the fixed frame 21, one end of the second link group 23 is rotatably connected with the other end of the fixed frame 21, and the other end of the first link group 22 and the other end of the second link group 23 are both rotatably connected with the functional component 30. The power assembly 24 is disposed in the accommodating cavity 102, and the power assembly 24 is connected to the second linkage 23 to drive the second linkage 23 to rotate relative to the fixed frame 21. Thereby realizing that the functional component 30 is driven to move by driving the second linkage 23 to rotate.

Alternatively, as shown in fig. 1, the power assembly 24 includes a motor 242, and one end of the second linkage 23 near the fixed frame 21 is connected to an output shaft of the motor 242. The motor 242 can drive the second linkage 23 to move and further drive the functional component 30 to move, and the motor 242 provides power for the functional component 30 to move between the first position and the second position. The motor 242 may be a steering engine. But the application is not limited thereto.

Optionally, as shown in fig. 1 and fig. 2, the unmanned aerial vehicle 1 further includes a fixing base 40, the fixing base 40 is connected with the other end of the first linkage 22 and the other end of the second linkage 23 in a rotating manner, and the functional component 30 is connected with the fixing base 40. Therefore, the power assembly 24 drives the second linkage 23 to rotate, so as to drive the fixing seat 40 to move, further drive the functional assembly 30 to move, and realize the movement of the functional assembly 30 between the first position and the second position.

Optionally, as shown in fig. 1, the unmanned aerial vehicle 1 further includes a shock absorbing member 50, and the shock absorbing member 50 is disposed between the fixing base 40 and the functional component 30. Therefore, when the unmanned aerial vehicle 1 flies, the possibility that the functional component 30 is affected by vibration to work accuracy is reduced, for example, if the functional component 30 is used for shooting operation, the shock absorption piece 50 can play a role in buffering when the unmanned aerial vehicle 1 flies, so that the picture of the functional component 30 is more stable when shooting.

Optionally, as shown in fig. 1 and fig. 2, the first link group 22 includes two spaced first links 222, one end of each first link 222 is rotatably connected to the fixing frame 21, and the other end of each first link 222 is rotatably connected to the fixing base 40, so that the smoothness of the functional assembly 30 along with the flight of the unmanned aerial vehicle 1 can be increased, and the possibility that the functional assembly 30 is affected by wind force to generate shaking is reduced.

Optionally, as shown in fig. 1 and fig. 2, the second linkage 23 includes two spaced second connecting rods 232, one end of each second connecting rod 232 is rotatably connected to the fixing frame 21, and the other end of each second connecting rod 232 is rotatably connected to the fixing base 40, so that the stability of the functional component 30 along with the flight of the unmanned aerial vehicle 1 can be increased, and the possibility that the functional component 30 is affected by wind force to generate shaking is reduced.

Optionally, the plane where the fixing seat 40 is located is parallel to the plane where the fixing frame 21 is located, so that the structure is relatively simple, and the functional component 30 is convenient to drive to move, thereby enabling the functional component 30 to be closer to the wall surface, opposite to the opening 104, of the accommodating cavity 102 when the functional component 30 is in the first position, enabling the functional component 30 to be better accommodated in the accommodating cavity 102 when the functional component is in the first position, further reducing the part, outside the accommodating cavity 102, of the functional component 30, thereby reducing the wind resistance of the unmanned aerial vehicle 1, and enabling the flight of the unmanned aerial vehicle 1 to be more stable. In addition, when unmanned aerial vehicle 1 awaits the opportune moment, also make things convenient for unmanned aerial vehicle 1's transportation and accomodating more, protect function component 30 simultaneously, reduce function component 30 and receive the possibility of damage.

According to some embodiments of the present invention, the open opening 104 is located on the lower surface of the fuselage 10. Therefore, the functional component 30 can be reduced to interfere with other parts on the unmanned aerial vehicle 1 or block the visual field when working at the second position, and the working reliability of the functional component 30 is ensured.

According to some embodiments of the present invention, as shown in fig. 1 and 2, the functional assembly 30 includes: a pan and tilt head 302 and a camera 304.

Specifically, the pan/tilt head 302 is coupled to the drive assembly 20, and the camera 304 is rotatably coupled to the pan/tilt head 302. Cloud platform 302 has stably, compact structure, rotates the advantage nimble and can the multi-angle adjustment camera 304 shooting field of vision, can make unmanned aerial vehicle 1 can be used for aerial photography etc. from this.

Further, when cloud platform 302 is in the first position, camera 304 is in holding chamber 102, thereby can further reduce the windage when unmanned aerial vehicle 1 flies, can better protect camera 304 simultaneously, and when cloud platform 302 is in the second position, camera 304 is located and holds chamber 102 outward, thereby can reduce the possibility that fuselage 10 is to camera 304 shooting field of vision sheltering from.

Optionally, as shown in fig. 3, the drone 1 further comprises: fixed wing 60, first power mechanism 70, tail wing 80, second power mechanism 90, battery, flight control unit, location module and communication module. The flight control unit comprises a mainboard and an Inertial Measurement Unit (IMU) arranged above the mainboard, the positioning module is electrically connected with the mainboard (can be in communication and/or electrical connection), and the communication module comprises a data transmission module and an antenna electrically connected with the data transmission module.

Optionally, the fuselage 10 is arranged symmetrically and has a symmetry plane, and the axis of the fuselage 10 and the center of gravity of the unmanned aerial vehicle 1 are both located on the symmetry plane of the fuselage 10. This makes it possible to make the unmanned aerial vehicle 1 more stable in flight.

Optionally, the unmanned aerial vehicle 1 further comprises an electrical installation part, and the electrical installation part is arranged on the fuselage 10. Electronic components such as batteries, functional components 30, flight control units, positioning modules, and communication modules may be provided within the electrical mounting portion.

Optionally, as shown in fig. 3, the number of the fixed wings 60 is two, and two fixed wing 60 branches are symmetrically arranged on two sides of the symmetric plane of the fuselage 10, so that the flight of the unmanned aerial vehicle 1 can be more stable. After the unmanned aerial vehicle 1 reaches a certain level of flying speed, the fixed wing 60 provides sufficient lift for the aircraft, so that the unmanned aerial vehicle 1 can fly normally.

Alternatively, as shown in fig. 3, the stationary wing 60 includes a first wing section 61 and a second wing section 62 connected to each other. The present application is not limited thereto, and the stationary wing 60 may further include a third wing section, a fourth wing section, etc., and the connection between these wing sections may be the same as the connection of the first wing section 61 and the second wing section 62.

Optionally, as shown in fig. 3, the fixed wing 60 further includes a wingtip winglet 63, the wingtip winglet 63 is connected to an end of the second wing section 62, which is far away from the first wing section 61, and the wingtip winglet 63 and the second wing section 62 form an included angle, so that the possibility of the air on the upper surface and the lower surface of the second wing section 62 generating the bypass flow can be blocked, and the damage of the bypass flow to the lift force of the drone 1 can be reduced. It should be noted that the angle formed by the winglet 63 and the second wing section 62 can be designed according to practical needs, and the present application is not limited thereto.

Optionally, as shown in fig. 3, an aileron 64 is further disposed at an end of the second wing section 62 close to the tail direction of the fuselage 10, and the aileron 64 can be turned up and down relative to the fuselage 10, so that the flight attitude of the drone 1 can be controlled. The second wing section 62 includes opposing upper and lower surfaces, the flap 64 includes opposing upper and lower surfaces, the upper surface of the flap 64 is substantially flush with the upper surface of the second wing section 62, and the lower surface of the flap 64 is substantially flush with the lower surface of the second wing section 62.

Optionally, a steering engine is arranged in the first wing segment 61, so that the angles of the ailerons 64 and the second wing segment 62 can be controlled, and the flight direction of the unmanned aerial vehicle 1 can be controlled.

Alternatively, as shown in fig. 3, the first power mechanism 70 is disposed on the first wing section 61, so as to provide the vertical take-off and landing flight power for the unmanned aerial vehicle 1, and enable the unmanned aerial vehicle 1 to vertically take off and land.

Further, as shown in fig. 3, the first power mechanism 70 includes a wing arm 71, a first power unit 72, and a first propeller 73, specifically, the wing arm 71 is disposed on the first wing section 61, the first power unit 72 is disposed on the wing arm 71, and the first propeller 73 is disposed on the first power unit 72.

Further, as shown in fig. 3, the number of the wing arms 71 is two, two wing arms 71 are respectively symmetrically arranged on both sides of the fuselage 10, and the axial direction of the two wing arms 71 is substantially parallel to the axis of the fuselage 10.

Further, as shown in fig. 3, the number of the first power units 72 is four, and the first power units are respectively arranged at two ends of the two wing arms 71, so that the unmanned aerial vehicle 1 can fly more stably.

Further, as shown in fig. 3, the second power mechanism 90 includes a base 91, a second power unit 92, and a second propeller 93, specifically, the second power unit 92 is disposed on the base 91, and the second propeller 93 is disposed on the second power unit 92. Preferably, the base 91 is in the form of a shell of a spar shape, thereby facilitating mating with the fuselage 10.

Alternatively, as shown in fig. 3, the tail wing 80 includes two wing plates 81 arranged in an inverted V shape, and the two wing plates 81 are pivotally connected to each other, i.e., the two wing plates 81 can be folded with each other. When unmanned aerial vehicle 1 was out of work, can dismantle fin 80, practice thrift from this and accomodate the shared space of unmanned aerial vehicle 1.

Alternatively, as shown in fig. 3, the tail wing 80 is fixed to one end of the wing arm 71 near the tail of the fuselage 10 by a tail stay 82 and a tail stay mount 83.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", and the like, indicate the orientation or positional relationship indicated based on the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention. Furthermore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In the description herein, references to the description of the term "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 invention. In this specification, the schematic representations of the terms used above 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.

While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims (10)

1. An unmanned aerial vehicle, comprising:

the device comprises a machine body, wherein an accommodating cavity is arranged on the machine body and is provided with an open hole positioned on the machine body;

the driving assembly is arranged in the accommodating cavity;

the functional component is connected with the driving component, the driving component drives the functional component to move between a first position and a second position, at least part of the functional component is located in the accommodating cavity at the first position, and the functional component is located outside the accommodating cavity at the second position.

2. The drone of claim 1, wherein the drive assembly includes:

the fixing frame is fixed on the wall surface of the accommodating cavity opposite to the opening;

one end of the first connecting rod group is rotatably connected with one end of the fixed frame;

one end of the second connecting rod assembly is rotatably connected with the other end of the fixing frame, and the other end of the first connecting rod assembly and the other end of the second connecting rod assembly are rotatably connected with the functional component;

the power assembly is arranged in the accommodating cavity and connected with the second connecting rod group to drive the second connecting rod group to rotate relative to the fixing frame.

3. The unmanned aerial vehicle of claim 2, wherein the power assembly comprises a motor, and an end of the second linkage proximate to the fixed mount is coupled to an output shaft of the motor.

4. The drone of claim 2, further comprising:

the fixing seat is connected with the other end of the first connecting rod group and the other end of the second connecting rod group in a rotating mode, and the functional component is connected with the fixing seat.

5. The drone of claim 4, further comprising:

and the damping piece is arranged between the fixed seat and the functional component.

6. The unmanned aerial vehicle of claim 4, wherein the first linkage set comprises two spaced first linkages, one end of each first linkage is rotatably connected to the mount, and the other end of each first linkage is rotatably connected to the mount.

7. The unmanned aerial vehicle of claim 4, wherein the second linkage comprises two spaced apart second links, one end of each second link is rotatably connected to the mount, and the other end of each second link is rotatably connected to the mount.

8. The unmanned aerial vehicle of claim 4, wherein the plane of the fixing seat is parallel to the plane of the fixing frame.

9. A drone according to any one of claims 1 to 8, wherein the open opening is located on a lower surface of the fuselage.

10. A drone according to any one of claims 1 to 8, characterised in that the functional components comprise:

the holder is connected with the driving assembly;

the camera is connected with the holder in a rotating mode.

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