Aircraft

Abstract

The present invention discloses an aircraft. The aircraft includes a fuselage, a fixed wing, a wing arm, a second power assembly and a first electric adjustment assembly. A control circuit is arranged in the fuselage. The fixed wing includes a first section and a second section connected to the first section, and the first section is connected to the fuselage. The wing arm is connected to the first section, and the wing arm extends along the length direction of the fuselage, and the first power assembly is arranged at both ends of the wing arm. The second power assembly is arranged on the fuselage. The first electric adjustment assembly is connected to the first section, and the first electric adjustment assembly is communicatively connected to the control circuit, and the first electric adjustment assembly can adjust the power size of the first power assembly. According to the aircraft of the present invention, by setting the first electric adjustment assembly to be connected to the first section, the layout of the aircraft can be optimized, the probability of interference between the first electric adjustment assembly and other components on the fuselage can be reduced, and the heat dissipation of the first electric adjustment assembly can be facilitated, thereby extending the service life of the first electric adjustment assembly.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to an aircraft. Background Art

[0002] With the development of society, the application areas of unmanned aerial vehicles are constantly expanding. Both industrial and consumer aircraft have made great progress, especially small unmanned aerial vehicles represented by multi-propeller unmanned aerial vehicles and fixed-wing unmanned aerial vehicles, which have been widely used in various application fields, such as aerial photography, surveying and mapping.

[0003] In the related art, the unmanned aerial vehicle is provided with an electric adjustment component for controlling the speed of the power motor. However, due to the unreasonable design of the position of the electric adjustment component, the heat dissipation effect of the electric adjustment component is poor and the service life is short. Summary of the invention

[0004] The present invention provides an aircraft, wherein the electric adjustment components of the aircraft are reasonably arranged and have good heat dissipation effect.

[0005] According to an embodiment of the present invention, the aircraft comprises a fuselage, a fixed wing, a wing arm and a first electric adjustment component. The fuselage is provided with a control circuit; the fixed wing comprises a first section and a second section connected to the first section, the first section is connected to the fuselage; the wing arm is connected to the first section, the wing arm extends along the length direction of the fuselage, and both ends of the wing arm are provided with a first power component; the first electric adjustment component is connected to the first section, the first electric adjustment component is in communication connection with the control circuit, and the first electric adjustment component can adjust the power of the first power component.

[0006] According to the aircraft of the embodiment of the present invention, by setting the first electric adjustment component to be connected to the first section, on the one hand, the layout of the aircraft can be optimized, the probability of interference between the first electric adjustment component and other components on the fuselage can be reduced, and the probability of the heat generated by the first electric adjustment component having an adverse effect on the operation of the components (such as power supply, control device) arranged on the fuselage can be reduced, which is conducive to extending the service life of the components (such as power supply, control device) arranged on the fuselage. On the other hand, the heat dissipation of the first electric adjustment component is facilitated, thereby extending the service life of the first electric adjustment group.

[0007] In some embodiments, the fixed wing has a first installation cavity, and the first installation cavity is provided at a connection position between the first section and the second section, and the first electrical adjustment component is provided in the first installation cavity.

[0008] In some embodiments, the fixed wing has a first connecting member, the first connecting member is connected to the end of the first section facing the second section, the first connecting member has a first groove, and the first groove is open toward the second section;

[0009] The second connecting member is connected to the end of the second section facing the first section, the second connecting member has a second groove, the second groove is open toward the first connecting member, and the second connecting member is connected to the second connecting member to define the first installation cavity.

[0010] In some embodiments, the aircraft further includes an aileron, wherein the aileron is connected to the fixed wing and is flippable relative to the fixed wing; the aircraft includes a driving member for driving the aileron to flip, wherein the driving member is disposed in the first mounting cavity; the aileron is connected to the second section and is flippable relative to the second section; and the driving member is connected to the first connecting member.

[0011] In some embodiments, a wire hole is provided at the first connecting member, and a connecting line between the control circuit and the first electrical adjustment component is passed through the wire hole.

[0012] In some embodiments, the fuselage has a connecting rod, the connecting rod is passed through the first section, the first connecting member has a first groove, the first connecting member has a first through-hole, the connecting rod is passed through the first through-hole, a portion of the connecting rod is located in the first groove, the second connecting member has a second groove, the second groove is opposite to the first groove and jointly defines the first installation cavity, the second connecting member has a second through-hole, and the portion of the connecting rod passing through the first through-hole is plugged into the second through-hole.

[0013] In some embodiments, the first section is detachably connected to the first connector; and the second section is detachably connected to the second connector.

[0014] In some embodiments, one of the first connecting member and the second connecting member has a locking foot, and the other has a locking groove matched with the locking foot.

[0015] In some embodiments, the wing arm is passed through the first mounting cavity; the control circuit is electrically connected to the first electric adjustment component through a first wire, and the first wire is passed through the first section; the first electric adjustment component is electrically connected to the first power component through a second wire, and the second wire is passed through the wing arm.

[0016] In some embodiments, the aircraft further includes a second power assembly, and the second power assembly is disposed on the fuselage.

[0017] In some embodiments, the aircraft includes a second electric adjustment component for adjusting the power of a second power component, and the second electric adjustment component is communicatively connected to the control circuit; the second power component includes: a fixed seat, the fixed seat is connected to the fuselage, the fixed seat and the fuselage define a second installation cavity, and the second electric adjustment component is arranged in the second installation cavity; a propeller, the propeller is connected to the fixed seat.

[0018] In some embodiments, the first section is detachably connected to the second section.

[0019] In some embodiments, the fuselage is provided with a connecting rod, the free end of the connecting rod has a plug hole, the connecting rod extends toward the second section, the connecting rod is passed through the first section, the second section has a plug column, and the plug column is passed through the plug hole. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The above and / or additional aspects and advantages of the present invention will become apparent and easily understood from the description of the embodiments in conjunction with the following drawings, in which:

[0021] Figure 1 is a schematic structural diagram of an aircraft according to an embodiment of the present invention;

[0022] Figure 2 yes Figure 1 Enlarged view of part A in the middle;

[0023] Figure 3 is a schematic structural diagram of an aircraft according to an embodiment of the present invention;

[0024] Figure 4 yes Figure 3 Enlarged view of part B;

[0025] Figure 5 is a schematic structural diagram of a second connecting member of an aircraft according to an embodiment of the present invention;

[0026] Figure 6 is a schematic structural diagram of a first connecting member of an aircraft according to an embodiment of the present invention;

[0027] Figure 7 is a schematic structural diagram of a first connecting member of an aircraft according to an embodiment of the present invention;

[0028] Figure 8 is an exploded view of a second power assembly of an aircraft according to an embodiment of the present invention;

[0029] Fig. 9 is a schematic diagram of a partial structure of an aircraft according to an embodiment of the present invention;

[0030] Fig.10 is a schematic structural diagram of an aircraft according to an embodiment of the present invention;

[0031] Fig.11 is a schematic structural diagram of an aircraft according to an embodiment of the present invention;

[0032] Fig.12 yes Fig.11 Enlarged view of part C.

[0033] Reference numerals:

[0034] Aircraft 100;

[0035] Fuselage 110; second power assembly 111; fixing seat 1111; propeller 1112; second installation cavity 1113;

[0036] Fixed wing 120; first section 121; first through hole 1212; first installation cavity 1213; wire hole 1214; second section 122; plug-in column 1221; second through hole 1222; button portion 1223; hook 1224; connecting rod 123; plug-in hole 1231; aileron 125;

[0037] First connecting member 126; first groove 1261, engaging groove 1262; second connecting member 127; second groove 1271; engaging hole 1273, engaging foot 1274;

[0038] Wing arm 130; first power assembly 131;

[0039] A first electric adjustment component 140 ; ​​a first fixing frame 150 ; a second fixing frame 160 ; a tail 170 ; a second electric adjustment component 180 ; and a driving member 190 . DETAILED DESCRIPTION

[0040] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0041] In the description of the present invention, it should be understood that the terms "front", "rear", "left", "right", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific position, be constructed and operated in a specific position, and therefore cannot be understood as limiting the present invention. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0042] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0043] Reference below Figure 1-Figure 12 An aircraft 100 is described according to an embodiment of the present invention.

[0044] like Figure 1-Figure 12 As shown, an aircraft 100 according to an embodiment of the present invention includes a fuselage 110 , fixed wings 120 , wing arms 130 and a first electrical adjustment assembly 140 .

[0045] Specifically, a control circuit is disposed in the body 110. Figure 3 As shown, the fixed wing 120 may include a first section 121 and a second section 122 that can be detachably connected to the first section 121, and the first section 121 may be connected to the fuselage 110. The wing arm 130 may be connected to the first section 121, and the wing arm 130 extends along the length direction of the fuselage 110, and the first power assembly 131 may be provided at both ends of the wing arm 130. Figure 1 , Figure 2 As shown, the first electric adjustment component 140 can be arranged in the first section 121, the first electric adjustment component 140 can adjust the power of the first power component 131, and the first electric adjustment component 140 can be connected to the control circuit for communication. It should be noted that when the power of the first power component 131 needs to be adjusted, the control circuit can issue a command to the first electric adjustment component 140.

[0046] For example, Figure 3 As shown, the left side of the fuselage 110 (such as Figure 3 The left side of the fixed wing 120 is provided, and the right end of the first section 121 of the fixed wing 120 (as shown in FIG. Figure 3 The right side of the fuselage 110 is connected to the fuselage 110, and the left end of the first section 121 is provided with a second section 122, and the second section 122 is connected to the first section 121. The right side of the fuselage 110 may also be provided with a fixed wing 120, and the left end of the first section 121 of the fixed wing 120 is connected to the fuselage 110, and the right end of the first section 121 is provided with a second section 122, and the second section 122 is connected to the first section 121.

[0047] like Figure 3 As shown, the left and right sides of the fuselage 110 (such as Figure 3In the left and right directions (as shown in FIG. 1 ), each wing arm 130 is provided. That is, a wing arm 130 is provided on the left side of the fuselage 110 and a wing arm 130 is provided on the right side of the fuselage 110. Both wing arms 130 can be extended in the front-to-back direction (as shown in FIG. Figure 3 The wing arm 130 located on the left side of the fuselage 110 may be connected to the first section 121 located on the left side of the fuselage 110, and the wing arm 130 located on the right side of the fuselage 110 may be connected to the first section 121 located on the right side of the fuselage 110. Figure 3 As shown, a first power assembly 131 may be provided at the front end of each wing arm 130 , and a first power assembly 131 may also be provided at the rear end of each wing arm 130 .

[0048] like Figure 1 , Figure 2 As shown, it is located on the right side of the fuselage 110 (such as Figure 1 The first section 121 (as shown in the right side) is connected to a first electric tilting assembly 140, and the first electric tilting assembly 140 is used to adjust the front and rear ends of the wing arm 130 (as shown in the right side) to adjust the front and rear ends of the wing arm 130 (as shown in the right side). Figure 1 The first electric tilting assembly 140 may have two output ends, wherein the output end at the front end of the first electric tilting assembly 140 may adjust the power of the first power assembly 131 disposed at the front end of the wing arm 130; and the output end at the rear end of the first electric tilting assembly 140 may adjust the power of the first power assembly 131 disposed at the rear end of the wing arm 130.

[0049] It should be noted that if Fig. 9 As shown, the power supply and control devices of the aircraft 100 are mostly distributed in the fuselage 110. Considering that the layout space of the fuselage 110 is limited and the components are closely connected, the first electric tilt assembly 140 can be arranged on the first section 121, that is, the first electric tilt assembly 140 is connected to the first section 121. In this way, the layout of the aircraft 100 can be optimized, and the probability of interference between the first electric tilt assembly 140 and other components on the fuselage 110 can be reduced.

[0050] In addition, the first electric tilt component 140 generates heat when working. Therefore, setting the first electric tilt component 140 in the first section 121 can not only reduce the probability that the heat generated by the first electric tilt component 140 will have an adverse effect on the operation of components installed in the fuselage 110 (such as a power supply, a control device), but also improve the heat dissipation efficiency of the first electric tilt component 140, which is beneficial to extending the service life of the components of the aircraft 100 (such as a power supply, a control device).

[0051] To further optimize the performance of the aircraft 100, such as Fig. 9As shown, the body 110 may be provided with a first fixing frame 150, and the first fixing frame 150 may accommodate a power source. Fig. 9 A second fixing frame 160 may be disposed adjacent to the rear end as shown, and the second fixing frame 160 may accommodate the control device.

[0052] In addition, the fixed wing 120 has a drainage effect on the airflow, so the first electric tilt assembly 140 is connected to the first section 121, so that the heat generated by the first electric tilt assembly 140 can be taken away by the airflow flowing through the fixed wing 120, that is, the heat dissipation efficiency of the first electric tilt assembly 140 can be improved. Therefore, the service life of the first electric tilt assembly 140 can be extended.

[0053] According to the aircraft 100 of the embodiment of the present invention, by arranging the first electric tilt assembly 140 on the first section 121, on the one hand, the layout of the aircraft 100 can be optimized, the probability of interference between the first electric tilt assembly 140 and other components on the fuselage 110 can be reduced, and the probability of the heat generated by the first electric tilt assembly 140 having an adverse effect on the operation of the components (such as a power supply and a control device) arranged on the fuselage 110 can be reduced, which is conducive to extending the service life of the components (such as a power supply and a control device) arranged on the fuselage 110. On the other hand, the heat dissipation of the first electric tilt assembly 140 is facilitated, thereby extending the service life of the first electric tilt assembly 140.

[0054] like Figure 1 , Figure 3 As shown, according to some embodiments of the present invention, the fixed wing 120 may have a first installation cavity 1213, and the first installation cavity 1213 may be provided at the connection position between the first section 121 and the second section 122, thereby not only constructing an accommodation space in the fixed wing 120, but also optimizing the layout and reducing the weight of the fixed wing 120. Figure 2 As shown, the first electric adjustment component 140 can be arranged in the first installation cavity 1213. Considering that the first power component 131 is arranged at the front and rear ends of the wing arm 130 connected to the first section 121 (such as Figure 1 By disposing the first electric adjustment component 140 in the first installation cavity 1213, it is also convenient to connect the first electric adjustment component 140 with the first power component 131, thereby optimizing the circuit layout of the aircraft 100.

[0055] like Figure 2 As shown, in some embodiments, a heat sink may be disposed in the first installation cavity 1213, and the heat sink may be closely connected to the first electrical adjustment component 140 to accelerate the heat dissipation speed of the first electrical adjustment component 140. In addition, an opening may be disposed at the housing of the first section 121, and the opening may correspond to the heat sink, thereby facilitating the heat released by the heat sink to be taken away by the external airflow.

[0056] like Figure 1 , Figure 3 , Figure 5 and Fig.10 As shown, in some embodiments, the fixed wing 120 has a first connector 126 and a second connector 127. The first connector 126 can be connected to the end of the first section 121 facing the second section 122, and the first connector 126 can have a first groove 1261 open to the second section 122. The second connector 127 can be connected to the first connector 126, and the second connector 127 can have a second groove 1271 open to the first connector 126. At this time, the connection between the second connector 127 and the first connector 126 can define a first installation cavity 1213. It can be understood that the first groove 1261 and the second groove 1271 can both define an accommodation space, thereby facilitating the arrangement of the connector to tighten the connection between the first section 121 and the second section 122. In addition, the second connector 127 can be connected to the end of the second end 122 facing the first section 121.

[0057] It can be understood that the first section 121, the first connecting member 126, the second connecting member 127 and the second section 122 can be connected in sequence to form a whole, and the first connecting member 126 can define a first installation cavity 1213 with the second connecting member 127, that is, the first installation cavity 1213 is an independent installation space relative to the first section 121 or the second section 122, which can not only provide a storage space for the components of the aircraft 100 (for example, provide an installation space for the electric adjustment component), but also reduce the probability of the components in the first installation cavity 1213 interfering with other components on the first section 121 or the second section 122.

[0058] For example, Figure 1 As shown, the right end of the first section 121 is provided with a first connecting member 126, and the right end of the first section 121 is connected to the first connecting member 126, and the first connecting member 126 has a first groove 1261, and the first groove 1261 is open to the right. Figure 3 , Fig.10 , Fig.11 As shown, a second connecting member 127 is provided on the right side of the first connecting member 126, and the right end of the second connecting member 127 is connected to the left end of the second section 122. Figure 5 As shown, the second connecting member 127 has a second groove 1271. It can be understood that, in combination with Fig.10 , Fig.11 The second groove 1271 may be open toward the first connecting member 126 , and the connection between the first connecting member 126 and the second connecting member 127 may enable the first groove 1261 and the second groove 1271 to cooperate to form a first installation cavity 1213 .

[0059] And if Figure 1As shown, the wing arm 130 is passed through the first installation cavity 1213, and the first electric adjustment component 140 is arranged in the first installation cavity 1213. It can be understood that the connection between the first electric adjustment component 140 and the first power component 131 can be routed along the wing arm 130, so as to optimize the line layout.

[0060] It should be noted that if Figure 1 , Figure 2 As shown, in the actual assembly process, considering the convenience of installation, it is preferred to make the first connecting member 126 and the first section 121 connected, and the first groove 1261 is open in the extension direction of the first section 121, at this time, part of the wing arm 130 can be inserted into the first groove 1261 along the front-back direction. Then the second connecting member 127 is connected to the first connecting member 126, and the second groove 1271 is connected to the first groove 1261 to construct the first installation cavity 1213. At this time, the matching connection between the second connecting member 127 and the first connecting member 126 can clamp and fix the wing arm 130 inserted into the first installation cavity 1213. Finally, the second section 122 is connected to the second connecting member 127.

[0061] In addition, in some embodiments, the wing surface of the fixed wing 120 may be made of foam material to reduce the weight of the aircraft 100. Accordingly, providing the first connector 126 and the second connector 127 on the fixed wing 120 may improve the support capability and reliability of the fixed wing 120.

[0062] like Figure 5 , Figure 6 As shown, in some embodiments, the inner wall of the first installation cavity 1213 may have reinforcing ribs. Thus, by providing reinforcing ribs on the inner wall of the first installation cavity 1213, the structural strength of the inner wall of the first installation cavity 1213 can be improved, thereby improving the supporting capacity of the inner wall of the first installation cavity 1213.

[0063] like Figure 3 As shown, according to some embodiments of the present invention, the aircraft 100 may further include an aileron 125, which may be connected to the fixed wing 120, and the aileron 125 may flip relative to the fixed wing 120. Therefore, by providing the aileron 125 that may be connected to the fixed wing 120, the aileron 125 may be controlled to flip relative to the fixed wing 120, thereby achieving control of the flight trajectory and flight state of the aircraft 100.

[0064] like Figure 3 , Figure 4As shown, according to some embodiments of the present invention, the aircraft 100 further includes a driving member 190 for driving the aileron 125 to flip, and the driving member 190 can be disposed in the first mounting cavity 1213. It can be understood that the control circuit can be connected to the driving member 190 to control the flipping of the aileron 125 to achieve the trajectory change of the aircraft 100. In addition, the first electric adjustment component 140 can be connected to the control circuit of the aircraft 100 for communication, such as Figure 6 As shown, a wire hole 1214 may be provided at the first connecting member 126, and a connecting wire (e.g., a wire) between the control circuit and the first electric tilt assembly 140 is passed through the wire hole 1214, that is, the connecting wire wire hole 1214 may pass through the wire hole 1214 to electrically connect the control circuit and the first electric tilt assembly 140. It can be understood that the wiring of the circuit connecting the control circuit and the driver 190 may also pass through the wire hole 1214, thereby, the driver 190 is arranged in the first installation cavity 1213, and the circuit connection between the control circuit and the driver 190 and the circuit connection between the control circuit and the first electric tilt assembly 140 may be arranged to have the same wiring path, thereby simplifying the circuit connection in the aircraft 100 and optimizing the circuit layout.

[0065] like Figure 3 As shown, the aileron 125 can be connected to the second section 122, and the aileron 125 can flip relative to the second section 122. It can be understood that the second section 122 is farther from the fuselage 110 than the first section 121. Therefore, by setting the aileron 125 to be connected to the second section 122, the distance between the aileron 125 and the fuselage 110 can be longer, so that the torque can be increased, and then the force generated by the flipping of the aileron 125 on the fuselage 110 can be enhanced, which is conducive to improving the agility of the aircraft 100 in changing direction. In some embodiments, the driving member 190 can be connected to the first connecting member 126. In this way, the layout of each component on the fixed wing 120 can be optimized, and the probability of interference between the components on the fixed wing 120 can be reduced.

[0066] According to some embodiments of the present invention, the wing arm 130 may be inserted into the first installation cavity 1213. Specifically, both ends of the first installation cavity 1213 have openings, and the wing arm 130 is inserted into the openings. Figure 3 As shown, the first installation cavity 1213 has open openings at both ends in the front-to-back direction, and the wing arm 130 is inserted into the two open openings along the front-to-back direction, thereby the wing arm can be fixed on the fixed wing 120 along the front-to-back direction. Further, the open opening and the wing arm 130 can be assembled together by interference fit, thereby not only improving the connection stability between the wing arm 130 and the first connecting member 126 and the second connecting member 127, but also preventing impurities from entering the first installation cavity 1213.

[0067] The control circuit and the first electric adjustment component 140 can be electrically connected through a first wire, and the first wire can be inserted through the first section 121. The first electric adjustment component 140 and the first power component 131 can be connected through a second wire, and the second wire can be inserted through the wing arm 130. Accordingly, a guide hole is provided at a position corresponding to the first installation cavity 1213 on the wing arm 130 for the second wire to pass through. Therefore, by inserting the first wire through the first section 121 and inserting the second wire through the wing arm 130, the first wire and the second wire can be both arranged inside the aircraft 100, avoiding the connection line from being exposed to the air, thereby reducing the probability of external factors (for example, rain, sand and dust) causing damage to the first wire or the second wire, extending the service life of the first wire or the second wire, and saving costs.

[0068] like Figure 1 As shown, according to some embodiments of the present invention, the aircraft 100 may further include a second power assembly 111, and the second power assembly 111 may be disposed at the fuselage 110. Thus, by disposing the second power assembly 111 at the fuselage 110, power can be provided for the aircraft 100 in the forward direction.

[0069] like Figure 1 , Figure 8 As shown, according to some embodiments of the present invention, the aircraft 100 may further include a second electric adjustment component 180 for adjusting the power of the second power component 111, and the second electric adjustment component 180 may be communicatively connected with the control circuit. Thus, by providing the second electric adjustment component 180, the power of the second power component 111 may be adjusted, and thus the flight speed of the aircraft 100 may be regulated.

[0070] like Figure 1 As shown, the second power assembly 111 may include a fixing seat 1111, and the fixing seat 1111 may be connected to the fuselage 110, and the fixing seat 1111 and the fuselage 110 may define a second installation cavity 1113, and the second installation cavity 1113 may accommodate the second electric tilt assembly 180. Therefore, by defining the second installation cavity 1113 that can accommodate the second electric tilt assembly 180 at the connection between the fixing seat 1111 and the fuselage 110, the second electric tilt assembly 180 and the second power assembly 111 can be closely distributed, so that the length of the connection line between the second electric tilt assembly 180 and the second power assembly 111 can be shortened, the line layout can be optimized, and the cost can be saved. In addition, the second power assembly 111 also includes a propeller 1112, and the propeller 1112 can be connected to the fixing seat 1111.

[0071] For example, Figure 1 As shown, the second power assembly 111 is disposed at the rear end of the fuselage 110 (eg Figure 1The rear end of the fuselage 110 and the front end of the fixing seat 1111 of the second power assembly 111 (as shown in FIG. Figure 1 The front end of the fixing base 1111 is connected to the propeller 1112. Figure 8 As shown, the fixing seat 1111 has an open opening. When the fixing seat 1111 is connected to the body 110 , the body 110 can cover the open opening to define a second installation cavity 1113 .

[0072] like Figure 3 , Figure 5 As shown, according to some embodiments of the present invention, the first section 121 can be detachably connected to the first connector 126, and the second section 122 can also be detachably connected to the second connector 127. Therefore, when the first connector 126 or the second connector 127 is damaged, the damaged first connector 126 or the second connector 127 can be replaced, which is beneficial to prolonging the service life of the aircraft 100 and saving costs.

[0073] In some embodiments, the first connector 126 may be snap-connected to the first section 121, and the second connector 127 may be snap-connected to the second section 122. It should be noted that the snap-connection does not involve other fasteners, which is convenient for assembly and disassembly, saves costs, and simplifies the connection.

[0074] In some embodiments, Fig.12 As shown, a button portion 1223 and a hook 1224 may be provided on the second section 122, and the button portion 1223 may drive the hook 1224 to switch between a latching state and a disengaged state. Figure 4 As shown, a latch hole 1273 may be constructed on the second connecting member 127. It is understandable that when the button portion 1223 is in a latching state, the latch hook 1224 may be latched in the latch hole 1273, and at this time, the second section 122 is connected to the second connecting member 127. When the button portion 1223 is in a disengaged state, the latch hook 1224 is suitable for being disengaged from the latch hole 1273, and at this time, the second section 122 may be separated from the second connecting member 127. Therefore, by providing the latch hook 1224 controlled by the button portion 1223, the disassembly and assembly process of the second section 122 and the second connecting member 127 can be simplified, and the assembly efficiency and convenience can be improved.

[0075] like Figure 1 , Figure 2 As shown, according to some embodiments of the present invention, the first section 121 can be detachably connected to the second section 122. This facilitates replacement of the damaged first section 121 or second section 122 when the first section 121 or second section 122 is damaged, thus saving costs.

[0076] For example, Figure 1 , Figure 6 and Fig. 9 As shown, the aircraft 100 may be provided with a connecting rod 123, which may be passed through the first section 121, and one end of the connecting rod 123 may be connected to the fuselage 110. The right end of the first section 121 located on the right side of the fuselage 110 may be connected to the first connecting member 126, the first connecting member 126 may be connected to the second connecting member 127, and the second connecting member 127 may be connected to the left end of the second section 122 located on the right side of the fuselage 110.

[0077] like Figure 1 , Figure 6 and Figure 7 As shown, the first connecting member 126 has a first groove 1261 open to the right, and the first connecting member 126 can be configured with a first through hole 1212, and the connecting rod 123 can pass through the first through hole 1212, so that the connecting rod 123 is partially inserted into the first groove 1261. It should be noted that the connecting rod 123 can be plugged into the first through hole 1212, and a portion of the connecting rod 123 passes through the first through hole 1212. Figure 5 As shown, the second connecting member 127 has a second groove 1271 open to the left, the second groove 1271 is opposite to the first groove 1261 and defines the first installation cavity 1213 together, and the second connecting member 127 can be configured with a second through hole 1222. It should be noted that the portion of the connecting rod 123 passing through the first through hole 1212 can be plugged into the second through hole 1222. Fig.11 , Fig.12 As shown, the hook 1224 on the second section 122 can be engaged with the engaging hole 1273 provided on the second connecting member 127, so that the second section 122 can be detachably connected to the second connecting member 127. That is, the connecting rod 123 can pass through the first section 121, the first connecting member 126 and the second connecting member 127 in sequence, and the second connecting member 127 can be engaged with the second section 122, so that the first section 121 and the second section 122 can be detachably connected together.

[0078] like Figure 5 , Figure 6 As shown, one of the first connecting member 126 and the second connecting member 127 has a snap-fit ​​foot 1274, and the other has a snap-fit ​​groove 1262 adapted to the snap-fit ​​foot 1274. In other words, when the first connecting member 126 has the snap-fit ​​foot 1274, the second connecting member 127 may be provided with the snap-fit ​​groove 1262; when the second connecting member 127 has the snap-fit ​​groove 1262, the first connecting member 126 may be provided with the snap-fit ​​foot 1274. It should be noted that the snap-fit ​​foot 1274 can extend into the snap-fit ​​groove 1262, and the snap-fit ​​foot 1274 can be snap-connected with the inner wall of the snap-fit ​​groove 1262, so that the first connecting member 126 and the second connecting member 127 can be connected together.

[0079] like Figure 5 , Figure 6 As shown, there may be multiple engaging feet 1274, and there may also be multiple engaging slots 1262, and the multiple engaging feet 1274 and the multiple engaging slots 1262 may correspond one to one. The free end of the engaging foot 1274 may have a protrusion, and when the engaging foot 1274 is fitted into the inside of the engaging slot 1262, the protrusion can be used to stably and securely fit the engaging foot 1274 together. In some examples, the engaging slot 1262 may be a through-hole structure.

[0080] like Figure 1 , Figure 2 As shown, according to some embodiments of the present invention, the body 110 is provided with a connecting rod 123, the free end of the connecting rod 123 may have a plug hole 1231, and the connecting rod 123 extends toward the second section 122. Figure 1 As shown, the connecting rod 123 can be inserted into the first section 121. Figure 3 As shown, the second section 122 has a plug-in column 1221, and the plug-in column 1221 can be inserted into the plug-in hole 1231. Therefore, the plug-in cooperation between the plug-in column 1221 and the plug-in hole 1231 can be used to connect the second section 122 with the free end of the connecting rod 123. It can be understood that the connecting rod 123 can be used as a supporting mechanism for the second section 122 to share the pressure borne by the second connecting member 127, that is, part of the load of the second section 122 can act on the second connecting member 127 through the connection between the hook 1224 and the plug-in hole 1273, and the other part can act on the connecting rod 123 through the plug-in connection between the plug-in column 1221 and the plug-in hole 1231, thereby reducing the probability of damage to the second section 122 or the second connecting member 127 due to excessive load on the second section 122, and increasing the reliability of the fixed wing 120.

[0081] It should be noted that the plug hole 1231 is not limited to being located on the connecting rod 123. For example, the plug post 1221 provided on the second section 122 can define the plug hole 1231, and the connecting rod 123 can be plugged into the plug hole 1231.

[0082] For example, Figure 1 , Fig. 9 and Fig.12 As shown, two connecting rods 123 are provided on the right side of the fuselage 110, one end of each connecting rod 123 is connected to the fuselage 110, and a plug hole 1231 is defined at the free end of each connecting rod 123, and the plug hole 1231 is open toward the second section 122. Two plug posts 1221 are provided at one end of the second section 122 facing the connecting rod 123, and it can be understood that the two plug posts 1221 can be adapted to be plugged with the two plug holes 1231 to connect the second section 122 and the connecting rod 123 together.

[0083] In some embodiments, Figure 1 As shown, in the actual assembly process of the fixed wing 120, the connecting rod 123 can be inserted into the first section 122, the first section 122 can be engaged with the first connecting member 126, and the free end of the connecting rod 123 can pass through the first through hole 1212, so that the connecting rod 123 is partially inserted into the first groove 1261, and the part of the connecting rod 123 that passes through the first through hole 1212 can pass through the second through hole 1222 provided on the second connecting member 127. Figure 1 As shown, the free end of the connecting rod 123 is defined with a plug hole 1231. Fig.11 , Fig.12 As shown, the end of the second section 122 facing the second connecting member 127 is provided with a plug-in column 1221 and a hook 1224. It can be understood that after the free end of the connecting rod 123 passes through the second through hole 1222, the plug-in column 1221 on the second section 122 can be plugged and matched with the plug-in hole 1231 on the connecting rod 123. At this time, the hook 1224 provided on the second section 122 can be plugged with the plug-in hole 1273 provided on the second connecting member 127 to connect the second section 122 and the second connecting member 127 together.

[0084] Reference below Figure 1-Figure 12 The aircraft 100 according to the present invention is described in detail. It should be understood that the following description is only for illustrative purposes and is not intended to limit the present invention.

[0085] like Figure 1-Figure 12 As shown, the aircraft 100 according to the embodiment of the present invention includes a fuselage 110 , fixed wings 120 , wing arms 130 , a first power assembly 131 , a second power assembly 111 , a first electric tilt assembly 140 , and a second electric tilt assembly 180 .

[0086] like Figure 3 As shown, the left side of the fuselage 110 (such as Figure 3 The left side of the fixed wing 120 is provided, and the right end of the first section 121 of the fixed wing 120 (as shown in FIG. Figure 3 The right side of the fuselage 110 is connected to the fuselage 110, the left end of the first section 121 is provided with a first connector 126, and the first connector 126 is connected to the left end of the first section 121, the left end of the first connector 126 is connected to the second connector 127, and the left side of the second connector 127 is connected to the right end of the second section 122. The right side of the fuselage 110 may also be provided with a fixed wing 120, the left end of the first section 121 of the fixed wing 120 is connected to the fuselage 110, the right end of the first section 121 is provided with a first connector 126, and the first connector 126 is connected to the right end of the first section 121, the right side of the first connector 126 is connected to the second connector 127, and the right side of the second connector 127 is connected to the left end of the second section 122. Figure 3As shown, the left and right sides of the fuselage 110 (such as Figure 3 The wing arms 130 are respectively provided with a left and right direction (as shown in the figure), and the wing arms 130 located on the left and right sides of the fuselage 110 are both in the front-to-back direction (as shown in the figure). Figure 3 The wing arm 130 located on the left side of the fuselage 110 is connected to the first connecting member 126 located on the left side of the fuselage 110, and the wing arm 130 located on the right side of the fuselage 110 can be connected to the first connecting member 126 located on the right side of the fuselage 110.

[0087] like Figure 1 As shown, it is located on the left side of the fuselage 110 (such as Figure 1 The front and rear ends of the wing arms 130 (as shown on the left side) Figure 1 The front and rear ends (shown in FIG. 1 ) are both provided with a first power assembly 131, which is located on the right side of the fuselage 110 (as shown in FIG. Figure 1 The front and rear ends of the wing arm 130 (as shown on the right side) are also provided with a first power assembly 131.

[0088] like Figure 1 As shown, it is located on the left side of the fuselage 110 (such as Figure 1 A tail 170 is provided at the rear end of the wing arm 130, which is located on the right side of the fuselage 110 (as shown in FIG. Figure 1 A tail 170 is also provided at the rear end of the wing arm 130 (shown on the right side), and the two tails 170 can be pivotally connected to each other in an inverted V shape. It should be noted that the inverted V-shaped tail 170 has the functions of a common fixed-wing vertical tail and a horizontal tail, has a small structural weight, and has high control efficiency.

[0089] like Figure 1 As shown, it is located on the right side of the fuselage 110 (such as Figure 1 The first connector 126 (shown on the right side) has a first groove 1261 open to the right. It should be noted that the second connector 127 located on the right side of the fuselage 110 has a second groove 1271 open to the left. The first connector 126 and the second connector 127 are connected to define a first installation cavity 1213. The first installation cavity 1213 is provided with a first electric tilt component 140. A heat sink is provided above the first electric tilt component 140. The heat sink has an opening above it so that the heat released by the heat sink can be taken away by the external airflow. Figure 6 As shown, a wire hole 1214 is provided on the end surface of the first section 121 connected to the second end, which is used to provide a path for the circuit connection between the control circuit and the first electrical adjustment component 140, thereby optimizing the circuit connection of the aircraft 100.

[0090] like Fig. 9 As shown, the body 110 is provided with a first fixing frame 150, and the first fixing frame 150 can accommodate a power source. Fig. 9A second fixing frame 160 may be disposed adjacent to the rear end as shown, and the second fixing frame 160 may accommodate the control device.

[0091] like Fig. 9 As shown, the left side of the fuselage 110 (such as Fig. 9 The left side as shown in FIG. 1 is connected to two connecting rods 123, and the right side of the fuselage 110 (as shown in FIG. Fig. 9 The right side of the second embodiment shown in FIG. 1 is also connected to two connecting rods 123, and one end of each connecting rod 123 is connected to the fuselage 110, and the other end is passed through the corresponding first section 121. Figure 1 As shown, two first through-holes 1212 are provided in the first groove 1261 on the right side of the fuselage 110 . The two first through-holes 1212 correspond to the two connecting rods 123 on the right side of the fuselage 110 , respectively. The two connecting rods 123 can partially pass through the two first through-holes 1212 , respectively.

[0092] like Figure 1 As shown, during the actual assembly process of the fixed wing 120, the connecting rod 123 can be inserted into the first section 122, the first section 122 can be snap-fitted with the first connecting member 126, the free end of the connecting rod 123 can pass through the first through hole 1212, so that the connecting rod 123 is partially inserted into the first groove 1261, and the part of the connecting rod 123 that passes through the first through hole 1212 can pass through the second through hole 1222 provided on the second connecting member 127.

[0093] like Figure 1 As shown, the free end of the connecting rod 123 is defined with a plug hole 1231. Fig.11 , Fig.12 As shown, the end of the second section 122 facing the second connecting member 127 is provided with a plug-in column 1221 and a hook 1224. It can be understood that after the free end of the connecting rod 123 passes through the second through hole 1222, the plug-in column 1221 on the second section 122 can be plugged and matched with the plug-in hole 1231 on the connecting rod 123. At this time, the hook 1224 provided on the second section 122 can be plugged with the plug-in hole 1273 provided on the second connecting member 127 to connect the second section 122 and the second connecting member 127 together.

[0094] like Figure 1 As shown, the second power assembly 111 is disposed at the rear end of the fuselage 110 (eg Figure 1 The rear end of the fuselage 110 and the front end of the fixing seat 1111 of the second power assembly 111 (as shown in FIG. Figure 1 The front end of the fixing base 1111 is connected to the propeller 1112. Figure 8As shown, the fixing seat 1111 has an open opening, which faces the direction of the fuselage 110. When the fixing seat 1111 is connected to the fuselage 110, the fuselage 110 can cover the open opening to define a second installation cavity 1113. The second installation cavity 1113 can accommodate the second electric adjustment component 180, and the second electric adjustment component 180 can be used to adjust the power of the second power component 111.

[0095] like Figure 1 , Figure 2 As shown, the front end of the first electrical adjustment component 140 (such as Figure 1 The front end (shown in FIG. 1 ) is provided with an output end, which is used to adjust the power of the first power assembly 131 at the front end of the wing arm 130. The rear end (shown in FIG. 1 ) of the first electric adjustment assembly 140 is provided with an output end, which is used to adjust the power of the first power assembly 131 at the front end of the wing arm 130. Figure 1 The rear end shown in the figure is also provided with an output end, which is used to adjust the power size of the first power component 131 at the rear end of the wing arm 130.

[0096] It should be noted that when it is necessary to control the aircraft 100 to change the flight speed, the control circuit can issue an instruction to the first electrical adjustment component 140, and the first electrical adjustment component 140 adjusts the power of the first power component 131 according to the instruction.

[0097] like Figure 3 As shown, the rear end of the second section 122 (such as Figure 3 The rear end of the second section 1213 is connected to the aileron 125, and the aileron 125 can be flipped relative to the second section 122. It should be noted that a driving member 190 can be disposed in the first installation cavity 1213, and the driving member 190 can drive the aileron 125 to flip, and the control circuit can be connected to the driving member 190 to control the flipping of the aileron 125 to achieve the trajectory change of the aircraft 100.

[0098] like Fig.12 As shown, a button portion 1223 and a hook 1224 may be provided on the second section 122, and the button portion 1223 may drive the hook 1224 to switch between a latching state and a disengaged state. Figure 4 As shown, a locking hole 1273 may be constructed on the second connecting member 127. It is understandable that when the button portion 1223 is in the locking state, the hook 1224 may be locked in the locking hole 1273, and at this time, the second section 122 is connected to the second connecting member 127. When the button portion 1223 is in the disengaged state, the hook 1224 is suitable for being disengaged from the locking hole 1273, and at this time, the second section 122 can be separated from the second connecting member 127.

[0099] like Figure 1 , Fig. 9 and Fig.12As shown, two connecting rods 123 are provided on the right side of the fuselage 110, one end of each connecting rod 123 is connected to the fuselage 110, and a plug hole 1231 is defined at the free end of each connecting rod 123, and the plug hole 1231 is open toward the second section 122. Two plug posts 1221 are provided at one end of the second section 122 facing the connecting rod 123, and it can be understood that the two plug posts 1221 can be adapted to be plugged with the two plug holes 1231 to connect the second section 122 and the connecting rod 123 together.

[0100] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "illustrative embodiments", "examples", "specific examples", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0101] Although the embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the claims and their equivalents.

Claims

1. An aircraft, characterized in that: include A fuselage, wherein a control circuit is arranged in the fuselage; A fixed wing, the fixed wing comprising a first section and a second section connected to the first section, the first section being connected to the fuselage; a wing arm, the wing arm being connected to the first section, the wing arm extending along the length direction of the fuselage, and a first power assembly being disposed at both ends of the wing arm; a first electric adjustment component for adjusting the power of the first power component, the first electric adjustment component being arranged in the first section and being communicatively connected with the control circuit; The fixed wing has a first installation cavity, and the first installation cavity is provided at the connection position of the first section and the second section, and the first electric adjustment component is provided in the first installation cavity; The fixed wing has a first connecting piece, the first connecting piece is connected to the end of the first section facing the second section, the first connecting piece has a first groove, and the first groove is open toward the second section; a second connecting member, the second connecting member being connected to an end of the second section facing the first section, the second connecting member having a second groove, the second groove being open toward the first connecting member, and the second connecting member being connected to the first connecting member to define the first installation cavity; The first section is detachably connected to the second section.

2. The aircraft according to claim 1, characterized in that The aircraft further comprises an aileron, wherein the aileron is connected to the fixed wing and the aileron is flippable relative to the fixed wing. The aircraft comprises a driving member for driving the aileron to flip, the driving member is arranged in the first mounting cavity, the aileron is connected to the second section, and the aileron is flippable relative to the second section. The driving member is connected to the first connecting member.

3. The aircraft according to claim 1, characterized in that: The first connecting member is provided with a wire hole, and the connecting wire between the control circuit and the first electric adjustment component is passed through the wire hole.

4. The aircraft according to claim 1, characterized in that: The fuselage has a connecting rod, and the connecting rod is arranged through the first section. The first connecting member has a first groove, the first connecting member has a first through hole, the connecting rod is passed through the first through hole, and a part of the connecting rod is located in the first groove. The second connecting member has a second groove, the second groove is opposite to the first groove and jointly defines the first installation cavity, the second connecting member has a second through hole, and the part of the connecting rod passing through the first through hole is plugged into the second through hole.

5. The aircraft according to claim 1, characterized in that: The first section is detachably connected to the first connecting member; the second section is detachably connected to the second connecting member.

6. The aircraft according to claim 1, characterized in that: One of the first connecting member and the second connecting member has a locking foot, and the other has a locking groove matched with the locking foot.

7. The aircraft according to claim 1, characterized in that: The wing arm is disposed in the first installation cavity; The control circuit is electrically connected to the first electrical adjustment component via a first wire, and the first wire is arranged through the first section; The first electric adjustment component is electrically connected to the first power component via a second wire, and the second wire is passed through the wing arm.

8. The aircraft according to claim 1, characterized in that: It also includes a second power assembly, which is arranged on the fuselage.

9. The aircraft according to claim 8, characterized in that The aircraft includes a second electric adjustment component for adjusting the power of the second power component, and the second electric adjustment component is communicatively connected with the control circuit; The second power assembly comprises: A fixing seat, the fixing seat is connected to the fuselage, the fixing seat and the fuselage define a second installation cavity, and the second electrical adjustment component is arranged in the second installation cavity; A propeller is connected to the fixing seat.

10. The aircraft according to claim 1, characterized in that: The fuselage is provided with a connecting rod, the free end of which has a plug hole, and the connecting rod extends toward the second section. The connecting rod is disposed through the first section. The second section has an inserting post, and the inserting post is inserted into the inserting hole.

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