CN210912850U

CN210912850U - Unmanned vehicles's fuselage and unmanned vehicles who has it

Info

Publication number: CN210912850U
Application number: CN201921178261.7U
Authority: CN
Inventors: 梁杰
Original assignee: Guangzhou Xaircraft Technology Co Ltd
Current assignee: Guangzhou Xaircraft Technology Co Ltd
Priority date: 2019-07-24
Filing date: 2019-07-24
Publication date: 2020-07-03
Anticipated expiration: 2029-07-24

Abstract

The utility model discloses an unmanned vehicles's fuselage and unmanned vehicles who has it, unmanned vehicles's fuselage includes: the fuselage frame is coated with the fuselage shell, an installation space is arranged in the fuselage frame, and the fuselage shell is provided with an installation opening positioned on the bottom wall of the installation space; the lower cover is detachably arranged at the mounting opening to open or close the mounting opening; and the communication module comprises an antenna, and the antenna is arranged on the lower cover and is positioned on the inner side of the mounting port. According to the utility model discloses unmanned vehicles, when using, the antenna is established and is covered under, and the communication connection carries out between antenna and the ground terminal of not only being convenient for, and the antenna can together pull down with the lower cover moreover, is convenient for maintain and change the antenna to improve unmanned vehicles's operational reliability.

Description

Unmanned vehicles's fuselage and unmanned vehicles who has it

Technical Field

The utility model relates to a flight field particularly, relates to an unmanned vehicles's fuselage and has unmanned vehicles of unmanned vehicles's fuselage.

Background

In the unmanned aerial vehicle, the antenna is an important element for realizing the wireless communication function, and the structure of the unmanned aerial vehicle tends to be more compact and the design of the antenna is more and more limited in the current design of the unmanned aerial vehicle. With the rapid development of unmanned aerial vehicles, the antenna is required to have a compact structure and a limited size, and also to have multiple radiation frequency bands.

In the prior art, the antenna of the unmanned aerial vehicle is unreasonable in design, and the radiation pattern of the antenna is stray, so that the signal transceiving capacity of the unmanned aerial vehicle is seriously reduced.

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 vehicles's fuselage, this unmanned vehicles's fuselage, when using, the antenna is established and is covered under, not only is convenient for carry out the communication between antenna and the ground terminal and is connected, and the antenna can be together torn down with the lower cover moreover, is convenient for maintain and change the antenna to improve unmanned vehicles's operational reliability.

The utility model discloses still provide one kind and have unmanned vehicles of unmanned vehicles's fuselage.

To achieve the above object, an embodiment according to a first aspect of the present invention provides an unmanned aerial vehicle including: the fuselage structure comprises a fuselage frame and a fuselage shell, wherein the fuselage shell is wrapped on the fuselage frame, an installation space is arranged in the fuselage frame, and an installation opening is formed in the bottom wall of the installation space; the lower cover is detachably arranged at the mounting opening to open or close the mounting opening; the communication module comprises an antenna, and the antenna is arranged on the lower cover and positioned on the inner side of the mounting opening.

According to the utility model discloses unmanned vehicles's fuselage, when using, the antenna is established and is covered under, is convenient for not only carry out the communication between antenna and the ground terminal and is connected, and the antenna can together pull down with the lower cover moreover, is convenient for maintain and change the antenna to improve unmanned vehicles's operational reliability.

In addition, the fuselage of the unmanned aerial vehicle according to the above embodiment of the present invention may also have the following additional technical features:

furthermore, the fuselage shell has the plane of symmetry, the fuselage shell is for the plane of symmetry bilateral symmetry, the antenna is a plurality of, and is a plurality of the antenna distributes the left and right sides of plane of symmetry.

Furthermore, a support foot rest extending downwards is arranged on the lower cover, an accommodating cavity is formed in the support foot rest, and at least one part of the antenna is arranged in the accommodating cavity.

Furthermore, the two supporting foot frames are arranged in a bilateral symmetry mode, the accommodating cavity is formed in each supporting foot frame, and the antenna is arranged in each accommodating cavity.

Further, the antenna in the accommodating cavity is vertically placed.

Further, the inner wall of the lower cover is provided with a containing groove positioned at the rear side of the supporting foot frame, and a part of the antenna is placed in the containing groove.

Further, the communication module further comprises a data transmission module, the antenna is electrically connected with the data transmission module, and the data transmission module is installed on the lower cover and located on the inner side of the installation opening.

Further, the lower cover includes: the base cover is detachably arranged on the machine body frame; the heat dissipation piece is arranged on the inner wall of the base cover, the data transmission module is installed on the heat dissipation piece, and the base cover is provided with heat dissipation holes used for dissipating heat of the heat dissipation piece.

Furthermore, the heat dissipation member comprises a heat dissipation substrate and heat dissipation fins, the heat dissipation fins are arranged on the heat dissipation substrate and extend out of the base cover through the heat dissipation holes, and the data transmission module is installed on the inner wall of the heat dissipation substrate.

Further, a heat conducting adhesive layer is arranged between the heat dissipation piece and the data transmission module.

According to the utility model discloses an embodiment of second aspect provides an unmanned vehicles, unmanned vehicles includes: a fuselage, the fuselage being an unmanned aerial vehicle fuselage in accordance with an embodiment of the first aspect of the present disclosure; the two fixed wings are symmetrically arranged on the opposite side walls of the machine body.

Furthermore, every the stationary vane includes branch and airfoil, branch is fixed on the fuselage frame, the airfoil cladding is in the outside of branch, the airfoil is light material spare.

According to the utility model discloses unmanned vehicles, through utilizing according to the utility model discloses an unmanned vehicles's the embodiment of first aspect fuselage, when using, the antenna is established and is covered under, not only is convenient for carry out the communication between antenna and the ground terminal and is connected, the antenna can together pull down with the lower cover in addition, is convenient for maintain and change the antenna to improve unmanned vehicles's operational reliability.

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 structural diagram of an unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 2 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 3 is a schematic partial structural view of a fuselage of an unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 4 is a schematic structural view of a first fixed frame of a fuselage of an unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 5 is a schematic structural view of a first fixed frame of a fuselage of an unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 6 is a schematic structural view of a second fixed frame of the fuselage of the unmanned aerial vehicle according to an embodiment of the invention.

Fig. 7 is a schematic structural diagram of a lower cover and a communication module of a fuselage of an unmanned aerial vehicle according to an embodiment of the invention.

Fig. 8 is a schematic structural diagram of a base cover of a lower cover of a fuselage of an unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 9 is a schematic structural diagram of a base cover of a lower cover of a fuselage of an unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 10 is a schematic structural view of a radiator element of a lower cover of a fuselage of an unmanned aerial vehicle according to an embodiment of the present invention.

Reference numerals: an unmanned aerial vehicle 100,

A body 10, a body frame 111,

The first fixing frame 11, the bottom wall 1101, the first side wall 1102, the first front end wall 1103, the first rear end wall 1104, the connecting wall 1105, the guide groove 1106, the locker 13, the first receiving cavity 110, the detaching opening 112, the first locking member 13, the second locking member, and the second locking member,

Second fixed frame 12, second front end wall 1201, second rear end wall 1202, top wall 1203, second side wall 1204, second receiving cavity 120, mounting opening 113, mounting hole 115, and the like,

An upper cover 15, a lower cover 16, a base cover 161, a support leg 1611, a receiving cavity 16110, a receiving groove 1612, a heat dissipating hole 1613, a heat dissipating member 162, a heat dissipating substrate 1621, heat dissipating fins 1622, a heat sink cover, a,

An electricity storage device 60,

A positioning module 114,

A flight control unit 80, a main board 81, an inertia measurement unit 82, a wiring space 83,

A communication module 90, a data transmission module 91, an antenna 92,

Fixed wing 20, strut 211, airfoil 212, first wing segment 21, second wing segment 22, fastener 23, retainer 231, guide hole 2310, hanging portion 232, annular hole 2320, guide bar 221, aileron 24,

A first power assembly 30, a wing arm 31, a first power unit 32, a first propeller 33 and a second power

Assembly 40, fixed base 41, second power unit 42, second propeller 43, tail wing 50, tail wing panel

51. A tail stay 53, a tail stay seat 54, a pin joint structure 55,

An aerial photographing module 70,

A body shell 14, a first mounting opening 1401.

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.

The following describes the body 10 according to an embodiment of the present invention with reference to the drawings.

As shown in fig. 1 to 10, the body 10 according to an embodiment of the present invention includes a body frame 111, a body housing 14, a lower cover 16, and a communication module 90.

The cladding of fuselage shell 14 is equipped with installation space in fuselage frame 111 on fuselage frame 111, is equipped with on fuselage shell 14 to be located the installing port 113 of installation space diapire. The lower cover 16 is detachably provided at the mounting port 113 to open or close the mounting port 113 (up and down direction is shown by arrow a in fig. 3). The communication module 90 includes an antenna 92, and the antenna 92 is provided on the lower cover 16 inside the mounting opening 113.

According to the present invention, the lower cover 16 is detachably disposed at the mounting opening 113 to open or close the mounting opening 113 by providing the body frame 11, the body housing 14, and the lower cover 16 in the body 10. This facilitates the mounting and dismounting of the various structures in the body 10, and facilitates the improvement of the assembly efficiency of the body 10.

By providing the communication module 90, the communication module 90 includes the antenna 92, and the antenna 92 is provided on the lower cover 16 and located inside the mounting opening 113. Therefore, the antenna 92 and the ground terminal are conveniently in communication connection, electromagnetic interference caused by other structures in the body 10 to the communication module 90 is avoided, the communication effect of the communication module 90 is improved, the ground terminal is convenient to control the unmanned aerial vehicle 100, and the control reliability of the unmanned aerial vehicle 100 is improved.

Meanwhile, the antenna 92 can be detached together with the lower cover 16, so that the antenna 92 can be conveniently detached and installed, maintenance and replacement of the antenna 92 are facilitated, and the working reliability of the unmanned aerial vehicle 100 is improved.

Therefore, according to the utility model discloses fuselage 10, when using, antenna 92 establishes on lower cover 16, is not only convenient for carry out the communication connection between antenna 92 and the ground terminal, and antenna 92 can be together torn down with lower cover 16 moreover, is convenient for maintain and change antenna 92 to improve unmanned vehicles 100's operational reliability.

In some embodiments of the present invention, as shown in fig. 1-10, a fuselage 10 according to embodiments of the present invention includes a fuselage frame 111, a fuselage shell 14, a lower cover 16, and a communication module 90.

Optionally, the fuselage 10 further comprises a flight control unit 80, the flight control unit 80 being mounted in the installation space, the flight control unit 80 comprising a main board 81.

According to some embodiments of the present invention, the fuselage frame 111 is provided with an installation space therein. The electricity storage device 60 is provided in the installation space. The positioning module 114 is provided on the top of the body frame 111. The flight control unit 80 comprises a main board 81 and an inertia measurement unit 82 arranged on the main board 81, the main board 81 is fixed in the installation space and located below the positioning module 114, the positioning module 114 is electrically connected with the main board 81, and the power storage device 60 is connected with the main board 81 to supply power to the flight control unit 80. The communication module 90 includes a data transmission module 91 and an antenna 92, the antenna 92 is electrically connected to the data transmission module 91, the data transmission module 91 is located below the flight control unit 80, and the data transmission module 91 is electrically connected to the main board 81.

It should be understood herein that the "positioning module 114 is electrically connected to the motherboard 81" for communication and/or electrical connection.

According to the embodiment of the present invention, the positioning module 114 is disposed at the top of the fuselage frame 111 by disposing the positioning module 114 on the fuselage 10. Therefore, the positioning module 114 can conveniently position the unmanned aerial vehicle 100, the positioning function of the positioning module 114 is enhanced, the positioning accuracy and precision of the positioning module 114 are improved, and the working reliability and stability of the positioning module 114 are improved, so that the flying position of the unmanned aerial vehicle 100 can be determined quickly and accurately.

Furthermore, by providing the communication module 90 such that the communication module 90 includes the data transmission module 91 and the antenna 92, the data transmission module 91 is located below the flight control unit 80. Therefore, the communication connection between the communication module 90 and the ground terminal is facilitated, electromagnetic interference to the communication module 90 caused by other structures in the fuselage 10 is avoided, the communication effect of the communication module 90 is improved, the ground terminal is convenient to control the unmanned aerial vehicle 100, and the control reliability of the unmanned aerial vehicle 100 is improved.

Further, by connecting the power storage device 60 to the main board 81, the main board 81 is located below the positioning module 114, and the data transmission module 91 is located below the flight control unit 80. Therefore, the power storage device 60 supplies power to the positioning module 114 and the data transmission module 91 through the main board 81, and the power storage device 60, the main board 81, the positioning module 114 and the data transmission module 91 are electrically connected, so that the wiring structure in the machine body 10 is simplified, and the layout in the machine body 10 is more reasonable and compact.

Specifically, the main board 81 is formed by integrating a flight control main board and a power supply main board, and an Inertial Measurement Unit (IMU)82 is disposed above the main board 81.

In some embodiments of the present invention, as shown in fig. 6, the communication module 90 and the main board 81 are spaced apart from each other to form a trace space 83. Therefore, enough operation space and accommodating space are reserved for the connecting line terminal between the data transmission module 91 and the flight control unit 80, assembly and forming of the unmanned aerial vehicle 100 are facilitated, operation of a user is facilitated, and assembly convenience of the unmanned aerial vehicle 100 is improved.

Alternatively, as shown in fig. 4 and 5, the body frame 111 includes a first fixed frame 11 and a second fixed frame 12, the first housing chamber 110 is provided in the first fixed frame 11, and the power storage device 60 is provided in the first housing chamber 110. A second accommodating cavity 120 is formed in the second fixed frame 12, the second fixed frame 12 is disposed on the first fixed frame 11, the positioning module 114 is fixed on the second fixed frame 12, and the flight control unit 80 is disposed in the second accommodating cavity 120. This facilitates positioning of the electrical storage device 60 for installation of the electrical storage device 60, positioning of the positioning module 114 and the flight control unit 80 for installation of the positioning module 114 and the flight control unit 80, thereby improving the assembly efficiency of the fuselage 10 and shortening the assembly time of the fuselage 10.

Further, as shown in fig. 6, the top wall of the second fixed frame 12 is provided with a through hole through which a part of the positioning module 114 protrudes out of the second fixed frame 12. This facilitates positioning of a part of the positioning module 114 above the second fixed frame 12, facilitates smooth positioning of the unmanned aerial vehicle 100 by the positioning module 114, and improves positioning accuracy and reliability of the positioning module 114.

Specifically, as shown in fig. 6, the bottom wall of the second fixed frame 12 is provided with a mounting opening 113, and the flight control unit 80 is mounted in the second housing chamber 120 through the mounting opening 113. This facilitates installation of the flight control unit 80 into the second housing chamber 120, further improving the assembly efficiency of the fuselage 10.

Alternatively, as shown in fig. 3, the first fixed frame 11 is provided on the front side of the second fixed frame 12 (the front-rear direction is shown by arrow B in fig. 3), the top of the first fixed frame 11 is provided with a detachment port 112, and the electric storage device 60 is detachably provided in the first housing chamber 110 through the detachment port 112. This facilitates the mounting and dismounting of the electrical storage device 60, and facilitates the maintenance and replacement of the electrical storage device 60.

Specifically, at least a part of the bottom wall of the second fixed frame 12 is located above the bottom wall of the first fixed frame 11 to form the routing space 83. Therefore, the formation of the wiring space 83 is facilitated, more operation spaces and accommodating spaces are conveniently arranged, and the reasonability and the neatness of the internal structure of the machine body 10 are improved.

In some embodiments of the present invention, as shown in fig. 4 and 5, the first fixed frame 11 comprises a bottom wall 1101, two first side walls 1102, a first front end wall 1103 and a first rear end wall 1104. The bottom wall 1101, the two first side walls 1102, the first front end wall 1103, and the first rear end wall 1104 together define a first housing cavity 110 having an opening at the top, and the first housing cavity 110 may be used to house the power storage device 60. Lightening slots are formed in the bottom wall 1101, the two first side walls 1102, the first front end wall 1103 and the first rear end wall 1104 to reduce the flight weight of the unmanned aerial vehicle 100. The end portions of the two first side walls 1102 close to the opening of the first receiving cavity 110 are extended outward to form a connecting wall 1105, and a reinforcing rib is arranged between the connecting wall 1105 and the first side wall 102. Further, the connecting wall 1105 has a guide groove 1106 formed in the longitudinal direction thereof so as to penetrate the upper and lower end surfaces thereof. Further, a locker 13 for locking the power storage device 60 is also provided on the first fixed frame 11. The locker 13 is movably coupled to the guide groove 1106.

In some embodiments of the present invention, as shown in fig. 6, second fixed frame 12 includes a second front end wall 1201, a second rear end wall 1202, a top wall 1203, and two second side walls 1204 connected to both sides of second front end wall 1201 and second rear end wall 1020. The second front end wall 1201, the second rear end wall 1202, the top wall 1203 and the two second side walls 1204 together enclose a second receiving cavity 120 with an open lower end. The second fixed frame 12 is fixed to the first rear end wall 1104 of the first fixed frame 11 by the second front end wall 1201, and an accommodating space is formed between the open lower end of the second fixed frame 12 and the first rear end wall 1104 of the first fixed frame 11. The top wall 1203 is formed with a through hole, the positioning module 114 is adapted to be received in the second receiving cavity 120 and fixed to the inner side of the top wall 1203, and a portion of the positioning module 114 penetrates through the second receiving cavity 120 along the through hole.

In some embodiments of the present invention, as shown in fig. 3, the bottom wall of the body frame 111 is provided with a mounting opening 113, and the lower cover 16 is detachably provided on the body frame 111 to open or close the mounting opening 113. The communication module 90 further includes a data transmission module 91, the antenna 92 is electrically connected to the data transmission module 91, the data transmission module 91 is electrically connected to the main board 81, and the data transmission module 91 is mounted on the lower cover 16 and located inside the mounting opening 113. This not only facilitates the removal and installation of the structure within the body 10, but also the data transmission module 91 can be removed along with the lower cover 16, facilitating the maintenance and replacement of the data transmission module 91. Meanwhile, the motherboard 81 is convenient to power the communication module 90.

Specifically, as shown in fig. 7, the lower cover 16 includes a base cover 161 and a heat dissipation member 162, the base cover 161 is detachably provided on the body frame 111, and the base cover 161 is provided with a heat dissipation hole 1613. The heat sink 162 is disposed on an inner wall of the base cover 161, the data transmission module 91 is mounted on the heat sink 162, and the base cover 161 is provided with a heat dissipation hole 1613 for dissipating heat of the heat sink 162. Therefore, the data transmission module 91 can conduct the internal heat to the heat dissipation member 162, and the heat dissipation member 162 is used for dissipating heat outside the machine body 10, so that the heat dissipation efficiency of the data transmission module 91 is improved, and the working performance of the data transmission module 91 is improved.

Optionally, a thermal conductive adhesive layer is disposed between the heat sink 162 and the data transmission module 91. Specifically, the data transmission module 91 is connected to the heat sink 162 via a thermally conductive silicone grease.

More specifically, as shown in fig. 10, the heat sink 162 includes a heat sink substrate 1621 and heat sink fins 1622, the heat sink fins 1622 are disposed on the heat sink substrate 1621 and extend out of the base cover 161 through a heat sink hole 1613, and the data transmission module 91 is mounted on an inner wall of the heat sink substrate 1621. The heat dissipation area of the heat dissipation member 162 can be increased by providing the heat dissipation fins 1622, so that the heat dissipation member 162 can exchange heat with the external environment, and the heat can be conducted out of the body 10, thereby improving the heat dissipation effect of the heat dissipation member 162.

Optionally, the antenna 92 is mounted on the lower cover 16. Therefore, the antenna 92 and the ground terminal are conveniently in communication connection, and the accuracy and the reliability of data transmission between the antenna 92 and the ground terminal are improved.

In some embodiments of the present invention, as shown in fig. 8, a downwardly extending supporting foot 1611 is disposed on the lower cover 16, a containing cavity 16110 is disposed inside the supporting foot 1611, and at least a portion of the antenna 92 is disposed in the containing cavity 16110. This facilitates the installation of the antenna 92, facilitates the positioning of the antenna 92 at the lower portion of the body 10, and facilitates the communication connection of the antenna 92 with a ground terminal.

Specifically, the two support legs 1611 are arranged symmetrically left and right (left and right directions are shown by an arrow C in fig. 3), each support leg 1611 is provided with an accommodating cavity 16110, and each accommodating cavity 16110 is provided with an antenna 92. Therefore, the antennas 92 are arranged on the left side and the right side of the lower cover 16, and the communication stability and reliability of the antennas 92 are improved.

More specifically, the antenna 92 within the housing chamber 16110 is vertically disposed. Thus, the antenna 92 can work smoothly, the signal receiving and sending capability of the antenna 92 is improved, the antenna 92 is in communication connection with the ground terminal conveniently, and the communication effect of the antenna 92 is improved.

Alternatively, as shown in fig. 6, the inner wall of the lower cover 16 has a receiving groove 1612 at the rear side of the supporting leg 1611, and a portion of the antenna 92 is placed in the receiving groove 1612. Therefore, more antennas 92 are arranged at different positions of the lower cover 16, the antennas 92 can receive and send signals at the left side, the right side, the front side and the rear side of the lower cover 16 conveniently, and the situation that poor communication occurs between the antennas 92 and the ground is avoided.

According to an alternative embodiment of the present invention, as shown in fig. 1, the fuselage 10 further includes an upper cover 15 and a fuselage housing 14, the fuselage housing 14 is wrapped on the fuselage frame 111, and the upper cover 15 and the lower cover 16 are in streamline transition with the fuselage housing 14. Specifically, the upper cover 15 covers and seals the first mounting opening 1401 on the fuselage housing 14 to ensure that the electrical storage device 60 provides safe flight for the unmanned aerial vehicle 100. The lower cover 16 is disposed at a second mounting opening corresponding to the opening of the second receiving cavity 120 opened at the lower end of the second fixing frame 12. Two support legs 1611 extend below the base cover 161, and a receiving cavity 16110 is formed in the support legs 1611. Accommodation grooves 1612 are provided on both sides of the rear end of the base cover 161. The antennas 92, which may be 4 antennas, may be disposed in the receiving cavities 16110 inside the rear-end receiving groove 1612 of the base cover 161 and the supporting leg 1611.

In other words, the fuselage 10 includes a fuselage frame 111 and a fuselage housing 14, the fuselage housing 14 covers the fuselage frame 111, an installation space is provided in the fuselage frame 111, and an installation opening 113 located on a bottom wall of the installation space is provided on the fuselage housing 14. The lower cover 16 is detachably provided at the mounting port 113 to open or close the mounting port 113. The antenna 92 is provided on the lower cover 16 inside the mounting opening 113. The body housing 14 is provided with an installation opening 113 at a bottom wall of the installation space, and the lower cover 16 is detachably provided at the installation opening 113 to open or close the installation opening 113.

Further, the positioning module 114 penetrates out of the second receiving cavity 120 along the through hole; then, the flight control unit 80 is accommodated in the second accommodating cavity 120 and fixed with the inner wall of the second accommodating cavity 120 through a fastener; the data transmission module 91 of the communication module 90 is fixed on the heat dissipation casing 162, the heat dissipation casing 162 fixed with the data transmission module 91 is fixed on the base cover 161, and the antenna 92 is disposed in the accommodation grooves 1612 at the two sides of the rear end of the base cover 161 and the accommodation cavity 16110 in the support foot 1611. Finally, the lower body cover 16 composed of the heat dissipation case 162 and the base cover 161 is disposed at the second mounting opening corresponding to the opening of the second receiving cavity 120 opened at the lower end of the second fixing frame 12, so as to seal the second mounting opening.

In some embodiments of the present invention, the fuselage shell 14 of the fuselage 10 is streamlined to reduce the air resistance during flight. Of course, the fuselage shell 14 of the fuselage 10 may have other shapes. The fuselage shell 14 is wrapped outside the fuselage frame 111, in other words, the fuselage frame 111 is embedded inside the fuselage shell 14. The body casing 14 is formed with a first mounting opening 1401 corresponding to an upper end opening of the first housing cavity 110 and a second mounting opening corresponding to a lower end opening of the second fixed frame 12, so that the power storage device 60 and other electronic components can be easily attached and detached.

Specifically, the fuselage 10 is symmetrically disposed, and the fuselage skin 14 has a plane of symmetry. The body housing 14 is symmetrical to the left and right with respect to the symmetry plane, and the plurality of antennas 92 are distributed on the left and right sides of the symmetry plane. This facilitates the fuselage 10 to be more evenly stressed during flight, facilitates the antenna 92 to send and receive signals on the left and right sides of the plane of symmetry, and facilitates the improvement of the stability and reliability of the communication between the antenna 92 and the ground terminal.

More specifically, the axis of the fuselage 10 and the center of gravity of the UAV 100 are both located on the plane of symmetry of the fuselage 10. The fuselage 10 is a load bearing component of the unmanned aerial vehicle 100, and electrical mounts may be provided on or in the fuselage 10. Electronic components such as the power storage device 60, the aerial photography module 70, the flight control unit 80, the positioning module 114, and the communication module 90 may be provided in the electrical installation part.

In some embodiments of the present invention, the positioning module 114 is disposed in the second accommodating cavity 120, so that the positioning module 114 penetrates the second accommodating cavity 120 along the through hole and is located at the top end of the body 10. The positioning function of the positioning module is greatly enhanced. The flight control unit 80 penetrates the second accommodating chamber 120 along the lower end opening of the second accommodating chamber 120 and is fixed, so that the unmanned aerial vehicle 100 is easy to disassemble, assemble and maintain and is reasonable in layout. The data transmission module 91 of the communication module 90 is fixed on the heat dissipation housing 162, the heat dissipation fins 1622 are arranged on the outer surface of the heat dissipation housing 162, the heat generated during the operation of the data transmission module 91 can be led out of the machine body 10, and the heat dissipation housing 162 fixed with the data transmission module 91 is fixed on the base cover 161, so that the lower cover 16 assembly body formed by the heat dissipation housing 162 and the base cover 161 is formed. During the assembly, only need to set up the assembly body of lower cover 16 in the corresponding second installing port of the fixed frame 12 lower extreme opening of second department, increased the rationality of unmanned vehicles 100 overall arrangement once more, the convenience of assembly, the equipment is convenient, easily the operation. And a wiring space 83 is formed between the lower end of the opening of the second accommodating cavity 120 and the first rear end wall 1104 of the first fixed frame 11, so that an operation space and an accommodating space are reserved for a connecting line terminal between the data transmission module 91 and the flight control unit 80, and the assembly is convenient. The antenna 92 is disposed in the receiving groove 1612 at both sides of the rear end of the base cover 161 and the receiving cavity 16110 inside the supporting leg 1611. Such that antenna 92 facilitates a communication link with a ground terminal.

The following describes the unmanned aerial vehicle 100 according to an embodiment of the present invention. According to the utility model discloses unmanned vehicles 100 includes fuselage 10 and two stationary vanes 20, and fuselage 10 is according to the unmanned vehicles's of the above-mentioned embodiment fuselage 10, two stationary vanes 20 symmetry are established on the relative lateral wall of fuselage 10.

Specifically, as shown in fig. 3, each stationary wing 20 includes a strut 211 and an airfoil 212, the strut 211 is fixed to the fuselage frame 111, the airfoil 212 is wrapped outside the strut 211, and the airfoil 212 is a light-weight material. This not only facilitates enhancing the structural strength and reliability of the stationary wing 20, but also facilitates reducing the weight of the stationary wing 20, thereby reducing the weight of the unmanned aerial vehicle 100.

It is understood that the light material is a new type of composite material, and it is made up by using alkali-resisting glass fibre as reinforcing material, using sulphoaluminate low-alkalinity cement as cementing material and adding proper aggregate to form base material, and adopting the processes of spraying, vertical mould casting, extruding and pulp-flowing to obtain the invented new type inorganic composite material, instead of stone and sand, etc. so as to greatly reduce weight.

Furthermore, the second fixing frame 12 is provided with a mounting hole 115, and the support rod 211 is inserted into the mounting hole 115. The installation setting of branch 211 of being convenient for like this improves the installation stability of branch 211 to the installation setting of stationary vane 20 of being convenient for improves the assembly efficiency of stationary vane 20, improves stationary vane 20's stability and reliability of setting.

Specifically, as shown in fig. 1, two fixed wings 20 are symmetrically installed on two sides of a symmetric plane of the fuselage 10, respectively, and when the unmanned aerial vehicle 100 reaches a certain horizontal flying speed, the fixed wings 20 provide sufficient lift force for the unmanned aerial vehicle 100, so as to ensure that the unmanned aerial vehicle 100 can fly normally. Each stationary wing 20 includes a first wing section 21 and a second wing section 22 connected to each other. Of course, in other embodiments, each stationary wing 20 is not limited to include the first wing segment 21 and the second wing segment 22, and each stationary wing 20 may further include a third wing segment, a fourth wing segment, and the like, which are connected in the same manner as the first wing segment 21 and the second wing segment 22, according to the size design of the unmanned aerial vehicle 100.

The first wing section 21 includes a first end connected to the fuselage 10 and a second end opposite to the first end, and specifically, the first wing section 21 includes two struts 211 and an airfoil 212. One ends of the two supporting rods 211 are respectively fixed on the second side wall of the second fixing frame 12. The airfoil 212 is wrapped around the outer sides of the struts 221 and is connected to the fuselage shell 14. Airfoil 212 may be a lightweight material such as foam to reduce the weight of UAV 100. During production, the airfoil 212 and the fuselage shell 14 can be integrally formed, and a streamline transition is formed between the airfoil 212 and the fuselage shell 14, so that air resistance in flight can be reduced.

Further, as shown in fig. 1, the fixed wing 20 further includes a fixing member 23, and the fixing member 23 is fixed to a second end of the first wing section 21. The fixing member 23 includes a fixing portion 231, the fixing portion 231 is rectangular and has two matching holes formed on its side wall, and one end of the two supporting rods 211 far from the fuselage 10 is connected to the second end of the first wing section 21. So that the volume space occupied by the entire unmanned aerial vehicle 100 can be reduced for storage and carrying.

Specifically, the fixing portion 231 is provided with a guide hole 2310 on the side away from the first wing section 21, and a side surface opposite to the first end of the second wing section 22 is provided with a guide rod 221, so that when the first end of the second wing section 22 is matched with the assembling position where the fixing portion 231 is away from the first wing section 21, the second wing section 22 can be connected to the first wing section 21 through the connection of the guide rod 221 and the guide hole 2310, and the rigidity of the connection of the second wing section 22 and the first wing section 21 is enhanced.

Of course, in an alternative embodiment of the present application, the fixing portion 231 has a guiding rod 221 formed on a side thereof away from the first wing section 21, and a guiding hole 2310 is formed on a side thereof opposite to the first end 221 of the second wing section 22.

In another embodiment, the guiding rod 221 may be two supporting rods 211 of the first wing section 21, and one end of the two supporting rods 211 of the first wing section 21, which is far away from the fuselage 10, penetrates through the side of the fixing portion 231, which is far away from the first wing section 21. A guide hole 2310 is formed on a side surface of the second wing section 22 opposite to the first end 221. The fixing of the first and

second wing sections

21 and 22 is achieved by inserting the guide bar 2310 into the guide hole 2310.

According to some embodiments of the present invention, a lock fitting (not shown) is also provided on the second wing section 22. When the second wing segment 22 is connected to the fixing portion 231, the fixing portion 231 is locked with the lock fitting on the second wing segment 22, and the lock fitting can also provide a supporting force for the second wing segment 22, so as to enhance the connection strength between the second wing segment 22 and the fixing member 23.

The second end of the second wing section 22 is configured as a wingtip winglet. An included angle is formed between the winglet and the second wing section 22 to block the air circumfluence on the upper and lower surfaces of the second wing section 22 and reduce the damage of the circumfluence on the lift force.

An aileron 24 is also provided at the trailing edge of the second panel 22. The ailerons 24 can be flipped up and down relative to the fixed wings 20 and the fuselage 10 to achieve control of the flight attitude of the unmanned aerial vehicle 100. The flap 24 includes opposing upper and lower surfaces, the upper surface of the flap 24 being substantially flush with the top surface of the second section 22 and the lower surface of the flap 24 being substantially flush with the bottom surface of the second section 22.

In some embodiments of the present invention, a steering engine is provided in the first wing section 21 to control the wing surface of the aileron 24, so that the flight direction of the unmanned aerial vehicle 100 can be controlled. Specifically, the steering gear is disposed on the first wing segment 21 or the fixing portion 231, and an output shaft of the steering gear penetrates out along a side wall of the fixing portion 231 and is connected with the aileron 24 through the connecting assembly 25 to drive the aileron 24 to rotate.

In some embodiments of the present invention, as shown in fig. 1, the unmanned aerial vehicle 100 further comprises a first power assembly 30, a second power assembly 40, a tail 50, and an aerial photography module 70.

Specifically, as shown in fig. 1, a first power assembly 30 is disposed on the first wing section 21, and is used for providing the vertical take-off and landing flight power for the unmanned aerial vehicle 100, so that the unmanned aerial vehicle 100 can be vertically taken off and landed. Specifically, the first power assembly 30 includes a wing arm 31 connected to the first wing section 21, a first power unit 32 connected to the wing arm 31, and a first propeller 33 connected to the first power unit 32. The two wing arms 31 are respectively symmetrically arranged at two sides of the fuselage 10, and the axial directions of the two wing arms 31 are consistent with the direction from the nose to the tail of the unmanned aerial vehicle 100.

Specifically, the fixing member 23 further includes a hanging portion 232, and the hanging portion 232 extends downward along the fixing portion 231. The hanging portion 232 is formed in a ring shape and has an annular hole 2320 formed therein. The wing arm 31 is inserted into the annular hole 2320 of the suspension portion 232. The first power units 32 include four, and the four first power units 32 are respectively fixed at end positions of the two wing arms 31.

Further, a cable channel (not shown) is provided in the wing arm 31 for receiving a cable connected between the first power unit 32 and the first wing section 21, so as to supply power to the first power unit 32 through a circuit in the first wing section 21. In addition, the cable also includes a communication cable, and the connection of the communication cable enables the main body 10 to acquire information such as the rotation speed of the propeller.

As shown in fig. 1, the second power assembly 40 includes a fixing base 41, a second power unit 42 disposed on the fixing base 41, and a second propeller 43 connected to the second power unit 42, wherein the fixing base 41 is a casing with a pillar shape as a whole to fit the shape of the fuselage housing 12. An installation cavity is formed in the fixing seat 41, and an electric adjusting device for adjusting the second power unit 42 can be arranged in the installation cavity. The fixing base 41 is adapted to be fixed to the second rear end wall of the second fixed frame 12.

As shown in fig. 1 and 2, the tail wing 50 includes two tail wings 51 arranged in an inverted V shape, and the two tail wings 51 are pivotally connected to each other, that is, the two tail wings 51 can be folded with each other. The storage space of the rear wing 50 can be reduced when the rear wing 50 is detached. The rear edge of the tail wing plate 51 is provided with a movable control surface, and the inverted V-shaped tail wing has the functions of a vertical tail and a horizontal tail of a common fixed wing, so that the structure weight is small, and the control efficiency is high; of course, in other embodiments, the tail 50 may be a double-droop tail or other tail configuration.

In some embodiments of the present invention, the tail fin 50 is fixedly connected to the rear end of the wing arm 31 through the tail stay 53 and the tail stay seat 54, specifically, the tail stay 53 includes two, two tail stays 53 are respectively disposed at the rear end of the wing arm 31 and coaxially disposed with the wing arm 31, and the two tail stays 53 are pivotally connected to the rear end of the wing arm 31 through the pivot structure 55. A tail stay seat 54 is attached to the end of the tail stay 53 remote from the fuselage 10.

Optionally, the aerial photography module 70 is disposed at a front position of the body 10 and is fixedly connected to the first fixed frame 11.

According to the utility model discloses unmanned vehicles 100. The unmanned aerial vehicle 100 can take off and land at zero speed, has hovering capability, has high horizontal flying speed, and can fly horizontally in a fixed-wing flying manner. The unmanned aerial vehicle 100 can be used in the fields of aerial photography and surveying and mapping, power inspection, environmental monitoring, disaster patrol and the like.

According to the utility model discloses unmanned vehicles 100, through utilizing according to the utility model discloses unmanned vehicles's fuselage 10 of above-mentioned embodiment, when using, antenna 92 is established on lower cover 16, is not only convenient for carry out the communication between antenna 92 and the ground terminal and is connected, and antenna 92 can together pull down with lower cover 16 in addition, is convenient for maintain and change antenna 92 to improve unmanned vehicles 100's operational reliability.

Other configurations and operations of the unmanned aerial vehicle 100 according to embodiments of the present invention are known to those of ordinary skill in the art and will not be described in detail herein.

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, the first feature "on" or "under" the second feature may include the first and second features being in direct contact, and may also include the first and second features being in contact with each other not directly but through another feature therebetween.

In the description of the invention, the first feature being "on", "above" and "above" the second feature includes the first feature being directly above and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature.

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

1. A fuselage for an unmanned aerial vehicle, comprising:

the fuselage structure comprises a fuselage frame and a fuselage shell, wherein the fuselage shell is wrapped on the fuselage frame, an installation space is arranged in the fuselage frame, and an installation opening is formed in the bottom wall of the installation space;

the lower cover is detachably arranged at the mounting opening to open or close the mounting opening;

the communication module comprises an antenna, and the antenna is arranged on the lower cover and positioned on the inner side of the mounting opening.

2. The fuselage of the UAV of claim 1 wherein the fuselage shell has a plane of symmetry, the fuselage shell being bilaterally symmetric about the plane of symmetry, the plurality of antennas being distributed on both the left and right sides of the plane of symmetry.

3. The fuselage of the unmanned aerial vehicle of claim 1, wherein the lower cover is provided with a downwardly extending supporting foot, the supporting foot is internally provided with a containing cavity, and at least a part of the antenna is arranged in the containing cavity.

4. The fuselage of the unmanned aerial vehicle of claim 3, wherein the two supporting foot frames are arranged symmetrically left and right, the accommodating cavity is arranged in each supporting foot frame, and the antenna is arranged in each accommodating cavity.

5. The fuselage of claim 3, wherein the antenna within the receiving cavity is vertically oriented.

6. The fuselage of claim 3, wherein the inner wall of the lower cover has a receiving groove at the rear side of the supporting foot, and a part of the antenna is placed in the receiving groove.

7. The fuselage of an unmanned aerial vehicle according to any one of claims 1 to 6, wherein the communication module further comprises a data transmission module, the antenna being electrically connected to the data transmission module, the data transmission module being mounted on the lower cover inside the mounting opening.

8. The fuselage of the UAV of claim 7, wherein the lower cover comprises:

the base cover is detachably arranged on the machine body frame;

the heat dissipation piece is arranged on the inner wall of the base cover, the data transmission module is installed on the heat dissipation piece, and the base cover is provided with heat dissipation holes used for dissipating heat of the heat dissipation piece.

9. The airframe of claim 8, wherein the heat sink comprises a heat sink base plate and heat sink fins, the heat sink fins are disposed on the heat sink base plate and extend out of the base cover through the heat sink holes, and the data transmission module is mounted on an inner wall of the heat sink base plate.

10. The fuselage of an unmanned aerial vehicle as defined in claim 8, wherein a layer of thermally conductive adhesive is disposed between the heat sink and the data transmission module.

11. An unmanned aerial vehicle, comprising:

a fuselage according to any one of claims 1-10;

the two fixed wings are symmetrically arranged on the opposite side walls of the machine body.

12. The unmanned aerial vehicle of claim 11, wherein each of the stationary vanes comprises a strut fixed to the fuselage frame and an airfoil coated on an outer side of the strut, the airfoil being a lightweight piece of material.