CN112543734A

CN112543734A - Unmanned aerial vehicle and operation method thereof, imaging device and operation method thereof

Info

Publication number: CN112543734A
Application number: CN202080004344.3A
Authority: CN
Inventors: 陈思聪
Original assignee: SZ DJI Technology Co Ltd
Current assignee: SZ DJI Technology Co Ltd
Priority date: 2020-03-31
Filing date: 2020-03-31
Publication date: 2021-03-23
Also published as: WO2021195966A1

Abstract

An unmanned aerial vehicle comprising an aircraft component; a horn (1001), at least one aircraft component being connected to the horn (1001); a fuselage (1002), the horn (1001) being rotatable relative to the fuselage (1002) to receive at least one aircraft component in the fuselage (1002). And an imaging apparatus comprising a photographing unit (1003); the support structure is connected with the flying suit, and the flying suit is used for realizing the lifting of the imaging device; the imaging device comprises an imaging device body, a shooting unit (1003) is connected to the body, and a supporting structure can rotate relative to the body so that the flying suit can be unfolded outside the body. This aircraft part and image device accomodate it completely in the aircraft fuselage when need not to use the aircraft part, or will fly the suit and expand outside the image device main part when needs lift image device for mechanism simple structure, the operation is convenient, has expanded the use scene of device, can apply to it and hand-held shooting or take photo by plane, has richened user experience.

Description

Unmanned aerial vehicle and operation method thereof, imaging device and operation method thereof

Technical Field

The invention relates to the field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle and an operation method thereof, and an imaging device and an operation method thereof.

Background

With the development of science and technology, aerial photography technology is gradually developing, wherein unmanned aerial vehicle aerial photography technology is gradually gaining favor of photographers due to its lower cost and higher safety than manned aerial photography. The unmanned aerial vehicle aerial photography work usually adopts shooting devices such as an aerial vehicle carrying a camera and a camera to shoot. Unmanned aerial vehicles generally include: the fuselage, install in horn on the fuselage and install the power component on the horn. However, the horn of this kind of many rotor unmanned aerial vehicle that has now is the snap-on the centre frame to the volume that has led to many rotor unmanned aerial vehicle's occupation is bigger, is unfavorable for storage or transportation.

Disclosure of Invention

The present invention is directed to solving at least one of the problems of the prior art.

To achieve the above object, an aspect of the present invention provides an unmanned aerial vehicle including an aircraft component; a horn to which at least one of the aircraft components is connected; a fuselage, the horn being rotatable relative to the fuselage to receive at least one of the aircraft components in the fuselage.

An aspect of a second aspect of the present invention provides an imaging apparatus including a photographing unit; the supporting structure is connected with a flying suit, and the flying suit is used for realizing the lifting of the imaging device; the shooting unit is connected to the main body, and the supporting structure can rotate relative to the main body so that the flying suit is unfolded outside the main body.

The technical scheme of the third aspect of the invention provides an operation method of an unmanned aerial vehicle, wherein the unmanned aerial vehicle comprises an aircraft part, a horn and a fuselage; the method comprises the following steps: switching the unmanned aerial vehicle to a first state, and controlling the arm to rotate relative to the fuselage so as to enable at least one aircraft component to be located outside the fuselage; and/or switching the unmanned aerial vehicle to a second state, and controlling the arm to rotate relative to the fuselage so as to enable at least one aircraft component to be located in the fuselage.

An aspect of the fourth aspect of the present invention provides a method of operating an imaging apparatus including a photographing unit, a support structure, a flying suit, and an imaging apparatus body, the photographing unit being connected to the body, the method including: switching the imaging device to a first state, and controlling the support structure to rotate relative to the main body so that at least one flying suit is positioned outside the main body; and/or switching the imaging device to a second state, and controlling the support structure to rotate relative to the main body so that at least one flying suit is positioned in the main body.

An aspect of the fifth aspect of the invention provides a computer-readable storage medium storing a computer program that, when executed by a processor, causes the processor to implement a method of operating an unmanned aerial vehicle.

An aspect of a sixth aspect of the present invention provides a computer-readable storage medium storing a computer program which, when executed by a processor, causes the processor to implement an operation method of an imaging apparatus.

Compared with the prior art, the invention has the following beneficial technical effects: according to the unmanned aerial vehicle, the aircraft component of the unmanned aerial vehicle is rapidly stored relative to the fuselage through the arrangement of the horn capable of rotating relative to the fuselage, or the flying suit on the imaging equipment is unfolded relative to the main body through the arrangement of the supporting structure capable of rotating relative to the main body; and the aircraft part is completely accommodated in the machine body during handheld shooting, so that the possibility of accidental injury of the aircraft part to a user is reduced, the occurrence rate of collision and damage accidents of the aircraft part is also reduced, the energy is saved, and the service life of a battery of the device is prolonged.

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

Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle in a deployed state according to an embodiment of the present invention;

FIG. 2 is a top view of an unmanned aerial vehicle according to an embodiment of the present invention in a deployed state;

FIG. 3 is a front view of an unmanned aerial vehicle according to an embodiment of the present invention in a deployed state;

fig. 4 is a schematic structural diagram of a storage state of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 5 is a plan view of a storage state of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 6 is a front view of a stowed state of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 7 is a schematic structural diagram of a deployed state of a horn and an aircraft component according to an embodiment of the present invention.

Fig. 8 is a top view of a deployed state of an arm and an aircraft component according to an embodiment of the invention.

FIG. 9 is a schematic structural diagram of a stored state of a horn and an aircraft component according to an embodiment of the present invention;

fig. 10 is a plan view of a stored state of an arm and an aircraft component according to an embodiment of the present invention.

Fig. 11 is a front view of a stowed arm and aircraft component according to an embodiment of the invention.

Wherein, the corresponding relationship between the reference numbers and the component names in fig. 1 to 11 is:

100 unmanned vehicles, 1001 horn, 1 propeller, 11 blades, 12 rotating shafts, 2 protective parts, 21 connecting parts, 211 containing parts, 22 protective covers, 221 protective supports, 3 horns, 31 main arms, 32 supporting arms, 33 rotating parts, 34 folding parts, 1002 fuselage, 1003 shooting unit and 1004 operating unit.

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 accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.

In the description of the present invention, it is to be understood that the terms "first", "second" and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implying any number of technical features indicated. Thus, features defined as "first", "second", may explicitly or implicitly include one or more of the described features. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable 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 specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

The following disclosure provides many different embodiments or examples for implementing different features of the invention. To simplify the disclosure of the present invention, the components and arrangements of specific examples are described below. Of course, they are merely examples and are not intended to limit the present invention. Furthermore, the present invention 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, the present invention provides examples of various specific processes and materials, but one of ordinary skill in the art may recognize applications of other processes and/or uses of other materials.

Example one

An unmanned aerial vehicle 100 according to some embodiments of the present invention is described below with reference to fig. 1 to 11.

As shown in fig. 1 to 11, according to some embodiments of the present invention, there is provided an unmanned aerial vehicle 100, the unmanned aerial vehicle 100 including: an aircraft component; a horn 1001 to which at least one of the aircraft components is attached; a fuselage 1002, said horn 1001 being rotatable relative to said fuselage 1002 to receive at least one said aircraft component in said fuselage 1002.

According to the unmanned aerial vehicle provided by the embodiment of the first aspect of the invention, the horn 1001 capable of rotating relative to the body 1002 is arranged, so that the aircraft component of the unmanned aerial vehicle can be rapidly stored relative to the body 1002; aircraft part can be located outside the fuselage when taking photo by plane, and aircraft part can accomodate completely in fuselage 1002 when handheld shooting, and benefit from fuselage 1002 to the protection of aircraft part, and the aircraft part can not expose under the state of accomodating, has correspondingly reduced the possibility of aircraft part to user's unexpected injury, has also reduced the incidence of aircraft part damage accident that collides with, and is more energy-conserving simultaneously, has prolonged the battery life of device.

Wherein the fuselage 1002 is connected to one end of the horn 1001 and the aircraft component is connected to the other end of the horn 1001. Accordingly, in order to meet the balance requirement of the unmanned aerial vehicle, the aircraft components can be arranged at any position on the arm, or the arm is not needed, and the aircraft components are directly connected to the fuselage 1002 and rotate to be unfolded or stored.

It should be noted that at least one aircraft component is accommodated in the fuselage 1002, at this time, the function corresponding to the aircraft component that is usually accommodated cannot be used, and the aircraft component that is accommodated is also in a closed state; when certain functions are desired, the user may deploy the aircraft component, either manually or with automated control, to position the corresponding aircraft component outside fuselage 1002, thereby activating the aircraft component to use the function. By closing the aircraft components in the storage state, the battery endurance of the unmanned aerial vehicle can be effectively prolonged, because the aircraft components are often powered by a power supply carried by the unmanned aerial vehicle.

Simultaneously, can make horn 1001 still includes rotates the piece 33, is connected through rotating the piece 33 between horn 1001 and the fuselage 1002, the contained angle between each aircraft part of corresponding adjustment and the fuselage 1002, makes relative rotation in order to accomplish the adjustment of gesture or angle between aircraft part and the fuselage 1002, also can with all lie in the fuselage 1002 outside aircraft parts and fuselage 1002 between relative rotation accomodate in the fuselage 1002 when switching over to accomodating the state, and need not to dismantle aircraft parts and can realize simple and convenient carrying and depositing. The present embodiment is not particularly limited with respect to the angle between the aircraft component and the fuselage 1002 and the adjustable range of the angle. Alternatively, the horn 1001 may be attached to the side of the body 1002 at the intersection of the front and rear, the horn 1001 may be attached to the side of the body 1002 at the midline, and the horn 1001 may be attached to at least one of the interiors of the body 1002. Preferably, the plurality of arms 1001 may be arranged uniformly in the axial direction of the body 1002. Particularly, when all the arms 1001 are connected to the boundary between the lateral side and the front and rear sides of the body 1002 as shown in fig. 1 to 6, the distance between the arms 1001 is the largest, and the air flow is guided well.

In a specific embodiment, the number of the rotating members 33 may be at least two, and the rotating members 33 are divided in the axial direction of the body 1002, and the at least two rotating members 33 are disposed opposite to the body 1002. Illustratively, an even number of rotating members 33 are disposed on opposite sides of the body 1002, the rotating members 33 rotate in two directions when the arms 1001 on both sides of the body 1002 are unfolded, and the two rotating members 33 on the same side of the body 1002 rotate in the same direction, so as to facilitate user operation. Or the three rotating components 33 can be uniformly distributed in the circumferential direction, that is, the included angle between adjacent rotating components 33 is 120 degrees from the central point of the machine body 1002, so as to facilitate the identification and independent operation of a user; in the case of including four rotating members 33, the four rotating members 33 may be symmetrically disposed, and an included angle between two adjacent rotating members 33 is 90 °; for the case of including five rotating members 33, six rotating members 33, and so on, the description thereof will be omitted.

In a particular embodiment, the aircraft component includes at least one of a power assembly, an illuminator, a sensor, a lidar, and a camera unit. Particularly, the quick-release structure is arranged between the aircraft part and the fuselage 1002, the aircraft parts with different functions can be conveniently replaced, so that different functions can be realized on the same fuselage 1002, and the universality of the unmanned aircraft is improved. For example, when the shooting unit is not needed, the body 1002 is separated from the shooting unit by a quick-release piece arranged on the body 1002 or the shooting unit so as to reduce the weight of the unmanned aerial vehicle; it is also possible to further install a sensor, such as a distance sensor, to be used at a position where the photographing unit is detached by a quick-release member, thereby turning on the distance detection function of the unmanned aerial vehicle.

Fix on fuselage 1002 with current aircraft part, can't dismantle with adjustment unmanned vehicles gesture, adjustment accessory angle or dismantle the accessory and compare, the quick replacement of aircraft part has been realized to this embodiment, and then the switching of various additional functions when realizing using unmanned vehicles 100 has promoted user operation's comfort level, makes unmanned vehicles 100's extension more simple and convenient, and the user is changeed the hands on to unmanned vehicles 100's manipulation.

In one specific embodiment, horn 1001 includes a main arm 31 and a boom 32, wherein boom 32 is coupled to main arm 31, wherein fuselage 1002 is coupled to main arm 31, and wherein the aircraft component is coupled to boom 32. Through this mode, can adapt to the adaptation demand of fuselage collecting space different shapes, provide the scheme for unmanned vehicles's miniaturization. In particular, it is also possible to connect the aircraft part to the free end of the arm 32 in order to balance the overall stress on the arm and thus guarantee the service life of the unmanned aircraft. Of course, the aircraft components may be attached to any position of the horn as desired to accomplish deployment and stowing of the aircraft components relative to the fuselage 1002 by rotation of the horn 1001 relative to the fuselage 1002. The main arm 31 may include one or more arms, and the arm 32 may include one or more arms 1001 to form various shapes.

In a specific embodiment, the supporting arm 32 can be perpendicular to the main arm 31, so that the leveling requirement of the unmanned aerial vehicle can be met under the condition that the stress of the arm is uniform. In a specific embodiment, the arm 32 may be connected to the middle of the main arm 31, so that the free end of the main arm 31 may be further installed with other structural members, and the moment balance of the main arm and the rigidity of the whole arm are enhanced. Arm 32 may be connected to other positions of main arm 31, such as the other end of main arm 31 connected to main body 1002 to form a substantially "L" shaped arm, or main arm 31 and arm 32 may be configured in various shapes, such as straight, curved, wavy, zigzag, etc., and the embodiment is not limited in particular.

In a specific embodiment, in order to adjust the angle between the arm 32 and the main arm 31, the arm 1001 further includes a folding member 34, and the arm 32 is connected to the main arm 31 through the folding member 34. The arm 32 is rotatable about the folding member 34 to be substantially parallel to the main arm 31 in a first state and to be angled with respect to the main arm 31 in a second state. Through the arrangement, the supporting arm 32 can be further close to the main arm 31 along the circumferential direction during storage, and finally the minimum included angle between the supporting arm 32 and the main arm 31 is ensured, even the supporting arm 32 and the main arm 31 are partially or completely overlapped, so that the space occupied by the horn 1001 is correspondingly reduced in a scene that the unmanned aerial vehicle needs to be used in a storage state. And when the arm 1001 needs to be unfolded, the arm 32 can rotate around the folding piece 34 to form an included angle with the main arm 31.

In particular, the arm 32 can be partially or completely covered by the main arm 31 in the first state. As mentioned above, the arm 32 may be substantially parallel to the main arm 31 in the first state, and thus, the two may be partially or completely overlapped; in a case where the arm 32 and the main arm 31 are located in different planes, that is, the arm 32 and the main arm 31 are relatively rotated in different planes by the folding member disposed therebetween, and finally partially or completely overlapped in a direction perpendicular to the rotation plane when the relative distance between the ends is shortest, the arm 32 is partially or completely covered by the main arm 31; alternatively, the arm 32 may be located in the same rotation plane as the main arm 31, and the arm 32 may be substantially parallel to the main arm 31 in the first state, so that the arm 32 is partially or completely covered by the main arm 31 due to the space limitation to avoid interference between the arm 32 and the main arm 31. In this case, the cross-section of the main arm 31 may comprise a cavity, for example in the form of

An "L" or "C" shape, the arm 32 being received in the cavity in a first state. Of course, the main arm 31 may be partially or completely covered by the arm 32, and the embodiment is not particularly limited.

In a specific embodiment, in order to achieve the relative fixation between the boom 32 and the main arm 31, for example, when the unmanned aerial vehicle takes an aerial photograph, the boom is in a deployed state (as shown in fig. 1-3), or when the unmanned aerial vehicle takes a photograph in a handheld manner or is not used and then in a stowed state (as shown in fig. 4-6), a limiting member may be provided for the boom 1001 to lock the relative position of the boom 32 and the main arm 31. Through this setting, can prevent that the relative position of support arm 32 for main arm 31 from taking place unexpected change, the corresponding possibility that has reduced unmanned vehicles's crash accident or aircraft part to user's unexpected injury has also reduced the incidence of aircraft part damage accident of colliding with.

In a particular embodiment, the unmanned aerial vehicle further comprises a protective component 2, the protective component 2 being configured to protect the aircraft component. For example, the protective component 2 may cover, wrap the aircraft component. In particular, the protective component 2 may protect aircraft components when they are outside the fuselage 1002 while preventing certain types of aircraft components, such as propellers, from causing damage to living beings or objects in the vicinity thereof during operation.

In a specific embodiment, the protection member 2 includes a protection cover 22, and the protection cover 22 is connected to the horn 1001. The protective cover 22 can reduce the weight of the body better than other types of protective members 2. At least a part of the protection cover 22 is movable toward the arm 1001 side to be retracted from the peripheral side of the arm 1001; and/or at least a part of protective cover 22 can move away from horn 1001 to protrude from the peripheral side of horn 1001. By providing the protective cover 22, the application surface and versatility of the protective cover 22 can be further enhanced, and the protective cover 22 can be used in different forms in different usage scenarios. Illustratively, in the first state, the protective cover 22 is retracted until the protective cover 22 at least partially fits the horn 1001; in the second state, protective cover 22 is deployed to partially or fully cover the aircraft component. That is, in one case, the protection cover 22 may be folded, stacked, or contracted to be in a state where the protection cover 22 is at least partially attached to the horn 1001, for example, the protection cover 22 is stacked as shown in fig. 3, and finally, when abutting against the horn 1001, the protection cover 22 is overlapped, and at this time, one side of the protection cover 22 is attached to the horn 1001, and the other part is not attached to the horn 1001; due to the limitation of the space structure, in order to further reduce the space occupied by the protective cover 22 when retracted and avoid interference between the protective cover 22 and the horn 1001, the protective cover 22 may be partially or completely covered by the horn 1001, for example, the protective cover 22 is partially covered by the horn 1001 as shown in fig. 3. In yet another instance, the protective covering 22 can be deployed to partially or fully cover the aircraft component. For example, the protective covering 22 may partially cover the aircraft component as shown in FIGS. 6-7, or may completely cover the aircraft component; in the deployed state, protective cover 22 may be held at least partially in contact with horn 1001 as shown in fig. 6 to 7, or may not be in contact with horn 1001. In particular, the protective cover 22 comprises protective brackets 221, the protective brackets 221 being foldable or stackable on each other. For example, as shown in fig. 1-2, the protection cover 22 includes a plurality of the protection brackets 221, and the protection brackets 221 can move relative to each other around the receiving member 211 to achieve mutual stacking or unfolding, so as to achieve the retracted state and the unfolded state of the protection cover 22; of course, it is also possible to make the protective bracket 221 foldable or unfoldable, for example fan-shaped, around the receptacle 211. The receiving member 211 may be disposed at an end of the arm 1001 as shown in fig. 1 to 3, or may be disposed at a middle portion of the arm 1001 as long as the protection brackets 221 can be folded or stacked; in particular, when the receptacle 211 is disposed in the middle of the horn 1001, the protection bracket 221 can rotate around the receptacle 211 until the outermost protection bracket 221 partially abuts against the horn 1001, thereby completely accommodating the aircraft components mounted in the middle of the horn 1001 in the protective cover 22. Even, the protective cover 22 may not include the receptacle 211, for example, the protective brackets 221 parallel to each other may be folded or stacked on each other by a movement direction forming an angle with the extension direction of the horn 1001, and particularly, the protective brackets 221 may be stacked or unfolded on each other by an external push-pull force in a movement direction perpendicular to the extension direction of the horn 1001 to expose the aircraft component when stacked on each other and surround the aircraft component when unfolded. The installation position and installation/non-installation of the receiving member 211 are not limited herein.

Further, it is also possible to make the protective cover 22 include a locking member by which a plurality of the protective brackets 221 are held fixed relative to each other. The locking members are particularly suitable for the stacked configuration of the protective supports 221, as shown in fig. 1-2, and are configured to keep the protective supports 221 fixed relative to each other in the extended state of the protective cover 22, so as to prevent the adjacent protective supports 221 from being separated from each other, thereby ensuring the integrity of the protective cover 22 in the extended state. In particular, the protection bracket 221 further includes a limiting portion, which limits a maximum distance between adjacent protection brackets 221, so that separation between adjacent protection brackets 221 can be avoided, thereby ensuring integrity of the protection cover 22 in the unfolded state. In the first state, the protective bracket 221 is partially or completely covered by the horn 1001. And the protection brackets 221 may have a fan shape or a square shape to facilitate folding or stacking each other. To achieve a shade for aircraft components, the protective component can be one or more of a sector, a cylinder, an elliptic cylinder or an approximately rectangular parallelepiped.

In a specific embodiment, the number of the protection members 2 is the same as that of the horn 1001. By providing the same number of protective members 2 and horn 1001, all aircraft components connected to horn 1001 can be protected. In particular, it is possible to include several protective hoods 22 on a single horn 1001, for example an even number of protective hoods 22 arranged symmetrically along the central axis of the horn 1001, so that all-round protection of aircraft components at different installation locations is achieved.

In a specific embodiment, the fuselage is in the form of one or more of a cuboid, a cylinder, a sphere. In the first state, all the aircraft components are located in the fuselage 1002, so that when the unmanned aerial vehicle 100 needs to be stored or transported, the occupied volume of the unmanned aerial vehicle 100 can be reduced, the storage or the transportation of the unmanned aerial vehicle is convenient, and the unmanned aerial vehicle is simple and attractive. In another embodiment, the aircraft component mounted on fuselage 1002 may be located outside said fuselage 1002 in the second state. By locating the aircraft components outside of the fuselage 1002 when they are needed and within the fuselage 1002 when they are not needed, the flight resistance can be reduced while further avoiding accidental damage to the aircraft components when the handheld unmanned aerial vehicle is filming. Optionally, the aircraft component comprises at least one of a power assembly, a lighting, a sensor, a lidar, a camera unit. For example, when a user desires to take an aerial photograph, the power assembly and camera unit may be located outside of fuselage 1002, while other aircraft components are located within fuselage 1002 to reduce wind resistance; when the user takes a photo at night, the lighting elements, power assembly and camera unit may be located outside of the fuselage 1002 while other aircraft components are located within the fuselage 1002 to increase the brightness of the night imagery. When fixed-point ranging is needed, the fuselage 1002 can be fixed at a certain preset position, the laser radar or other types of ranging sensors are arranged outside the fuselage 1002, and other aircraft components are arranged in the fuselage 1002, so that interference caused by other aircraft components on distance measurement is reduced, and accidental damage caused by other aircraft components can be further avoided.

Preferably, the unmanned aerial vehicle 100 may further include one or more shooting units 1003, and since the shooting target during aerial shooting is generally located in front of, behind or below the unmanned aerial vehicle 100, the shooting unit 1003 may be disposed on the front side, the rear side or the bottom of the unmanned aerial vehicle 100. In order to further avoid the transmission of vibrations on the fuselage 1002 of the unmanned aerial vehicle 100 to the shooting unit 1003 and to enhance the shooting range in which the shooting unit 1003 is implemented, the shooting unit 1003 may further include one or more holders, which are attached to the fuselage 1002. In addition, other holders can be installed at the bottom or the top of the fuselage 1002, so that different devices can be installed on the holders in different application scenarios to expand the functions of the unmanned aerial vehicle 100. For example, when the unmanned aerial vehicle 100 is used for aerial photography, a shooting unit may be mounted on the pan/tilt head for shooting, recording, and the like. For example, when the unmanned aerial vehicle 100 is used for remote sensing, a remote sensing device such as an infrared sensor or a night vision imager may be mounted on the pan/tilt head. For another example, when the unmanned aerial vehicle 100 is used for agricultural production, a sowing machine may be mounted on the pan/tilt head to sow seeds, fertilize fertilizer, spray pesticides, or the like. For example, when the unmanned aerial vehicle 100 is used to assist the construction of a suspension bridge, one end of the pilot cable may be fixed to the cradle head, and the pilot cable is pulled by the unmanned aerial vehicle so as to erect a linear temporary construction convenience road parallel to the main cable under the main cable of the suspension bridge, thereby facilitating the construction of bridge constructors.

In a specific embodiment, the unmanned aerial vehicle further comprises an operation unit 1004. The operating unit 1004 includes at least one of a thumb wheel, a stick, a dial, a rocker, and a key, the number of the operating unit 1004 may be one or more according to the application scenario and the use requirement of the unmanned aerial vehicle 100, and the specific structure of the operating unit 1004 may be designed according to the specific number and type of the aircraft components, generally, the operating unit 1004 may include a plurality of operating units 1004, for example, the number of the operating units 1004 is two, three, or four, for example, the operating unit 1004 in fig. 6 is composed of a key and a stick. The operation unit 1004 may include a composite function key, which may include several keys, and the composite function key may enable switching of functions in a first state and/or a second state. The functions comprise one or more of photographing, video recording, aircraft state switching, focal length adjustment and exposure adjustment. For example, the shift lever in fig. 6 may be divided into three stages, where the first stage corresponds to the power being turned off, the second stage corresponds to the first state, and the third stage corresponds to the second state; that is, in first gear unmanned aerial vehicle 100 is not powered and all of the aircraft components are received in fuselage 1002, in second gear unmanned aerial vehicle 100 is powered and all of the aircraft components are received in fuselage 1002, and in third gear unmanned aerial vehicle 100 is powered and at least one of the aircraft components is located outside of fuselage 1002. For example, the composite function key in fig. 6 may include only one key, and the composite function key corresponds to several functions such as focus adjustment, exposure adjustment, and shutter speed switching (for example, different functions are realized by long pressing, short pressing, and several clicks) in the first state, and corresponds to several functions such as photographing, recording, and stopping photographing in the second state, so as to realize the switching of the functions in the first state and/or the second state. It is emphasized that the corresponding functions of the multi-function key in the first state and the second state may be identical, partially identical or completely different. Further, as shown in fig. 8, the complex function keys do not protrude from the surface of the fuselage 1002 to reduce the storage space and the flight wind resistance of the unmanned aerial vehicle 100.

As described above, the functions corresponding to the composite function key may further include switching of an aircraft state, and when the aircraft state switching function is triggered, the aircraft switches between a first state and a second state, where at least one aircraft component is located outside the fuselage in the first state, and the aircraft component is housed in the fuselage in the second state.

In a specific embodiment, the horn 1001 can be housed in the fuselage 1002, thereby further reducing the housing space of the unmanned aerial vehicle 100. In particular, when the horn 1001 is received in the fuselage 1002, the outer surface of the horn 1001 is flush with the outer surface of the fuselage 1002, i.e., when a portion of the horn 1001 forms the outer surface of the aircraft 100 with the outer surface of the fuselage 1002, and the outer surface of the aircraft 100 extends continuously, avoiding excessive sag and faults, to maintain the integrity of the outer surface of the aircraft 100 when the horn 1001 is received.

Example two

According to some embodiments of the present invention, there is provided an image forming apparatus including: a shooting unit; the supporting structure is connected with a flying suit, and the flying suit is used for realizing the lifting of the imaging device; the shooting unit is connected to the main body, and the supporting structure can rotate relative to the main body so that the flying suit is unfolded outside the main body.

According to the imaging device provided by the embodiment of the second aspect of the invention, the supporting structure capable of rotating relative to the main body is arranged, so that the flying suit can be rapidly stored relative to the main body; the flight suit can be located outside the main part during the aerial photography, and the flight suit can be accomodate in the main part completely when handheld shooting, and benefit from the protection of main part to the flight suit, and the flight suit can not expose under accomodating the state, has correspondingly reduced the possibility of flight suit to the unexpected injury of user, has also reduced the incidence that the damage accident was collided with to the flight suit, and is more energy-conserving simultaneously, has prolonged the battery life of device.

Wherein the main body is connected to one end of the support structure and the flying suit is connected to the other end of the support structure. Accordingly, in order to satisfy the balance requirement of the imaging device, the flying suit can be correspondingly arranged at any position on the supporting structure, or the flying suit can be directly connected to the main body and automatically rotate to be unfolded or stored without the supporting structure.

It should be noted that at least one of the flight suits is stored in the main body, at this time, the corresponding function of the stored flight suit is not used, and the stored flight suit is also in a closed state; when some functions need to be used, the user can manually or automatically control the unfolding of the flight suit to enable the corresponding flight suit to be positioned outside the main body, so that the flight suit is opened to use the functions. Through closing the flight suit when being in the state of accomodating, can effectively prolong imaging device's battery duration because the flight suit often is by imaging device self carried's power supply.

Simultaneously, can make bearing structure still includes rotates piece 33, is connected through rotating piece 33 between bearing structure and the main part, and the contained angle between each flight suit and the main part of corresponding adjustment makes the relative rotation between flight suit and the main part in order to accomplish the adjustment of gesture or angle, also can with all be located the main part outside the flight suit and the main part between the relative rotation accomodate in the main part when switching over to accomodating the state, and need not to dismantle the flight suit and can realize simple and convenient carrying and depositing. As for the included angle between the flying suit and the main body and the adjustable range of the included angle, the embodiment is not particularly limited. Optionally, the support structure is connected to the body at a lateral and anterior-posterior junction, the support structure is connected to the body at a lateral midline, and the support structure is connected to at least one of the body interiors. Preferably, a plurality of support structures can be arranged uniformly in the axial direction of the main body. Particularly, when all the supporting structures are connected to the junction of the side and the front and the rear of the main body as shown in fig. 1 to 6, the distance between the supporting structures is the largest, and the guiding effect on the air flow is better.

In a specific embodiment, the number of the rotating members 33 may be at least two, and the rotating members 33 are divided in the central axis direction of the main body, and the at least two rotating members 33 are disposed opposite to the main body. Illustratively, an even number of rotating members 33 are provided on opposite sides of the main body, the rotating members 33 rotate in two directions when the supporting structures on both sides of the main body are unfolded, and the two rotating members 33 on the same side of the main body rotate in the same direction, so as to facilitate the user's operation. Or the three rotating pieces 33 can be uniformly distributed in the circumferential direction, that is, the included angle between the adjacent rotating pieces 33 is 120 degrees from the central point of the main body, so that the identification and the independent operation of a user are facilitated; in the case of including four rotating members 33, the four rotating members 33 may be symmetrically disposed, and an included angle between two adjacent rotating members 33 is 90 °; for the case of including five rotating members 33, six rotating members 33, and so on, the description thereof will be omitted.

In a specific embodiment, the imaging device further comprises at least one of an illumination unit, a sensing unit, a lidar. Particularly, the quick-release structure is arranged between the flight suit and the main body, so that the flight suit with different functions can be conveniently replaced, different functions can be realized on the same main body, and the universality of the imaging device is improved. For example, when the illumination unit is not required to be used, the main body is separated from the illumination unit by a quick-release member provided on the main body or the illumination unit to reduce the weight of the image forming apparatus; it is also possible to further mount a sensor, such as a distance sensor, which is desired to be used, in a position where the image forming apparatus is detached by the quick-release member, thereby turning on the distance detection function of the image forming apparatus.

Fix in the imaging device main part with current accessory, can't dismantle with adjustment imaging device gesture, adjustment accessory angle or dismantle the accessory and compare, the quick replacement of accessory has been realized to this embodiment, and then the switching of various additional functions when realizing using imaging device has promoted user operation's comfort level, makes imaging device's extension more simple and convenient, and the user is changeed the hands to imaging device's manipulation.

In one embodiment, the support structure comprises a main arm 31 and an arm 32, the arm 32 being connected to the main arm 31, the body being connected to the main arm 31, and the flight suit being connected to the arm 32. Through this mode, can adapt to the adaptation demand of main part receiving space different shapes, provide the scheme for imaging device's miniaturization. In particular, the flying suit may be attached to the free end of the arm 32 to balance the overall stress on the support structure and thereby ensure the useful life of the imaging device. Of course, the flying suit may be attached to any position of the support structure as desired to accomplish the deployment and stowing of the flying suit relative to the main body by rotation of the support structure relative to the main body. The main arm 31 may comprise one or more arms and the arm 32 may comprise one or more arms to form support structures of different shapes.

In one embodiment, the arm 32 can be perpendicular to the main arm 31, which can meet the leveling requirements of the imaging device while ensuring that the supporting structure is uniformly stressed. In a specific embodiment, the arm 32 may be connected to the middle of the main arm 31, so that the free end of the main arm 31 may be further installed with other structural members, and the moment balance of the main arm and the rigidity of the whole supporting structure are enhanced. The arm 32 may be connected to other positions of the main arm 31, such as the other end of the main arm 31 connected to the main body to form a substantially "L" shaped support structure, or the main arm 31 and the arm 32 may be configured in various shapes, such as a straight line, an arc, a wave, a zigzag, etc., and the embodiment is not limited in particular.

In a specific embodiment, in order to adjust the angle between the arm 32 and the main arm 31, the support structure further includes a folding member 34, and the arm 32 is connected to the main arm 31 through the folding member 34. The arm 32 is rotatable about the folding member 34 to be substantially parallel to the main arm 31 in a first state and to be angled with respect to the main arm 31 in a second state. Through the arrangement, the support arm 32 can be further close to the main arm 31 along the circumferential direction during storage, and finally the minimum included angle between the support arm 32 and the main arm 31 is ensured, even the two partially or completely coincide with each other, so that the space occupied by the support structure is correspondingly reduced in a scene in which the imaging device is required to be used in a storage state. And enables the arm 32 to rotate about the folding member 34 to form an angle with the main arm 31 when it is desired to unfold the support structure.

In a specific embodiment, in order to achieve the relative fixation between the arm 32 and the main arm 31, for example, to ensure that the support structure is in the unfolded state (as shown in fig. 1-3) when the imaging device is taking an aerial photograph, or in the folded state (as shown in fig. 4-6) when the imaging device is taking a photograph in a handheld manner or not in use, a limiting member may be provided for the support structure to lock the relative position of the arm 32 and the main arm 31. Through this setting, can prevent that the relative position of support arm 32 for main arm 31 from taking place unexpected change, the corresponding possibility that has reduced image device's air crash accident or flight suit to user's unexpected injury has also reduced the incidence of flight suit damage accident of colliding with.

In a particular embodiment, the imaging device further comprises a protection component 2, the protection component 2 being used for protecting the flying suit. For example, the protective component 2 may cover, wrap the flight suit. In particular, the protection means 2 can protect the flight suit when it is outside the body, while preventing certain types of flight suit, such as propellers, from causing damage to living beings or objects in its vicinity during operation.

In a particular embodiment, the protective member 2 comprises a protective cover 22, the protective cover 22 being connected to the support structure. The protective cover 22 can reduce the weight of the main body better than other types of protective members 2. At least a portion of boot 22 is movable toward the support structure side to retract from the peripheral side of the support structure; and/or at least a portion of boot 22 is movable away from the support structure side to protrude from the support structure peripheral side. By providing the protective cover 22, the application surface and versatility of the protective cover 22 can be further enhanced, and the protective cover 22 can be used in different forms in different usage scenarios. Illustratively, in a first state, boot 22 is retracted until boot 22 is at least partially engaged with a support structure; in the second state, the protective cover 22 is deployed to partially or fully shroud the flight suit. That is, in one case, the protective cover 22 may be folded, stacked, or retracted to a state where at least a portion of the protective cover 22 is attached to the support structure, for example, the protective cover 22 is stacked as shown in fig. 3, and finally, when abutting against the support structure, the protective cover 22 is overlapped, and at this time, one side of the protective cover 22 is attached to the support structure, and the other portion is not attached to the support structure; due to space constraints, to further reduce the space occupied by shield 22 when retracted and to avoid interference between shield 22 and the support structure, shield 22 may be partially or completely covered by the support structure, for example, shield 22 is partially covered by the support structure as shown in fig. 3. In yet another aspect, the protective cover 22 can be deployed to partially or fully shroud the flight suit. For example, the protective cover 22 may partially or completely cover the flight suit as shown in FIGS. 6-7; in the deployed state, shield 22 may or may not remain at least partially engaged with the support structure as shown in FIGS. 6-7. In particular, the protective cover 22 comprises protective brackets 221, the protective brackets 221 being foldable or stackable on each other. For example, as shown in fig. 1-2, the protection cover 22 includes a plurality of the protection brackets 221, and the protection brackets 221 can move relative to each other around the receiving member 211 to achieve mutual stacking or unfolding, so as to achieve the retracted state and the unfolded state of the protection cover 22; of course, it is also possible to make the protective bracket 221 foldable or unfoldable, for example fan-shaped, around the receptacle 211. The receiving members 211 may be disposed at the ends of the supporting structure as shown in fig. 1 to 3, or may be disposed at the middle of the supporting structure, as long as the folding or stacking of the protection brackets 221 can be achieved; in particular, when the receptacle 211 is arranged in the middle of the support structure, the protection brackets 221 can rotate around the receptacle 211 until the outermost protection bracket 221 partially abuts against the support structure, so that the flight suit mounted in the middle of the support structure is completely accommodated in the protective cover 22. Even, the protective cover 22 may not comprise a receptacle 211, for example, the protective brackets 221 parallel to each other may be folded or stacked on each other by a movement direction at an angle to the extension direction of the support structure, in particular, the protective brackets 221 may be stacked or unfolded on each other by an external push-pull force in a movement direction perpendicular to the extension direction of the support structure, in order to expose the flight suit when stacked on each other and to surround the flight suit when unfolded. The installation position and installation/non-installation of the receiving member 211 are not limited herein.

Further, it is also possible to make the protective cover 22 include a locking member by which a plurality of the protective brackets 221 are held fixed relative to each other. The locking members are particularly suitable for the stacked configuration of the protective supports 221, as shown in fig. 1-2, and are configured to keep the protective supports 221 fixed relative to each other in the extended state of the protective cover 22, so as to prevent the adjacent protective supports 221 from being separated from each other, thereby ensuring the integrity of the protective cover 22 in the extended state. In particular, the protection bracket 221 further includes a limiting portion, which limits a maximum distance between adjacent protection brackets 221, so that separation between adjacent protection brackets 221 can be avoided, thereby ensuring integrity of the protection cover 22 in the unfolded state. In the first state, the protective bracket 221 is partially or completely covered by the support structure. And the protection brackets 221 may have a fan shape or a square shape to facilitate folding or stacking each other. To realize a shade for a flight suit, the protective part can be one or more of a sector, a cylinder, an elliptic cylinder or an approximately rectangular parallelepiped.

In a particular embodiment, the number of protective members 2 is the same as the number of support structures. The same number of protective members 2 and support structures are provided to protect all flying suits connected to the support structures. In particular, a single support structure may include several protective shields 22, such as an even number of protective shields 22 symmetrically disposed about a central axis of the support structure, to provide full protection for flight suits at different installation locations.

In a specific embodiment, the body is one or more of a cuboid, a cylinder, and a sphere. In the first state, all flight suit is located in the main part to when imaging device need save or transport, can reduce the volume that this imaging device occupy, make things convenient for its storage or transport, succinct pleasing to the eye. In another embodiment, the flying suit mounted on the body may be located outside the body in the second state. By locating the flying suit outside the body when it is needed and within the body when it is not needed, accidental damage to the flying suit when the handheld imaging device is used for shooting can be further avoided. Optionally, the imaging device further comprises at least one of an illumination unit, a sensing unit, a lidar. For example, when the user needs to take an aerial photograph, the flying suit and the shooting unit can be positioned outside the main body, and other accessories are positioned in the main body to reduce wind resistance; when the user takes a photo by plane at night, the lighting unit, the flight suit and the shooting unit can be positioned outside the main body, and other accessories are positioned in the main body, so that the brightness of night imaging is improved. When the fixed-point distance measurement is needed, the main body can be fixed at a certain preset position, the laser radar or other types of distance measurement sensors are arranged outside the main body, and the flying suit and other accessories are arranged in the main body, so that the interference of the flying suit and other accessories on the distance measurement is reduced, and the accidental damage caused by the flying suit and other accessories can be further avoided.

Preferably, since the shooting target in the aerial photography is usually located in front of, behind or below the imaging device, the shooting unit 1003 may be disposed on the front side, the rear side or the bottom of the imaging device. In order to further avoid transmitting the vibration on the imaging apparatus main body to the shooting unit 1003 and to strengthen the shooting range of the shooting unit 1003, the shooting unit 1003 may further include one or more holders, and the holders may be connected to the main body. In addition, other holders can be arranged at the bottom or the top of the main body, so that different devices can be arranged on the holders in different application scenes to expand the functions of the imaging device. For example, when the imaging apparatus is used for aerial photography, an imaging device may be mounted on the pan/tilt head for taking pictures, recording videos, and the like. For example, when the imaging device is used for remote sensing, a remote sensing device such as an infrared sensor or a night vision imager may be mounted on the pan/tilt head. For another example, when the image forming apparatus is used for agricultural production, a sowing machine may be carried on the pan/tilt head to sow seeds, fertilize, or spray pesticides, etc. For example, when the imaging device is used to assist the construction of a suspension bridge, one end of the guide cable may be fixed to the pan/tilt head, and the guide cable may be pulled by the imaging device so as to erect a linear temporary construction convenience road parallel to the main cable under the main cable of the suspension bridge, thereby facilitating the construction of bridge constructors.

In a specific embodiment, the imaging apparatus further includes an operation unit 1004. The operating unit 1004 includes at least one of a thumb wheel, a stick, a dial, a rocker, and a key, the number of the operating unit 1004 may be one or more according to the application scenario and the usage requirement of the imaging device, and the specific structure of the operating unit 1004 may be designed according to the specific number and type of the flight suit, generally, the operating unit 1004 may include a plurality of operating units 1004, for example, the number of the operating units 1004 is two, three, or four, for example, the operating unit 1004 in fig. 6 is composed of a key and a stick. The operation unit 1004 may include a composite function key, which may include several keys, and the composite function key may enable switching of functions in a first state and/or a second state. The functions comprise one or more of photographing, recording, imaging device state switching, focal length adjustment and exposure adjustment. For example, the shift lever in fig. 6 may be divided into three stages, where the first stage corresponds to the power being turned off, the second stage corresponds to the first state, and the third stage corresponds to the second state; that is, in the first gear the imaging device is not powered and all of the flight suits are received in the main body, in the second gear the imaging device is powered and all of the flight suits are received in the main body, in the third gear the imaging device is powered and at least one of the flight suits is located outside the main body. For example, the composite function key in fig. 6 may include only one key, and the composite function key corresponds to several functions such as focus adjustment, exposure adjustment, and shutter speed switching (for example, different functions are realized by long pressing, short pressing, and several clicks) in the first state, and corresponds to several functions such as photographing, recording, and stopping photographing in the second state, so as to realize the switching of the functions in the first state and/or the second state. It is emphasized that the corresponding functions of the multi-function key in the first state and the second state may be identical, partially identical or completely different. Further, as shown in fig. 8, the complex function key does not protrude from the surface of the main body to reduce the storage space and the flight wind resistance of the imaging device.

As described above, the functions corresponding to the composite function key may further include switching of states of an imaging device, and when the switching of the states of the imaging device is triggered, the imaging device is switched between a first state and a second state, where at least one of the flying suits is located outside the main body in the first state and all the flying suits are stored in the main body in the second state.

In a specific embodiment, the support structure can be received in the main body, thereby further reducing a receiving space of the image forming apparatus. In particular, when the support structure is received in the body, the outer surface of the support structure is flush with the outer surface of the body, i.e. when a portion of the support structure forms the outer surface of the imaging device together with the outer surface of the body, and the outer surface of the imaging device extends continuously, avoiding excessive sag and dislocation, to maintain the integrity of the outer surface of the imaging device when the support structure is received.

EXAMPLE III

The present embodiments provide a method of operating an unmanned aerial vehicle comprising an aircraft component, a horn, and a fuselage; the method comprises the following steps: switching the unmanned aerial vehicle to a first state, and controlling the arm to rotate relative to the fuselage so as to enable at least one aircraft component to be located outside the fuselage; and/or switching the unmanned aerial vehicle to a second state, and controlling the arm to rotate relative to the fuselage so as to enable at least one aircraft component to be located in the fuselage.

According to the operation method of the unmanned aerial vehicle provided by the embodiment of the third aspect of the invention, the horn 1001 capable of rotating relative to the body 1002 is arranged, so that the aircraft component of the unmanned aerial vehicle in the second state can be rapidly stored relative to the body 1002; aircraft part can be located outside the fuselage when taking photo by plane, and aircraft part can accomodate completely in fuselage 1002 when handheld shooting, and benefit from fuselage 1002 to the protection of aircraft part, and the aircraft part can not expose under the state of accomodating, has correspondingly reduced the possibility of aircraft part to user's unexpected injury, has also reduced the incidence of aircraft part damage accident that collides with, and is more energy-conserving simultaneously, has prolonged the battery life of device.

The specific structure, function and working principle of the unmanned aerial vehicle have been described in detail in the first embodiment, and are not described herein again.

Example four

The present embodiment provides a method of operating an imaging device comprising a camera unit, a support structure, a flight suit, and an imaging device body, the camera unit being connected to the body, the method comprising: switching the imaging device to a first state, and controlling the support structure to rotate relative to the main body so that at least one flying suit is positioned outside the main body; and/or switching the imaging device to a second state, and controlling the support structure to rotate relative to the main body so that at least one flying suit is positioned in the main body.

According to the operating method of the imaging device provided by the embodiment of the fourth aspect of the invention, the supporting structure capable of rotating relative to the main body is arranged, so that the flying suit can be rapidly stored relative to the main body in the second state; the flight suit can be located outside the main part during the aerial photography, and the flight suit can be accomodate in the main part completely when handheld shooting, and benefit from the protection of main part to the flight suit, and the flight suit can not expose under accomodating the state, has correspondingly reduced the possibility of flight suit to the unexpected injury of user, has also reduced the incidence that the damage accident was collided with to the flight suit, and is more energy-conserving simultaneously, has prolonged the battery life of device.

The detailed structure, function and operation principle of the imaging device have been described in detail in the second embodiment, and are not described herein again.

EXAMPLE five

The present embodiment provides a computer-readable storage medium storing a computer program, which, when executed by a processor, causes the processor to implement the method of operation as described in the third embodiment.

EXAMPLE six

The present embodiment provides a computer-readable storage medium storing a computer program that, when executed by a processor, causes the processor to implement the method of operation as described in the fourth embodiment.

In the description of the present specification, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or unit must have a specific direction, be configured and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

In the description herein, the description of the terms "one embodiment," "some embodiments," "specific embodiments," etc., means 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 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.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An unmanned aerial vehicle, comprising:

an aircraft component;

a horn to which at least one of the aircraft components is connected;

a fuselage, the horn being rotatable relative to the fuselage to receive at least one of the aircraft components in the fuselage.

2. The unmanned aerial vehicle of claim 1, wherein: the unmanned aerial vehicle further comprises a protection component for protecting the aircraft component.

3. The unmanned aerial vehicle of claim 2, wherein: the protection component comprises a protection cover, and the protection cover is connected to the horn.

4. The unmanned aerial vehicle of claim 3, wherein: at least a part of the protective cover is movable toward a horn side to be retracted from a peripheral side of the horn; and/or the presence of a gas in the gas,

at least a part of the protective cover is movable to a side away from the horn to protrude from a peripheral side of the horn.

5. The unmanned aerial vehicle of claim 4, wherein: in a first state, the protective cover is retracted until the protective cover is at least partially attached to the horn; in a second state, the protective cover is deployed to partially or fully cover the aircraft component.

6. The unmanned aerial vehicle of claim 3, wherein: the protective cover comprises protective brackets which are foldable on themselves or stackable on each other.

7. The unmanned aerial vehicle of claim 6, wherein: the protective cover further comprises a locking member, and the plurality of protective brackets are kept fixed relative to each other through the locking member.

8. The unmanned aerial vehicle of claim 6, wherein: in a first state, the protective bracket is partially or completely covered by the horn.

9. The unmanned aerial vehicle of claim 6, wherein: the protective bracket is fan-shaped or square.

10. The unmanned aerial vehicle of claim 6, wherein: the protective bracket comprises a limiting part, and the limiting part limits the maximum distance between adjacent protective brackets.

11. The unmanned aerial vehicle of claim 2, wherein: the protective component is one or more of a sector, a cylinder, an elliptic cylinder or an approximate cuboid.

12. The unmanned aerial vehicle of claim 2, wherein: the number of the protection components is the same as that of the machine arms.

13. The unmanned aerial vehicle of claim 1, wherein: the fuselage is connected to one end of the horn, and the aircraft component is connected to the other end of the horn.

14. The unmanned aerial vehicle of claim 1, wherein: the horn includes main arm and support arm, the support arm connect in the main arm, the fuselage connect in the main arm, the aircraft part connect in the support arm.

15. The unmanned aerial vehicle of claim 14, wherein: the support arm is perpendicular to the main arm.

16. The unmanned aerial vehicle of claim 14, wherein: the support arm is connected to the middle part of the main arm.

17. The unmanned aerial vehicle of claim 14, wherein: the aircraft component is attached to the free end of the arm.

18. The unmanned aerial vehicle of claim 14, wherein: the horn still includes the folded piece, the support arm passes through the folded piece with main arm is connected.

19. The unmanned aerial vehicle of claim 18, wherein: the arm is rotatable about the fold so as to be substantially parallel to the primary arm in a first state and at an angle to the primary arm in a second state.

20. The unmanned aerial vehicle of claim 19, wherein: the arm is partially or fully shielded by the main arm in the first state.

21. The unmanned aerial vehicle of claim 14, wherein: the horn further includes a limiting member to lock the relative position of the arm to the main arm.

22. The unmanned aerial vehicle of claim 1, wherein: the mode that the horn is connected to the horn includes: the horn is connected to through rotating the piece fuselage side and preceding, rear junction, the horn is connected to fuselage side central line department, the horn is connected to at least one kind in the fuselage inside.

23. The unmanned aerial vehicle of claim 1, wherein: the fuselage is one or more in cuboid, cylinder, spheroid.

24. The unmanned aerial vehicle of claim 1, wherein: in a first state, all the aircraft components are received in the fuselage.

25. The unmanned aerial vehicle of claim 1, wherein: the aircraft component comprises at least one of a power assembly, a lighting piece, a sensor, a laser radar and a shooting unit.

26. The unmanned aerial vehicle of claim 1, wherein: the unmanned aerial vehicle further comprises one or more shooting units, and the shooting units are arranged on the front side, the rear side or the bottom of the unmanned aerial vehicle.

27. The unmanned aerial vehicle of claim 26, wherein: the shooting unit further comprises one or more cloud platforms, and the cloud platforms are connected to the machine body.

28. The unmanned aerial vehicle of claim 1, wherein: the unmanned aerial vehicle further comprises an operating unit.

29. The unmanned aerial vehicle of claim 28, wherein: the operation unit comprises a composite function key, and the composite function key can realize the switching of functions in a first state and/or a second state.

30. The unmanned aerial vehicle of claim 29, wherein: the functions comprise at least one of photographing, video recording, aircraft state switching, focal length adjustment and exposure adjustment.

31. The unmanned aerial vehicle of claim 30, wherein: when an aircraft state switching function is triggered, the aircraft is switched between a first state and a second state, at least one aircraft component is located outside the fuselage in the first state, and at least one aircraft component is stored in the fuselage in the second state.

32. The unmanned aerial vehicle of claim 28, wherein: the operation unit comprises at least one of a dial wheel, a dial rod, a rotary table and a key.

33. The unmanned aerial vehicle of claim 1, wherein: the horn is receivable in the body.

34. The unmanned aerial vehicle of claim 33, wherein: when the horn is received in the fuselage, the outer surface of the horn is flush with the outer surface of the fuselage.

35. An image forming apparatus, comprising:

a shooting unit;

the supporting structure is connected with a flying suit, and the flying suit is used for realizing the lifting of the imaging device;

the shooting unit is connected to the main body, and the supporting structure can rotate relative to the main body so that the flying suit is unfolded outside the main body.

36. The imaging apparatus of claim 35, wherein: the main part is connected in the one end of bearing structure, the flight suit is connected in the other end of bearing structure.

37. The imaging apparatus of claim 35, wherein: the support structure comprises a main arm and a support arm, the support arm is connected to the main arm, the main body is connected to the main arm, and the flying suit is connected to the support arm.

38. The imaging apparatus of claim 37, wherein: the support arm is perpendicular to the main arm.

39. The imaging apparatus of claim 37, wherein: the support arm is connected to the middle part of the main arm.

40. The imaging apparatus of claim 37, wherein: the flight suit is connected to the free end of support arm.

41. The imaging apparatus of claim 37, wherein: the support structure further comprises a folding member, and the support arm is connected with the main arm through the folding member.

42. The imaging apparatus of claim 41, wherein: the arm is rotatable about the fold so as to be substantially parallel to the primary arm in a first state and at an angle to the primary arm in a second state.

43. The imaging apparatus of claim 42, wherein: the arm is partially or fully shielded by the main arm in the first state.

44. The imaging apparatus of claim 37, wherein: the support structure further includes a limiting member to lock the position of the arm relative to the main arm.

45. The imaging apparatus of claim 35, wherein: the manner in which the support structure is attached to the body includes: the support structure is connected to the body at a lateral and anterior-posterior junction, the support structure is connected to the body at a lateral midline, and the support structure is connected to at least one of the interior of the body.

46. The imaging apparatus of claim 35, wherein: the imaging device further comprises a protection component for protecting the flying suit.

47. The imaging apparatus of claim 46, wherein: the protective member includes a protective cover connected to the support structure.

48. The imaging apparatus of claim 47, wherein: at least a portion of the protective cover is movable toward a support structure side to retract from a peripheral side of the support structure; and/or the presence of a gas in the gas,

at least a portion of the protective cover is movable away from the support structure side to project from the peripheral side of the support structure.

49. The imaging apparatus of claim 48, wherein: in a first state, the protective cover is retracted until the protective cover is at least partially attached to the support structure; in a second state, the protective bracket is deployed to partially or fully shade the flight suit.

50. The imaging apparatus of claim 47, wherein: the protective cover comprises protective brackets which are foldable on themselves or stackable on each other.

51. The imaging apparatus of claim 50, wherein: the protective cover further comprises a locking member, and the plurality of protective brackets are kept fixed relative to each other through the locking member.

52. The imaging apparatus of claim 50, wherein: in a first state, the protective bracket is partially or fully covered by the support structure.

53. The imaging apparatus of claim 50, wherein: the protective bracket is fan-shaped or square.

54. The imaging apparatus of claim 50, wherein: the protective bracket comprises a limiting part, and the limiting part limits the maximum distance between adjacent protective brackets.

55. The imaging apparatus of claim 46, wherein: the protective component is one or more of a sector, a cylinder, an elliptic cylinder or an approximate cuboid.

56. The imaging apparatus of claim 46, wherein: the number of the protection components is the same as that of the support structures.

57. The imaging apparatus of claim 35, wherein: the main body is one or more of a cuboid, a cylinder and a sphere.

58. The imaging apparatus of claim 35, wherein: in a first state, all of the flight suits are received in the main body.

59. The imaging apparatus of claim 35, wherein: the imaging device further comprises at least one of an illumination unit, a sensing unit and a laser radar.

60. The imaging apparatus of claim 35, wherein: the shooting unit is arranged on the front side, the rear side or the bottom of the main body.

61. The imaging apparatus of claim 35, wherein: the shooting unit further comprises one or more holders, and the holders are connected to the main body.

62. The imaging apparatus of claim 35, wherein: the image forming apparatus further includes an operation unit.

63. The imaging apparatus of claim 62, wherein: the operation unit comprises a composite function key, and the composite function key can realize the switching of functions in a first state and/or a second state.

64. An imaging device as defined in claim 63, wherein: the functions comprise one or more of photographing, recording, imaging device state switching, focal length adjustment and exposure adjustment.

65. The imaging apparatus of claim 64, wherein: when the imaging device state switching function is triggered, the imaging device is switched between a first state and a second state.

66. The imaging apparatus of claim 62, wherein: the operating piece comprises at least one of a shifting wheel, a shifting rod, a rotating disc and a key.

67. The imaging apparatus of claim 35, wherein: the support structure is receivable in the body.

68. An imaging apparatus according to claim 67, wherein: when the support structure is received in the body, an outer surface of the support structure is flush with an outer surface of the body.

69. A method of operating an unmanned aerial vehicle, the unmanned aerial vehicle comprising an aircraft component, a horn, and a fuselage; the method comprises the following steps:

switching the UAV to a first state,

controlling the arm to rotate relative to the fuselage such that at least one of the aircraft components is located outside the fuselage; and/or the presence of a gas in the gas,

switching the UAV to a second state,

controlling the arm to rotate relative to the fuselage such that at least one of the aircraft components is located in the fuselage.

70. A method of operating an imaging device, the imaging device including a camera unit, a support structure, a flight suit, and an imaging device body, the camera unit being coupled to the body, the method comprising:

switching the imaging device to a first state,

controlling the support structure to rotate relative to the body such that at least one of the flying suits is located outside the body; and/or the presence of a gas in the gas,

switching the imaging device to a second state,

controlling the support structure to rotate relative to the body such that at least one of the flying suits is located in the body.

71. A computer-readable storage medium, characterized in that the computer-readable storage medium stores a computer program which, when executed by a processor, causes the processor to carry out the method of operation of claim 69.

72. A computer-readable storage medium, characterized in that the computer-readable storage medium stores a computer program which, when executed by a processor, causes the processor to carry out the method of operation of claim 70.