CN112278228A

CN112278228A - Unmanned vehicles's fuselage and unmanned vehicles who has it

Info

Publication number: CN112278228A
Application number: CN201910673146.5A
Authority: CN
Inventors: 梁杰; 肖锭锋
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: 2021-01-29

Abstract

The invention discloses a fuselage of an unmanned aerial vehicle and the unmanned aerial vehicle with the fuselage, wherein the fuselage of the unmanned aerial vehicle comprises: the machine body frame comprises a first fixing frame and a second fixing frame, a first accommodating cavity is formed in the first fixing frame, a second accommodating cavity is formed in the second fixing frame, and the first fixing frame and the second fixing frame are connected in parallel in the length direction of the machine body; the lower cover is arranged on the bottom wall of the machine body frame, and a wiring space is defined among the bottom wall of the second fixing frame, the side wall of the first fixing frame and the lower cover; the first electronic element is arranged at the top of the second fixing frame; the second electronic element is arranged in the second accommodating cavity and is positioned below the first electronic element; and the third electronic element is arranged on the lower cover and is positioned below the second electronic element. When the electronic component mounting device is used, the electronic components can be conveniently mounted and arranged, the assembly efficiency of the machine body is improved, and sufficient operation space and accommodating space are reserved for connecting terminals among the electronic components.

Description

Unmanned vehicles's fuselage and unmanned vehicles who has it

Technical Field

The invention relates to the field of flight, in particular to a fuselage of an unmanned aerial vehicle and the unmanned aerial vehicle with the fuselage of the unmanned aerial vehicle.

Background

Because contain in unmanned vehicles's the fuselage and realize various functions's of unmanned vehicles multiple equipment and wiring, the unmanned vehicles of correlation technique, its structural design, overall arrangement are unreasonable, lead to the equipment of each overall arrangement in the fuselage to appear mutual interference easily, perhaps the function of partial equipment is limited, influences unmanned aerial vehicle's complete machine performance, influences unmanned aerial vehicle's functionality and suitability, can't deal with diversified user demand.

Disclosure of Invention

The present invention is directed to solving at least one of the problems of the prior art. Therefore, the fuselage of the unmanned aerial vehicle is provided with the first fixing frame, the second fixing frame and the lower cover, and a wiring space is defined among the bottom wall of the second fixing frame, the side wall of the first fixing frame and the lower cover, so that the installation and the arrangement of all electronic elements are facilitated, the assembly efficiency of the fuselage is improved, the assembly time of the fuselage is shortened, and sufficient operation space and accommodating space are reserved for connecting line terminals among all electronic elements.

The invention also provides the unmanned aerial vehicle with the fuselage of the unmanned aerial vehicle.

To achieve the above object, an embodiment according to a first aspect of the present invention proposes a fuselage of an unmanned aerial vehicle, comprising: the fuselage frame comprises a first fixed frame and a second fixed frame, a first accommodating cavity is formed in the first fixed frame, a second accommodating cavity is formed in the second fixed frame, the first fixed frame and the second fixed frame are connected in parallel in the length direction of the fuselage, and the height of at least one part of the bottom wall of the second fixed frame is greater than that of the bottom wall of the first fixed frame in the height direction of the fuselage; the lower cover is arranged on the bottom wall of the machine body frame, and a wiring space is defined among the bottom wall of the second fixing frame, the side wall of the first fixing frame and the lower cover; the first electronic element is arranged at the top of the second fixing frame; the second electronic element is arranged in the second accommodating cavity and is positioned below the first electronic element; and the third electronic element is arranged on the lower cover and is positioned below the second electronic element.

According to the fuselage of the unmanned aerial vehicle, due to the arrangement of the first fixing frame, the second fixing frame and the lower cover, the wiring space is defined among the bottom wall of the second fixing frame, the side wall of the first fixing frame and the lower cover, so that the installation and arrangement of the first electronic element, the second electronic element and the third electronic element are facilitated, the assembly efficiency of the fuselage is improved, the assembly time of the fuselage is shortened, and sufficient operation space and accommodating space are reserved for connecting line terminals among the electronic elements.

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

further, the top wall of the second fixing frame is provided with a through hole, and a part of the first electronic element penetrates through the through hole and extends out of the second fixing frame.

Further, the bottom wall of the second fixing frame is provided with an installation opening, and the second electronic element is installed in the second storage cavity through the installation opening.

Further, first fixed frame is established the front side of the fixed frame of second, the fuselage still includes power storage device, the top of first fixed frame is equipped with dismantles the mouth, power storage device passes through it establishes to dismantle a mouthful detachably first intracavity of accomodating.

Furthermore, the first electronic component is a positioning module, the second electronic component is a flight control unit, and the third electronic component is a communication module.

Furthermore, the flight control unit comprises a main board and an inertia measurement unit arranged on the main board, and the main board is fixed in the second accommodating cavity and positioned below the positioning module.

Further, the third electronic component includes a data transmission module, and the lower cover includes: the base cover is detachably arranged on the machine body frame and is provided with heat dissipation holes; 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, the third electronic component further includes an antenna mounted on the lower cover.

Embodiments according to the second aspect of the present invention provide an unmanned aerial vehicle comprising a fuselage of the unmanned aerial vehicle according to embodiments of the first aspect of the present invention and two fixed wings symmetrically arranged on opposite side walls of the fuselage.

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.

Further, the second fixing frame is provided with a mounting hole, and the support rod is arranged in the mounting hole in a penetrating mode.

According to the unmanned aerial vehicle provided by the embodiment of the invention, by utilizing the fuselage of the unmanned aerial vehicle provided by the embodiment of the first aspect of the invention and by arranging the first fixing frame, the second fixing frame and the lower cover, the wiring space is defined among the bottom wall of the second fixing frame, the side wall of the first fixing frame and the lower cover, so that the installation and arrangement of the first electronic element, the second electronic element and the third electronic element are facilitated, the assembly efficiency of the fuselage is improved, the assembly time of the fuselage is shortened, and sufficient operation space and accommodating space are reserved for connecting line terminals among the electronic elements.

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 view 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 partial structural schematic view of a fuselage of an unmanned aerial vehicle according to an embodiment of the 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 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 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 third electronic component of a fuselage of an unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 8 is a schematic structural view 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 view 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 first electronic component 114,

A second electronic component 80, a main board 81, an inertia measurement unit 82, a trace space 83,

A third electronic component 90, a data transmission module 91, an antenna 92,

The fixed wing 20, the strut 211, the wing surface 212, the first wing section 21, the second wing section 22, the fixing piece 23, the fixing portion 231, the guide hole 2310, the hanging portion 232, the annular hole 2320, the guide rod 221, the aileron 24, the first power assembly 30, the wing arm 31, the first power unit 32, the first propeller 33, the second power assembly 40, the fixing seat 41, the second power unit 42, the second propeller 43, the empennage 50, the tail wing plate 51, the tail brace rod 53, the tail brace seat 54, the pivot structure 55, the aerial photography module 70, the fuselage shell 14 and the first mounting port 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 or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.

The fuselage 10 according to an embodiment of the invention is described below with reference to the drawings.

As shown in fig. 1 to 10, the body 10 according to the embodiment of the present invention includes a body frame 111, a lower cover 16, a first electronic component 114, a second electronic component 80, and a third electronic component 90.

The body frame 111 includes a first fixed frame 11 and a second fixed frame 12, a first storage chamber 110 is provided in the first fixed frame 11, a second storage chamber 120 is provided in the second fixed frame 12, the first fixed frame 11 and the second fixed frame 12 are connected in parallel in the longitudinal direction of the body 10, and the height of at least a part of the bottom wall of the second fixed frame 12 is greater than the height of the bottom wall of the first fixed frame 11 in the height direction of the body 10 (the vertical direction is indicated by an arrow a in fig. 3). The lower cover 16 is provided at a bottom wall of the body frame 111, and a routing space 83 is defined between the bottom wall of the second fixing frame 12, a side wall of the first fixing frame 11, and the lower cover 16. The first electronic component 114 is provided on top of the second fixed frame 12. The second electronic component 80 is disposed in the second receiving cavity 120 and located below the first electronic component 114. The third electronic component 90 is disposed on the lower cover 16 and below the second electronic component 80.

According to the main body 10 of the embodiment of the invention, the first fixing frame 11, the second fixing frame 12 and the lower cover 16 are arranged, so that the first electronic component 114, the second electronic component 80 and the third electronic component 90 are conveniently positioned, and the first electronic component 114, the second electronic component 80 and the third electronic component 90 are conveniently arranged, so that the assembly efficiency of the main body 10 is improved, and the assembly time of the main body 10 is shortened.

Moreover, by arranging the routing space 83, it is convenient to reserve sufficient operation space and accommodating space for the connection terminal among the first electronic element 114, the second electronic element 80, and the third electronic element 90, so that the assembly and the molding of the unmanned aerial vehicle 100 are facilitated, the operation of a user is facilitated, and the assembly convenience of the unmanned aerial vehicle 100 is improved.

In addition, the third electronic component 90 is provided on the lower cover 16, which not only facilitates the removal and installation of the structure inside the body 10, but also facilitates the removal of the third electronic component 90 together with the lower cover 16 for the maintenance and replacement of the third electronic component 90.

Therefore, according to the main body 10 of the embodiment of the present invention, by providing the first fixing frame 11, the second fixing frame 12 and the lower cover 16, and defining the wiring space 83 between the bottom wall of the second fixing frame 12, the side wall of the first fixing frame 11 and the lower cover 16, it is not only convenient to install the first electronic component 114, the second electronic component 80 and the third electronic component 90, improve the assembly efficiency of the main body 10, shorten the assembly time of the main body 10, but also convenient to reserve sufficient operation space and accommodating space for the connecting line terminals between the electronic components.

In some embodiments of the present invention, as shown in fig. 1 to 10, the body 10 according to the embodiment of the present invention includes a body frame 111, a lower cover 16, a first electronic component 114, a second electronic component 80, and a third electronic component 90.

Further, as shown in fig. 6, the top wall of the second fixing frame 12 is provided with a through hole through which a part of the first electronic component 114 protrudes out of the second fixing frame 12. This facilitates a part of the first electronic component 114 to be located above the second fixed frame 12, for example, when the first electronic component 114 is a positioning module, the first electronic component 114 can smoothly position the unmanned aerial vehicle 100, and the positioning accuracy and reliability of the first electronic component 114 can be improved.

Specifically, as shown in fig. 6, the bottom wall of the second fixing frame 12 is provided with a mounting opening 113, and the second electronic component 80 is mounted in the second receiving cavity 120 through the mounting opening 113. This facilitates the installation of the second electronic component 80 into the second receiving cavity 120, further improving the assembly efficiency of the body 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 an arrow B in fig. 3), the body 10 further includes the power storage device 60, the top of the first fixed frame 11 is provided with a detachment port 112, and the power 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.

Optionally, the first electronic component 114 is a positioning module, the second electronic component 80 is a flight control unit, and the third electronic component 90 is a communication module. Therefore, the positioning module can conveniently position the unmanned aerial vehicle 100, the positioning function of the positioning module is enhanced, the positioning accuracy and precision of the positioning module are improved, and the working reliability and stability of the positioning module are improved, so that the flying position of the unmanned aerial vehicle 100 can be determined quickly and accurately.

Moreover, the communication connection between the communication module and the ground terminal is facilitated, electromagnetic interference caused by other structures in the body 10 to the communication module is avoided, the communication effect of the communication module is improved, the ground terminal is facilitated to control the unmanned aerial vehicle 100, and the control reliability of the unmanned aerial vehicle 100 is improved.

Further, the flight control unit includes a main board 81 and an inertia measurement unit 82 disposed on the main board 81, and the main board 81 is fixed in the second receiving cavity 120 and located below the positioning module. Therefore, the main board 81 is convenient to connect with the positioning module, the power storage device 60, the main board 81 and the positioning module are convenient to electrically connect, the wiring structure in the machine body 10 is simplified, and the layout in the machine body 10 is more reasonable and compact.

According to some embodiments of the present invention, the second electronic component 80 includes a main board 81 and an inertia measurement unit 82 disposed on the main board 81, the main board 81 is fixed in the second receiving cavity 120 and located below the first electronic component 114, the first electronic component 114 is electrically connected to the main board 81, the third electronic component 90 is electrically connected to the main board 81, and the power storage device 60 is connected to the main board 81 to supply power to the second electronic component 80. Therefore, the power storage device 60 supplies power to the first electronic component 114 and the third electronic component 90 through the main board 81, and the power storage device 60, the main board 81, the first electronic component 114, the second electronic component 80 and the third electronic component 90 are electrically connected, so that the wiring structure in the body 10 is simplified, and the layout in the body 10 is more reasonable and compact.

It should be understood herein that "the first electronic component 114 is electrically connected to the main board 81" and "the third electronic component 90 is electrically connected to the main board 81" may be respectively in communication and/or electrical connection.

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.

According to other embodiments of the present invention, the main body 10 includes a first electronic component 114, a second electronic component 80, a third electronic component 90, and a main board 81, and the first electronic component 114, the second electronic component 80, and the third electronic component 90 are electrically connected to the main board 81, respectively.

In some embodiments of the 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 invention, as shown in fig. 6, second fixed frame 12 comprises 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 first electronic component 114 is adapted to be accommodated in the second accommodating cavity 120 and fixed to the inner side of the top wall 1203, and a portion of the first electronic component 114 penetrates through the second accommodating 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, the lower cover 16 is detachably provided on the body frame 111 to open or close the mounting opening 113, and the third electronic component 90 is mounted on the lower cover 16 inside the mounting opening 113. This not only facilitates removal and installation of the structure within the body 10, but also allows the third electronic component 90 to be removed along with the lower cover 16, facilitating maintenance and replacement of the third electronic component 90.

Specifically, as shown in fig. 7, the third electronic component 90 includes a data transmission module 91, the data transmission module 91 is located below the second electronic component 80, and the data transmission module 91 is electrically connected to the main board 81. The lower cover 16 includes a base cover 161 and a heat sink 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 third electronic component 90 further includes an antenna 92, the antenna 92 is mounted on the lower cover 16, and the antenna 92 is electrically connected to the data transmission module 91. Therefore, the antenna 92 is conveniently powered, the antenna 92 is conveniently in communication connection with the ground terminal, and the accuracy and 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 receiving cavity 16110 is disposed inside the supporting foot 1611, and at least a portion of the antenna 92 is disposed inside the receiving 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 covers 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 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, wherein the number of the antennas 92 is 4, and the antennas 92 may be patch antennas or rod antennas.

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 first electronic component 114 passes through the second receiving cavity 120 along the through hole; then, the second electronic component 80 is accommodated in the second accommodating cavity 120 and fixed to the inner wall of the second accommodating cavity 120 by 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 air drag in 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 image module 70, the second electronic component 80, the first electronic component 114, and the third electronic component 90 may be provided in the electrical installation portion.

In some embodiments of the invention, the first electronic component 114 is disposed in the second receiving cavity 120, such that the first electronic component 114 passes through the second receiving cavity 120 along the through hole and is located at the top end of the main body 10. The positioning function of the first electronic component 114 is greatly enhanced. Second electronic component 80 penetrates second accommodating cavity 120 along the opening at the lower end of second accommodating cavity 120 and is fixed, so that the assembly, disassembly and maintenance are easy, and unmanned aerial vehicle 100 is reasonable in layout. The data transmission module 91 of the third electronic component 90 is fixed on the heat dissipation housing 162, the heat dissipation fins 1622 are disposed on the outer surface of the heat dissipation housing 162, so that heat generated during the operation of the data transmission module 91 can be conducted out of the main body 10, and then the heat dissipation housing 162 fixed with the data transmission module 91 is fixed on the base cover 161, thereby forming the lower cover 16 assembly composed of the heat dissipation housing 162 and the base cover 161. 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 fixing 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 second electronic element 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. The unmanned aerial vehicle 100 according to the embodiment of the present invention includes a fuselage 10 and two fixed wings 20, the fuselage 10 is the fuselage 10 of the unmanned aerial vehicle according to the above-described embodiment of the present invention, and the two fixed wings 20 are symmetrically disposed on opposite sidewalls of the 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 segment 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 UAV 100 further includes a first power assembly 30, a second power assembly 40, a tail wing 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 portion of the wing arm 31 through a tail stay 53 and a tail stay seat 54, specifically, the tail stay 53 includes two tail stays 53, two tail stays 53 are respectively disposed at the rear end of the wing arm 31 and are coaxially disposed with the wing arm 31, and the two tail stays 53 are pivotally connected to the rear end portion of the wing arm 31 through a 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.

The unmanned aerial vehicle 100 according to an embodiment of the present invention. 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 unmanned aerial vehicle 100 of the embodiment of the invention, by using the body 10 of the unmanned aerial vehicle according to the above-described embodiment of the invention, by providing the first fixed frame 11, the second fixed frame 12, and the lower cover 16, the routing space 83 is defined between the bottom wall of the second fixed frame 12, the side wall of the first fixed frame 11, and the lower cover 16, not only is the installation and installation of the first electronic component 114, the second electronic component 80, and the third electronic component 90 facilitated, the assembly efficiency of the body 10 is improved, the assembly time of the body 10 is shortened, but also it is facilitated to reserve sufficient operating space and accommodating space for the connecting line terminals between the electronic components.

Other configurations and operations of the UAV 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 "central," "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 are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the 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 being "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, "above", "over" and "above" a first feature in a second feature includes the first feature being directly above and obliquely above the second feature, or simply means that the first feature is higher in level than the second feature.

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; 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 meanings 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 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 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 frame comprises a first fixed frame and a second fixed frame, a first accommodating cavity is formed in the first fixed frame, a second accommodating cavity is formed in the second fixed frame, the first fixed frame and the second fixed frame are connected in parallel in the length direction of the fuselage, and the height of at least one part of the bottom wall of the second fixed frame is greater than that of the bottom wall of the first fixed frame in the height direction of the fuselage;

the lower cover is arranged on the bottom wall of the machine body frame, and a wiring space is defined among the bottom wall of the second fixing frame, the side wall of the first fixing frame and the lower cover;

the first electronic element is arranged at the top of the second fixing frame;

the second electronic element is arranged in the second accommodating cavity and is positioned below the first electronic element;

and the third electronic element is arranged on the lower cover and is positioned below the second electronic element.

2. The fuselage of the unmanned aerial vehicle of claim 1, wherein a top wall of the second fixed frame is provided with a through hole through which a portion of the first electronic component protrudes out of the second fixed frame.

3. The fuselage of the unmanned aerial vehicle of claim 1, wherein a bottom wall of the second fixed frame is provided with a mounting opening through which the second electronic component is mounted in the second receiving cavity.

4. The unmanned aerial vehicle fuselage of claim 1, characterized in that the first fixed frame is established at the front side of the second fixed frame, the fuselage still includes power storage device, the top of first fixed frame is equipped with dismantles the mouth, power storage device passes through dismantle mouthful detachably establish in the first storage cavity.

5. The fuselage of claim 1, wherein the first electronic component is a positioning module, the second electronic component is a flight control unit, and the third electronic component is a communication module.

6. The fuselage of claim 5, wherein the flight control unit comprises a main board and an inertial measurement unit provided on the main board, the main board being fixed in the second receiving cavity and located below the positioning module.

7. The fuselage of the UAV of claim 5, wherein the third electronic component comprises a data transmission module, and wherein the lower cover comprises:

the base cover is detachably arranged on the machine body frame and is provided with heat dissipation holes;

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.

8. The airframe of claim 7, wherein the heat sink includes 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.

9. The fuselage of the UAV of claim 7 wherein the third electronic component further comprises an antenna mounted on the lower cover.

10. An unmanned aerial vehicle, comprising:

a fuselage according to any one of claims 1-9;

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

11. The unmanned aerial vehicle of claim 10, 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.

12. The unmanned aerial vehicle of claim 11, wherein the second fixed frame is provided with a mounting hole, and the strut is arranged in the mounting hole in a penetrating manner.