Aircraft fuselage and aircraft

Abstract

The present invention discloses a fuselage of an aircraft and an aircraft. The fuselage includes: a fuselage frame and an adjustment assembly for adjusting the position of a functional component. A receiving cavity adapted to receive the functional component is defined within the fuselage frame, and a plurality of first locking portions are formed on the fuselage frame and arranged at intervals in the front-rear direction. The adjustment assembly includes: a connecting seat and a locking assembly for locking the connecting seat to the fuselage frame. The connecting seat is movably arranged on the fuselage frame in the front-rear direction, and the functional component is adapted to be connected to the connecting seat. The locking assembly includes a locking member, the locking member is movably arranged on the connecting seat in the up-down direction, a second locking portion is formed on the locking member, the second locking portion is adapted to cooperate with any one of the plurality of first locking portions to lock the connecting seat to the fuselage frame, and the second locking portion can be disengaged from the first locking portion by moving the locking member up and down. For the fuselage of the aircraft according to the embodiments of the present invention, the center of gravity of the aircraft can be adjusted by adjusting the position of the functional component.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and more particularly to an aircraft fuselage and an aircraft Background Art

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

[0003] In different application scenarios, an aerial photography UAV needs to replace aerial photography lenses of different specifications according to requirements. Different specifications of aerial photography lenses have unequal weights, which causes the center of gravity of the aerial photography UAV to change. In related technologies, an unmanned aircraft cannot adjust its center of gravity to adapt to the change of the load, which greatly affects the flight performance, economy and safety of the aircraft. Summary of the Invention

[0004] The present invention aims to at least solve one of the technical problems existing in the prior art. For this purpose, an object of the present invention is to provide a fuselage of an aircraft, which can adjust the position of the center of gravity, so as to change the position of the center of gravity according to the change of the load, thereby greatly improving the flight performance, economy and safety of the aircraft.

[0005] The present invention also provides an aircraft with the above fuselage.

[0006] According to an embodiment of the first aspect of the present invention, the fuselage of the aircraft includes: a fuselage frame, a receiving cavity adapted to receive functional components is defined within the fuselage frame, and a plurality of first locking portions are formed on the fuselage frame and arranged at intervals in the front-rear direction; an adjusting assembly for adjusting the position of the functional components, the adjusting assembly includes: a connecting seat, the connecting seat is movably arranged on the fuselage frame in the front-rear direction, and the functional components are adapted to be connected to the connecting seat; a locking assembly for locking the connecting seat on the fuselage frame, the locking assembly includes a locking member, the locking member is movably arranged on the connecting seat in the up-down direction, a second locking portion is formed on the locking member, and the second locking portion is adapted to cooperate with any one of the plurality of first locking portions to lock the connecting seat on the fuselage frame, and the second locking portion can be disengaged from the first locking portion by moving the locking member up and down.

[0007] According to the fuselage of the aircraft according to an embodiment of the present invention, by providing an adjustment assembly, the position of the functional component can be adjusted in the front-rear direction. Thus, when the aircraft's fuselage mounting changes, the position of the functional component can be adjusted through the adjustment assembly, the center of gravity of the aircraft can be adjusted, so that the center of gravity of the aircraft can change according to the weight of the mounting, and the center of gravity of the aircraft can be adjusted to a position where the aircraft as a whole is relatively balanced, greatly improving the flight performance, economy, and safety of the aircraft.

[0008] According to some embodiments of the present invention, the upper end of the accommodation cavity is open, flanging portions are respectively formed on the left side wall and the right side wall of the accommodation cavity, and the left and right ends of the connecting seat are respectively supported on the flanging portions.

[0009] According to some alternative embodiments of the present invention, a guiding groove penetrating the flanging portion in the up-down direction is formed on the flanging portion, the guiding groove extends in the front-rear direction, a plurality of the first locking portions are respectively formed at positions corresponding to the guiding groove on the left and right outer wall surfaces of the accommodation cavity, the locking member is inserted through the corresponding guiding groove and can move back and forth along the corresponding guiding groove, and the second locking portion extends downward out of the corresponding guiding groove and is adapted to cooperate with the corresponding first locking portion.

[0010] Optionally, the adjustment assembly includes: a first fixing seat, which is provided directly below the flanging portion and is connected to the connecting seat.

[0011] Optionally, a first installation groove opposite to and communicating with the guiding groove is formed on the connecting seat, the locking member is movably disposed up and down in the first installation groove, a first stopping portion is formed on the inner peripheral wall of the first installation groove, the locking member includes a locking member body and a stopping protrusion formed on the locking member body, the locking assembly includes a first elastic member, the first elastic member is telescopable in the up-down direction, the upper end of the first elastic member abuts or is connected to the stopping protrusion, and the lower end of the first elastic member abuts or is connected to the first stopping portion.

[0012] Furthermore, the adjustment assembly includes: a second fixing seat, which is provided on the top of the connecting seat and is connected to the connecting seat, and the upper end surface of the stopping protrusion is adapted to abut against the second fixing seat in the up-down direction.

[0013] Optionally, a receiving groove is formed on the locking member, the stopping protrusion constitutes the top wall of the receiving groove, the bottom of the receiving groove is open, and the first elastic member is received in the receiving groove.

[0014] According to some embodiments of the present invention, a first guiding rib extending in the front-rear direction is formed on the upper surface of the flanging portion. The first guiding ribs are multiple and arranged at intervals in the left-right direction, and the connecting seat is supported on the multiple first guiding ribs.

[0015] According to some embodiments of the present invention, the locking member includes a locking member body, a second locking portion is formed on the locking member body. The second locking portion is a locking protrusion formed on the locking member body, and the first locking portion is a locking groove formed on the fuselage frame.

[0016] According to some alternative embodiments of the present invention, the surfaces of the locking protrusion and the locking groove that cooperate with each other are both cylindrical surfaces.

[0017] According to some alternative embodiments of the present invention, the locking member includes a mating protrusion. The mating protrusion is connected to the locking member body through an elastic arm. The mating protrusion is located directly above the second locking portion. The mating protrusion and the second locking portion both cooperate with the same first locking portion. When the connecting seat moves, the mating protrusion can move from one of the multiple first locking portions to another of the multiple first locking portions.

[0018] Optionally, the surface of the mating protrusion that cooperates with the first locking portion is a spherical surface.

[0019] According to some embodiments of the present invention, the functional component is a battery module.

[0020] According to some embodiments of the present invention, the functional component is detachably connected to the connecting seat.

[0021] According to some alternative embodiments of the present invention, the connecting seat includes: a connecting portion extending in the left-right direction; two mounting portions respectively provided at the left and right ends of the connecting portion. A part of the functional component is located in the fitting space defined by the two mounting portions and the connecting portion. Second guiding ribs extending in the up-down direction are respectively formed on the left and right side walls of the fitting space.

[0022] According to some alternative embodiments of the present invention, the functional component is a battery module. The battery module includes a battery housing and a battery provided in the battery housing. A step portion is formed on one side of the battery housing. The step portion is adapted to be supported on the connecting seat. Limiting grooves are respectively formed on the opposite two side walls of the step portion. Limiting protrusions mating with the limiting grooves are provided on the connecting seat.

[0023] Further, the connecting seat includes: a connecting portion extending in the left - right direction, and the stepped portion is adapted to be supported on the connecting portion; mounting portions, there are two mounting portions respectively arranged at the left and right ends of the connecting portion, a part of the battery module is located within the fitting space defined by the two mounting portions and the connecting portion, guiding holes are respectively provided on the left and right side walls of the fitting space, and the limiting protrusion is telescopically inserted into the corresponding guiding hole.

[0024] Optionally, it includes: a second elastic member, a second mounting groove is formed on the mounting portion, the second elastic member is arranged in the second mounting groove and the second elastic member is telescopically movable along the central axis direction of the guiding hole, one end of the second elastic member is connected to the limiting protrusion, and the other end of the second elastic member is connected to the side wall of the second mounting groove.

[0025] Optionally, a positioning protrusion is formed on one of the top of the connecting portion and the bottom of the stepped portion, and a positioning groove cooperating with the positioning protrusion is formed on the other.

[0026] According to some alternative embodiments of the present invention, a first through - hole adapted for the male end of the electrical connector to pass through is formed on the connecting portion, a second through - hole adapted for the female end of the electrical connector to pass through is formed on the stepped portion, and the first through - hole and the second through - hole are arranged opposite to each other.

[0027] The aircraft according to the embodiment of the second aspect of the present invention includes: a fuselage, and the fuselage is the fuselage according to the above - mentioned first aspect embodiment of the present invention.

[0028] By providing the above - mentioned fuselage in the aircraft according to the embodiment of the present invention, when the aircraft's fuselage hanging changes, the position of the battery module can be adjusted through the adjustment assembly, so that the center of gravity of the aircraft can be adjusted, enabling the center of gravity of the aircraft to change according to the weight of the hanging, and enabling the center of gravity of the aircraft to be adjusted to a position where the aircraft as a whole remains relatively balanced, greatly improving the flight performance, economy, and safety of the aircraft in use.

[0029] The additional aspects and advantages of the present invention will be partially given in the following description, partially will become obvious from the following description, or will be understood through the practice of the present invention. Description of the Drawings

[0030] The above - mentioned and / or additional aspects and advantages of the present invention will become obvious and easy to understand from the description of the embodiments in conjunction with the following drawings, where:

[0031] Figure 1 is a perspective view of an aircraft according to some embodiments of the present invention, where the second wing segment is removed from the fuselage;

[0032] Figure 2 is Figure 1 a perspective view of the fixing part of the aircraft in

[0033] Figure 3 is Figure 1 a perspective view of the lower cover body of the aircraft in

[0034] Figure 4 is Figure 1 a perspective view of the lower cover body of the aircraft from another angle in

[0035] Figure 5 is Figure 1 a perspective view of the heat dissipation shell of the aircraft in

[0036] Figure 6 a perspective view of a partial structure of the aircraft according to some embodiments of the present invention;

[0037] Figure 7 is Figure 6 a perspective view of the connection between the fuselage frame and the aerial photography module of the aircraft in

[0038] Figure 8 is Figure 7 an exploded view of the first fixing frame of the fuselage frame and the adjusting component in

[0039] Figure 9 is Figure 8 an enlarged view of part A in

[0040] Figure 10 is Figure 8 an enlarged view of part B in

[0041] Figure 11 is Figure 7 an assembly view of the first fixing frame of the fuselage frame and the adjusting component in

[0042] Figure 12 is Figure 11 an enlarged view of part C in

[0043] Figure 13 is Figure 8 a perspective view of the first fixing frame in

[0044] Figure 14 is Figure 8 a perspective view of the first fixing frame from another angle in

[0045] Figure 15 is Figure 14 an enlarged view of part D in

[0046] Figure 16 is Figure 8 a perspective view of the connecting seat in

[0047] Figure 17 is Figure 16 an enlarged view of the E position in

[0048] Figure 18 is Figure 8 a perspective view of the connecting seat in

[0049] Figure 19 is Figure 8 a perspective view of the locking member in

[0050] Figure 20 is Figure 8 a perspective view of the limiting protrusion in

[0051] Figure 21 is Figure 8 a perspective view of the first fixing seat in

[0052] Figure 22 is Figure 8 a perspective view of the second fixing seat in

[0053] Figure 23 is Figure 7 a perspective view of the battery module in

[0054] Figure 24 is Figure 23 an enlarged view of the F position in

[0055] Figure 25 is Figure 7 a perspective view of the second fixing frame in

[0056] Reference numerals:

[0057] Aircraft 100;

[0058] Fuselage 1; Fuselage outer shell 11; First mounting opening 111; Fuselage upper cover 12; Lower cover body 131; Heat dissipation housing 132; Heat dissipation fins 1321; First fixing frame 14; Accommodating cavity 141; Flanging portion 142; Guide groove 1421; First guide rib 143; First locking portion 144; Second fixing frame 15; Receiving cavity 151;

[0059] Connecting seat 16; Connecting portion 161; First through hole 1611; Positioning protrusion 1612; Mounting portion 162; First mounting groove 1621; First stop portion 1622; Second mounting groove 1623; Guide hole 1624; Second guide rib 1625; Limiting protrusion 163; First limiting section 1631; Second limiting section 1632; Mounting hole 1633; Second elastic member 164;

[0060] Locking member 17; Locking member body 171; Stopping protrusion 172; Accommodating groove 173; Second locking portion 174; Fitting protrusion 175; Elastic arm 176; First elastic member 177;

[0061] First fixing seat 18; Avoiding notch 181; Second fixing seat 19; First avoiding hole 191; Second avoiding hole 192;

[0062] Functional component 2; Battery housing 21; Step portion 22; Limiting groove 221; Positioning groove 222; Second through hole 223; Battery 23; Female end 24;

[0063] Fixed wing 3; First wing segment 31; Support rod 311; Second wing segment 32; Connecting rod 321; Fixing portion 33; Second connection hole 331; Aileron 34;

[0064] Wing arm 4;

[0065] Tail wing 5; Tail wing plate 51; Movable control surface 52;

[0066] Tail support rod 6;

[0067] Tail support seat 7;

[0068] First power component 81; First power unit 811; First propeller 812; Second power component 82; Second power unit 821; Second propeller 822;

[0069] Aerial photography module 9. Specific embodiments

[0070] The embodiments of the present invention will be described in detail below. Examples of the embodiments are shown in the drawings, where the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the drawings are exemplary and are only used to explain the present invention and should not be construed as limiting the present invention.

[0071] The following refers to Figures 1 - 25 Describe the fuselage 1 of the aircraft 100 according to an embodiment of the present invention. The aircraft 100 may be an unmanned aircraft 100, and the aircraft 100 may be used in fields such as aerial photography mapping, power inspection, environmental monitoring, and disaster inspection. For example, the aircraft 100 may be a fixed-wing aircraft 100, which can take off and land at zero speed, has the ability to hover, has a large horizontal flight speed, and can fly horizontally in the manner of the fixed wing 3.

[0072] Such as Figure 1 、 Figure 6 、 Figure 7 And Figure 8As shown, the fuselage 1 of the aircraft 100 according to the embodiment of the first aspect of the present invention includes: a fuselage frame and an adjustment assembly for adjusting the position of the functional component 2.

[0073] An accommodation cavity 141 adapted to accommodate the functional component 2 is defined within the fuselage frame, and a plurality of first locking portions 144 are formed on the fuselage frame and arranged at intervals in the front-rear direction. Among them, the adjustment assembly includes: a connection seat 16 and a locking assembly for locking the connection seat 16 to the fuselage frame. The connection seat 16 is movably arranged on the fuselage frame in the front-rear direction, and the functional component 2 is adapted to be connected to the connection seat 16. Thus, when the connection seat 16 moves in the front-rear direction, the functional component 2 moves along with the connection seat 16 in the front-rear direction. Thereby, the front-rear position of the functional component 2 can be adjusted, and thus the center-of-gravity position of the aircraft 100 can be changed.

[0074] For example, when aerial photography modules 9 of different specifications are provided on the fuselage 1, by adjusting the position of the functional component 2, the center-of-gravity position of the aircraft 100 can be adjusted, so that the center-of-gravity position of the aircraft 100 can change adaptively according to the weight of the load (such as the aerial photography module 9), so that the center-of-gravity position of the aircraft 100 is maintained at a position where the overall aircraft 100 is balanced, which can improve the flight performance and flight safety of the aircraft 100, and there is no need to additionally add other counterweights to keep the center-of-gravity position of the aircraft 100 balanced, thus improving economy.

[0075] The locking assembly is used to lock the connection seat 16 to the fuselage frame. The locking assembly includes a locking member 17. The locking member 17 is movably arranged on the connection seat 16 in the up-down direction. A second locking portion 174 is formed on the locking member 17. The second locking portion 174 is adapted to cooperate with any one of the plurality of first locking portions 144 to lock the connection seat 16 to the fuselage frame. The locking member 17 can be moved up and down to disengage the second locking portion 174 from the first locking portion 144. By cooperating the second locking portion 174 on the locking member 17 with any one of the first locking portions 144 in the fuselage frame, the connection seat 16 can be locked to the fuselage frame, and thus the functional component 2 can be locked to the fuselage frame.

[0076] When it is necessary to adjust the center of gravity position of the aircraft 100, the locking member 17 can be moved up and down so that the second locking portion 174 of the locking member 17 is disengaged from the first locking portion 144 on the fuselage frame (for example, the locking member 17 can be moved downward so that the second locking portion 174 of the locking member 17 is disengaged from the first locking portion 144 on the fuselage frame). Thereby, the connecting seat 16 can be unlocked, so that the connecting seat 16 can move in the front-rear direction, and thus the functional component 2 can be driven to move in the front-rear direction to adjust the center of gravity position of the aircraft 100. When the connecting seat 16 moves to the set position, the second locking portion 174 of the locking member 17 can be made to cooperate with the first locking portion 144 at the corresponding position on the fuselage frame by moving the locking member 17 up and down (for example, the locking member 17 can be moved upward so that the second locking portion 174 of the locking member 17 cooperates with the first locking portion 144 on the fuselage frame). Thereby, the connecting seat 16 can be locked, and thus the functional component 2 can be locked in the set position.

[0077] Optionally, the functional component 2 can be a battery module. Since the weight of the battery module is usually large, the center of gravity position of the aircraft 100 can be adjusted quickly and effectively.

[0078] It should be noted that the "plurality" referred to in the present invention means two or more.

[0079] It should be noted that the "front, rear, left, right, up, and down" directions described in the present invention are relative to the flight direction of the aircraft 100.

[0080] According to the fuselage 1 of the aircraft 100 according to an embodiment of the present invention, by providing an adjustment assembly, the position of the functional component 2 can be adjusted in the front-rear direction. Thus, when the payload of the fuselage 1 of the aircraft 100 changes, the position of the functional component 2 can be adjusted by the adjustment assembly to adjust the center of gravity of the aircraft 100, so that the center of gravity of the aircraft 100 can be changed according to the weight of the payload, and the center of gravity of the aircraft 100 can be adjusted to a position where the overall aircraft 100 is relatively balanced, greatly improving the flight performance, economy, and safety of the aircraft 100.

[0081] According to some embodiments of the present invention, referring to Figure 8 、 Figure 13 and Figure 14, the upper end of the above-mentioned accommodation cavity 141 of the fuselage frame is open, flanging portions 142 are respectively formed on the left side wall and the right side wall of the accommodation cavity 141, and the left and right ends of the connecting seat 16 are respectively supported on the flanging portions 142. By making the upper end of the accommodation cavity 141 open, it is convenient to install the functional component 2 into the accommodation cavity 141 through the open end of the accommodation cavity 141. Moreover, by respectively forming the flanging portions 142 on the left side wall and the right side wall of the accommodation cavity 141, the supporting force and the supporting area of the fuselage frame for the connecting seat 16 can be increased, so that the connecting seat 16 is reliably supported on the top of the accommodation cavity 141.

[0082] According to some alternative embodiments of the present invention, referring to Figure 8 , Figure 9 , Figures 13 - 15 , a guiding groove 1421 penetrating the flanging portion 142 in the up-and-down direction is formed on the flanging portion 142, the guiding groove 1421 extends in the front-and-rear direction, and a plurality of first locking portions 144 are respectively formed at positions corresponding to the guiding groove 1421 on the left and right outer wall surfaces of the accommodation cavity 141. The locking member 17 is inserted into the corresponding guiding groove 1421 and can move back and forth along the corresponding guiding groove 1421. The second locking portion 174 extends downward out of the corresponding guiding groove 1421 and is adapted to cooperate with the corresponding first locking portion 144. Thus, through the guiding groove 1421 provided on the flanging portion 142 and the locking member 17 being inserted into the guiding groove 1421, when the connecting seat 16 moves in the front-and-rear direction, the locking member 17 can move along the extending direction of the guiding groove 1421, which has a guiding effect on the front-and-rear movement of the connecting seat 16. Moreover, when the locking member 17 moves to different positions along the front-and-rear direction with the connecting seat 16, it is convenient for the second locking portion 174 of the locking member 17 to cooperate with the first locking portion 144 at the corresponding position, so that the movement of the locking member 17 and the locking of the connecting seat 16 can be conveniently realized.

[0083] Furthermore, referring to Figure 8 , Figure 12 and Figure 21 , the adjusting assembly includes: a first fixing seat 18, the first fixing seat 18 is arranged directly below the flanging portion 142 and is connected to the connecting seat 16, and the first fixing seat 18 can be in contact with the lower surface of the flanging portion 142. Thus, through the provided first fixing seat 18, a limiting effect on the connecting seat 16 in the up-and-down direction can be achieved, preventing the connecting seat 16 from falling off the fuselage frame.

[0084] In some alternative embodiments of the present invention, referring to Figures 8 - 10 , Figure 12 and Figure 17, a first mounting groove 1621 opposite to and communicating with the guiding groove 1421 is formed on the connecting seat 16, and the locking member 17 is movably disposed in the first mounting groove 1621 in the up-and-down direction, thus facilitating the installation of the locking member 17. A first stopping portion 1622 is formed on the inner peripheral wall of the first mounting groove 1621. The locking member 17 includes a locking member body 171 and a stopping protrusion 172 formed on the locking member body 171. The locking assembly includes a first elastic member 177. The first elastic member 177 is telescopable in the up-and-down direction. The upper end of the first elastic member 177 abuts against or is connected to the stopping protrusion 172, and the lower end of the first elastic member 177 abuts against or is connected to the first stopping portion 1622. Thus, through the arranged first elastic member 177, the up-and-down movement of the locking member 17 can be realized by the telescopic deformation of the first elastic member 177 in the up-and-down direction.

[0085] For example, the locking member 17 can be pressed downward so that the locking member 17 moves downward, so that the first locking portion 144 of the locking member 17 is disengaged from the corresponding second locking portion 174 on the fuselage frame. At this time, the connecting seat 16 can be moved to a set position in the front-rear direction. Then, the pressing force on the locking member 17 downward is released. At this time, the locking member 17 moves upward to the initial position under the elastic force of the first elastic member 177, and the second locking portion 174 of the locking member 17 cooperates with the first locking portion 144 at the corresponding position to lock the connecting seat 16 at the set position on the fuselage frame.

[0086] Further, referring to Figure 8 , Figure 12 and Figure 22 , the adjusting assembly includes: a second fixing seat 19. The second fixing seat 19 is disposed on the top of the connecting seat 16 and connected to the connecting seat 16. The upper end surface of the stopping protrusion 172 is adapted to abut against the second fixing seat 19 in the up-and-down direction. Thus, by arranging the second fixing seat 19 on the top of the connecting seat 16, the locking member 17 can be limited in the up-and-down direction, preventing the locking member 17 from moving upward too much under the elastic force of the first elastic member 177 and causing the locking member 17 to fall off the connecting seat 16.

[0087] In some alternative embodiments of the present invention, referring to Figure 9 , Figure 12 and Figure 19, a receiving groove 173 is formed on the locking member 17, the stop projection 172 constitutes the top wall of the receiving groove 173, the bottom of the receiving groove 173 is open, and the first elastic member 177 is received in the receiving groove 173. Thus, the upper end of the first elastic member 177 abuts against or is connected to the top wall of the receiving groove 173, and the lower end of the first elastic member 177 passes downward through the bottom of the receiving groove 173 and is connected to and abuts against the first stop portion 1622, which facilitates the installation and fixation of the first elastic member 177, and the receiving groove 173 can play a role in limiting the first elastic member 177 to ensure the stable expansion and contraction of the first elastic member 177 in the up and down direction.

[0088] According to some embodiments of the present invention, referring to Figure 9 and Figure 13 , a first guiding rib 143 extending in the front-rear direction is formed on the upper surface of the flanging portion 142. The first guiding ribs 143 are multiple and arranged at intervals in the left-right direction, and the connecting seat 16 is supported on the multiple first guiding ribs 143. Thus, through the multiple first guiding ribs 143 provided on the flanging portion 142, the movement of the connecting seat 16 can be guided, and while ensuring the support of the fuselage frame for the connecting seat 16, the contact area between the connecting seat 16 and the fuselage frame can be reduced, the resistance to the front-rear movement of the connecting seat 16 can be reduced, and the movement of the connecting seat 16 can be made smoother.

[0089] According to some embodiments of the present invention, referring to Figure 5 , Figure 15 and Figure 19 , the locking member 17 includes a locking member body 171, a second locking portion 174 is formed on the locking member body 171, the second locking portion 174 is a locking projection formed on the locking member body 171, and the first locking portion 144 is a locking groove formed on the fuselage frame. Thus, by setting the first locking portion 144 as a locking groove and the second locking portion 174 as a locking projection, and by inserting the locking projection into the locking groove, a reliable cooperation between the first locking portion 144 and the second locking portion 174 can be achieved, so that the reliable locking of the connecting seat 16 and the fuselage frame support can be realized, and the structures of the first locking portion 144 and the second locking portion 174 are simple.

[0090] Optionally, the surfaces of the locking projection and the locking groove that cooperate with each other are both cylindrical surfaces. Thus, when the locking member 17 moves in the up and down direction, the friction between the first locking portion 144 and the second locking portion 174 can be reduced, and thus the resistance when the locking member 17 moves up and down can be reduced.

[0091] In some alternative embodiments of the present invention, the locking member 17 includes a mating protrusion 175, which is connected to the locking member body 171 by an elastic arm 176. The mating protrusion 175 is located directly above the second locking portion 174. Both the mating protrusion 175 and the second locking portion 174 (i.e., the above-mentioned locking protrusion) cooperate with the same first locking portion 144. When the connecting seat 16 moves, the mating protrusion 175 can move from one of the plurality of first locking portions 144 (i.e., the above-mentioned locking grooves) to another one of the plurality of first locking portions 144.

[0092] Thus, by providing the mating protrusion and making the mating protrusion 175 connected to the locking member body 171 by the elastic arm 176, through the elastic deformation of the elastic arm 176, the mating protrusion 175 can be driven to elastically deform, so that through the elastic deformation of the mating protrusion 175, it is convenient for the mating protrusion 175 to disengage from one first locking portion 144 in the front-rear direction and move across the protrusion between two adjacent first locking portions 144 to another first locking portion 144. Thus, when the connecting seat 16 moves in the front-rear direction, it can be conveniently judged whether the locking member 17 has moved to the set position by whether the mating protrusion 175 has moved into a certain first locking portion 144. When the mating protrusion 175 moves into a certain first locking portion 144, the locking member 17 can be moved upward so that the second locking portion 174 of the locking member 17 cooperates within the first locking portion 144. In addition, when the second locking portion 174 cooperates with the corresponding first locking portion 144, the mating protrusion 175 cooperates with the same first locking portion 144, which can further increase the mating area between the locking member 17 and the first locking portion 144 and improve the reliability of the locking between the connecting seat 16 and the fuselage frame.

[0093] Optionally, referring to Figure 19 , the surface of the mating protrusion 175 that cooperates with the first locking portion 144 is a spherical surface. Thus, it is convenient for the mating protrusion 175 to disengage from or cooperate with the first locking portion 144 when moving in the front-rear direction, reducing the moving resistance of the mating protrusion 175 when moving back and forth.

[0094] According to some embodiments of the present invention, the functional component 2 is detachably connected to the connecting seat 16. Thus, it is convenient for the maintenance and replacement of the functional component 2. And when manually moving the connecting seat 16, the functional component 2 can be detached from the connecting seat 16. After the connecting seat 16 moves to the set position and is locked, the functional component 2 is then connected to the connecting seat 16, so that the front-rear movement of the connecting seat 16 can be time-saving and labor-saving.

[0095] According to some alternative embodiments of the present invention, referring to Figure 8 、 Figure 16 and Figure 18, the connecting seat 16 includes: a connecting portion 161 and a mounting portion 162. The connecting portion 161 extends in the left-right direction. The functional component 2 can be connected to the mounting portion 162 or the connecting portion 161. There are two mounting portions 162 which are respectively arranged at the left and right ends of the connecting portion 161. A part of the functional component 2 is located within the fitting space defined by the two mounting portions 162 and the connecting portion 161. Second guiding ribs 1625 extending in the up-down direction are respectively formed on the left and right side walls of the fitting space. Thus, by providing the second guiding ribs 1625 on the left and right side walls of the above-mentioned fitting space, when the functional component 2 is installed or disassembled, the functional component 2 moves in the up-down direction. The second guiding ribs 1625 can play a guiding role in the installation or disassembly operation of the functional component 2, and can reduce the sliding fitting area between the functional component 2 and the connecting seat 16 when the functional component 2 moves up and down, reducing the resistance of the functional component 2 to move, making the installation and disassembly of the functional component 2 more convenient and labor-saving.

[0096] According to some alternative embodiments of the present invention, referring to Figure 8 , Figure 10 , Figure 16 , Figure 17 , Figure 23 and Figure 24 , the functional component 2 is a battery module. The battery module includes a battery housing 21 and a battery 23 provided in the battery housing 21. A stepped portion 22 is formed on one side of the battery housing 21. The stepped portion 22 is adapted to be supported on the connecting seat 16. Limiting grooves 221 are respectively formed on the opposite two side walls of the stepped portion 22. Limiting protrusions 163 that cooperate with the limiting grooves 221 are provided on the connecting seat 16. Thus, by providing the stepped portion 22 on the battery housing 21 and through the cooperation of the limiting grooves 221 formed on the side walls of the stepped portion 22 and the limiting protrusions 163 on the connecting seat 16, the battery module can be detachably connected to the connecting seat 16, and the battery module can be limited in all directions, making the installation and fixation of the battery module reliable.

[0097] Furthermore, referring to Figure 8 , Figure 10 , Figure 16 , Figure 17 and Figure 20, the connection base 16 includes: a connection portion 161 and a mounting portion 162. The connection portion 161 extends in the left - right direction. The step portion 22 is adapted to be supported on the connection portion 161, which can play a supporting role for the battery module. There are two mounting portions 162, which are respectively arranged at the left and right ends of the connection portion 161. A part of the battery module is located within the fitting space defined by the two mounting portions 162 and the connection portion 161. Guide holes 1624 are respectively provided on the left and right side walls of the fitting space. The limit protrusions 163 are telescopically inserted into the corresponding guide holes 1624. Thus, by telescopically inserting the limit protrusions 163 into the corresponding guide holes 1624, the installation of the battery module is facilitated and the reliable installation of the battery module can be ensured. Moreover, the guide holes 1624 also have a guiding effect on the telescoping of the limit protrusions 163.

[0098] For example, when connecting and mating the battery module with the connection base 16, during the process of the step portion 22 of the battery module moving downward to be supported on the connection portion 161, the left and right side walls of the step portion 22 squeeze the limit protrusions 163, squeezing the limit protrusions 163 into the guide holes 1624. When the step portion 22 is completely supported on the connection portion 161, the limit protrusions 163 are opposite to the limit grooves 221 on the step portion 22, and at this time, a part of the limit protrusions 163 extends out of the guide holes 1624 and extends into the limit grooves 221, so that the battery module can be installed and fixed. When removing the battery module from the connection base 16, during the process of the step portion 22 of the battery module moving upward to disengage from the connection portion 161, the left and right side walls of the step portion 22 squeeze the limit protrusions 163, squeezing the limit protrusions 163 into the guide holes 1624, and the limit protrusions 163 are disengaged from the limit grooves 221 on the step portion 22, so that the battery module can be removed.

[0099] Optionally, referring to Figure 10 , Figure 17 and Figure 20 , the adjusting assembly includes: a second elastic member 164. A second installation groove 1623 is formed on the mounting portion 162. The second elastic member 164 is arranged in the second installation groove 1623 and the second elastic member 164 is telescopic along the central axis direction of the guide hole 1624 (for example, the left - right direction). One end of the second elastic member 164 is connected to the limit protrusion 163, and the other end of the second elastic member 164 is connected to the side wall of the second installation groove 1623. Thus, by providing the second elastic member 164, through the telescoping of the second elastic member 164 along the central axis direction of the guide hole 1624, the telescoping of the limit protrusions 163 can be conveniently realized.

[0100] Optionally, referring to Figure 16 , Figure 17 and Figure 24, a positioning protrusion 1612 is formed on one of the top of the connecting portion 161 and the bottom of the stepped portion 22, and a positioning groove 222 cooperating with the positioning protrusion 1612 is formed on the other. For example, when the positioning protrusion 1612 is formed on the top of the connecting portion 161, the positioning groove 222 cooperating with the positioning protrusion 1612 is formed on the bottom of the stepped portion 22; when the positioning protrusion 1612 is formed on the bottom of the stepped portion 22, the positioning groove 222 cooperating with the positioning protrusion 1612 is formed on the top of the connecting portion 161. Thus, through the cooperation of the positioning protrusion 1612 and the positioning groove 222, the connection strength and reliability between the battery module and the connection base 16 can be further improved.

[0101] In some alternative embodiments of the present invention, Figure 8 , Figure 16 , Figure 23 and Figure 24 , a first through hole 1611 adapted for the male end of the electrical connector to pass through is formed on the connecting portion 161, and a second through hole 223 adapted for the female end 24 of the electrical connector to pass through is formed on the stepped portion 22, and the first through hole 1611 and the second through hole 223 are arranged oppositely. Thus, the plug-in cooperation of the male end and the female end 24 of the electrical connector is facilitated, so that the battery module can supply power to other components of the aircraft 100.

[0102] The aircraft 100 according to the second aspect embodiment of the present invention includes: a fuselage 1, and the fuselage 1 is the fuselage 1 according to the above first aspect embodiment of the present invention.

[0103] According to the aircraft 100 of the embodiment of the present invention, by providing the above-mentioned fuselage 1, when the hanging of the fuselage 1 of the aircraft 100 changes, the position of the functional component 2 can be adjusted through the adjusting assembly, so that the center of gravity of the aircraft 100 can be adjusted, so that the center of gravity of the aircraft 100 can be changed according to the hanging weight, so that the center of gravity of the aircraft 100 is adjusted to a position where the overall aircraft 100 is relatively balanced, so that the flight performance and the economy and safety of the use of the aircraft 100 are greatly improved.

[0104] Next, refer to Figures 1 - 25 to describe the aircraft 100 according to an embodiment of the present invention. The aircraft 100 is a fixed-wing unmanned aircraft 100.

[0105] In this embodiment, refer to Figure 1 and Figure 6 , the aircraft 100 has a left-right symmetric structure, and the aircraft 100 includes: a fuselage 1, a fixed wing 3, wing arms 4, a power assembly, a tail wing component, a functional component 2, a flight control unit, an antenna module, an aerial photography module 9, and a communication module. The aerial photography module 9 is arranged on the front side of the fuselage 1 and is connected to the fuselage 1. Among them, the functional component 2 is a battery module.

[0106] Reference Figure 1 、 Figure 2 and Figure 6 , there are two fixed wings 3, which are respectively arranged on the left and right sides of the fuselage 1. The power assembly includes four first power components 81 and one second power component 82. The four first power components 81 are evenly distributed around the fuselage 1. Each first power component 81 is connected to the fixed wing 3 through a wing arm 4. Each wing arm 4 extends in the front-back direction. Two of the first power components 81 are distributed on the front and back sides of the fixed wing 3 on the left side, and the other two first power components 81 are distributed on the front and back sides of the fixed wing 3 on the right side. One second power component 82 is connected to the rear end of the fuselage 1. The tail wing component is arranged on the rear side of the fuselage 1 and behind the second power component 82. The tail wing component includes a tail strut 6 assembly and a tail wing 5. There are two tail strut 6 assemblies, which are respectively located on the left and right sides of the tail wing 5. The two tail strut 6 assemblies are respectively connected to two wing arms 4 located behind the fixed wing 3.

[0107] Reference Figure 1 and Figure 6 , the fuselage 1 includes a fuselage frame and a fuselage outer shell 11 wrapped around the outside of the fuselage frame. The fuselage outer shell 11 is streamlined, which can reduce the flight resistance of the aircraft 100. The fuselage frame includes a first fixed frame 14 and a second fixed frame 15 arranged and connected in the front-back direction. An accommodation cavity 141 with an open upper end is defined in the first fixed frame 14, and a receiving cavity 151 with an open lower end is defined in the second fixed frame 15. The battery module is installed in the accommodation cavity 141, and the flight control unit, antenna module and communication module are all installed in the receiving cavity 151.

[0108] Reference Figure 6 , a first installation opening 111 and a second installation opening are respectively formed at the top and bottom of the fuselage outer shell 11. The first installation opening 111 corresponds to the first fixed frame 14. The battery module accommodated in the first fixed frame 14 can be taken out from the first installation opening 111 or loaded into the first fixed frame 14 from the first installation opening 111. The second installation opening is arranged opposite to the second fixed frame 15, which is convenient for the installation and removal of the flight control unit, antenna module and communication module in the second fixed frame 15.

[0109] Reference Figure 1 、 Figures 3 - 6 , a fuselage upper cover 12 is provided at the first installation opening 111. The fuselage upper cover 12 is detachably connected to the fuselage outer shell 11. A fuselage lower cover is provided at the second installation opening. The fuselage lower cover is detachably connected to the fuselage outer shell 11. The fuselage lower cover includes a lower cover body 131 and a heat dissipation shell provided on the lower cover body 131. The heat dissipation shell has a plurality of heat dissipation fins 1321. Among them, the inner surface of the heat dissipation shell can be used to fix the communication module, so that the heat generated by the communication module can be quickly exported to the outside of the fuselage 1.

[0110] Referring to Figure 8 、 Figure 9 、 Figures 13 - 15 ,On the top of the left and right side walls of the first fixing frame 14, flanging parts 142 extending outward (the outer refers to the direction away from the center of the first fixing frame 14) are respectively formed. On each flanging part 142, a guiding groove 1421 extending in the front-rear direction is formed. On the upper surface of each flanging part 142, two first guiding ribs 143 extending in the front-rear direction are respectively formed. The two first guiding ribs 143 on each flanging part 142 are located on the left and right sides of the corresponding guiding groove 1421. On the left and right outer wall surfaces of the first fixing frame 14, a plurality of first locking parts 144 arranged at intervals in the front-rear direction are respectively formed. Each first locking part 144 is a locking groove, and one of the locking grooves penetrates upward through the flanging part 142 to communicate with the corresponding guiding groove 1421.

[0111] Referring to Figures 8 - 12 and Figures 16 - 18 ,The fuselage 1 further includes an adjusting assembly for adjusting the position of the battery module. The adjusting assembly includes a connecting seat 16, a locking assembly for locking the connecting seat 16 on the fuselage frame, a first fixing seat 18, and a second fixing seat 19. Among them, the connecting seat 16 includes a connecting portion 161 extending in the left-right direction and two mounting portions 162. The two mounting portions 162 are respectively connected to the left and right ends of the connecting portion 161. A fitting space is defined between the connecting portion 161 and the two mounting portions 162. A first through hole 1611 and two positioning protrusions 1612 are formed on the connecting portion 161. The first through hole 1611 is located in the middle of the connecting portion 161, and the two positioning protrusions 1612 are located on the left and right sides of the first through hole 1611. On the left and right side walls of the fitting space, two second guiding ribs 1625 extending in the up-down direction are respectively formed. The second guiding ribs 1625 are formed on the side walls of the mounting portions 162 facing the fitting space. A first mounting groove 1621 and a second mounting groove 1623 are formed on each mounting portion 162. Among them, the first mounting groove 1621 penetrates downward through the mounting portion 162 and is opposite to and communicates with the guiding groove 1421. A first stopping portion 1622 is formed on the inner peripheral wall of the first mounting groove 1621. A guiding hole 1624 is formed on the side wall of the second mounting groove 1623 adjacent to the fitting space. The guiding hole 1624 communicates the second mounting groove 1623 and the fitting space.

[0112] Referring to Figure 10 and Figure 17, a limiting protrusion 163 that is telescopically movable in the left - right direction is disposed in the guiding hole 1624. The limiting protrusion 163 includes a first limiting section 1631 and a second limiting section 1632 with different cross - sectional areas. The cross - sectional area of the second limiting section 1632 is larger than that of the first limiting section 1631, and the outer surface of the first limiting section 1631 is a spherical surface. The second limiting section 1632 has a mounting hole 1633, and one end of the second elastic member 164 extends into the mounting hole 1633 to be connected to the second limiting section 1632.

[0113] Referring to Figure 9 and Figure 19 , the locking assembly includes a locking member 17 and a first elastic member 177. The locking member 17 includes a locking member body 171 and a stop protrusion 172 formed on the locking member body 171. The stop protrusion 172 is formed at the upper end of the locking member body 171. Two receiving grooves 173 are formed on the locking member body 17. The stop protrusion 172 constitutes the top wall of the receiving groove 173, and the bottom of the receiving groove 173 is open. The first elastic member 177 is received in the receiving groove 173. A second locking portion 174 and a mating protrusion 175 are provided at the lower end of the locking member body 171. The second locking portion 174 is a locking protrusion, and the mating protrusion 175 is located directly above the second locking portion 174. The mating protrusion 175 is connected to the locking member body 171 through an elastic arm 176.

[0114] Referring to Figure 21 and Figure 22 , an avoidance notch 181 is formed on the first fixing seat 18, and a first avoidance hole 191 and a second avoidance hole 192 are formed on the second fixing seat 19.

[0115] Referring to Figure 23 and Figure 24 , the battery module includes a battery housing 21 and a battery 23 disposed in the battery housing 21. A stepped portion 22 is formed at the rear side of the battery housing 21. Limiting grooves 221 are respectively formed on the left and right side walls of the stepped portion 22, and two positioning grooves 222 are formed at the bottom of the stepped portion 22. A second through - hole 223 suitable for the female end 24 of the electrical connector to pass through is formed on the stepped portion 22.

[0116] When installing the adjusting component to the first fixing frame 14, the connecting seat 16 can be first placed on the top of the first fixing frame 14. At this time, the two mounting parts 162 of the connecting seat 16 are respectively supported on the flanging parts 142 of the first fixing frame 14, and the two mounting parts 162 are respectively arranged opposite to the guiding grooves 1421 on the two flanging parts 142. Install the first elastic member 177 into the receiving groove 173 of the locking member 17, so that the top end of the first elastic member 177 abuts or is connected to the stop protrusion 172. Install the locking member 17 into the first mounting groove 1621, the lower end of the first elastic member 177 abuts against the first stop portion 1622 in the first mounting groove 1621, the lower end of the locking member 17 passes downward through the bottom of the first mounting groove 1621 and through the guiding groove 1421 on the flanging part 142. The second locking portion 174 of the locking member 17 first cooperates with the first locking portion 144 that penetrates the flanging part 142 among the plurality of first locking portions 144, so that the second locking portion 174 of the locking member 17 can extend downward below the flanging part 142. By moving the connecting seat 16, the second locking portion 174 of the locking member 17 can be made to cooperate with one of the first locking portions 144, and at the same time, the cooperating protrusion 175 of the locking member 17 cooperates with the same first locking portion 144.

[0117] There are two second fixing seats 19, which are respectively installed on the tops of the two mounting parts 162. The first avoidance hole 191 and the second avoidance hole 192 on the second fixing seat 19 are respectively used to avoid the limit protrusion 163 and the locking member 17. The second fixing seat 19 presses against the stop protrusion 172 of the locking member 17 to limit the locking member 17 in the up and down directions. There are two first fixing seats 18, which are respectively located below the two flanging parts 142. The two first fixing seats 18 are arranged opposite to the two mounting parts 162 in the up and down directions. The avoidance notch 181 on the first fixing seat 18 is used to avoid the lower end of the first locking member 17. Connect the first fixing seat 18, the connecting seat 16 and the second fixing seat 19 through fasteners. The second fixing seat 19 can limit the connecting seat 16 in the up and down directions to prevent the connecting seat 16 from falling off the first fixing frame 14. When the connecting seat 16 moves, the first fixing seat 18 and the second fixing seat 19 move together with the connecting seat 16.

[0118] Connect one end of the second elastic member 164 with the second limiting section 1632 of the limit protrusion 163, and install the second elastic member 164 and the limit protrusion 163 into the second mounting groove 1623, so that the other end of the second elastic member 164 abuts or is connected to the side wall of the second mounting groove 1623, and make the first limiting section 1631 of the limit protrusion 163 pass through the corresponding guiding hole 1624. The second limiting section 1632 of the limit protrusion 163 is located in the second mounting groove 1623 and is adapted to abut against the side wall of the second mounting groove 1623.

[0119] When the battery module is connected to the connecting seat 16 and accommodated in the accommodation cavity 141, the stepped portion 22 of the battery housing 21 is supported on the connecting portion 161. The positioning protrusion 1612 on the connecting portion 161 cooperates with the positioning groove 222 on the stepped portion 22. The first limiting segments 1631 of the two limiting protrusions 163 respectively extend into the two limiting grooves 221 on the stepped portion 22, so that the battery module can be installed and fixed.

[0120] When it is necessary to adjust the center of gravity of the battery module, press down the locking member 17. The locking member 17 moves downward so that the second locking portion 174 is disengaged from the first locking portion 144. At this time, the locking of the connecting seat 16 is released, and the mating protrusion 175 of the locking member 17 still cooperates with the first locking portion 144. Move the connecting seat 16 in the front-rear direction, and the battery module moves along with the connecting seat 16 in the front-rear direction. When the connecting seat 16 moves, the locking member 17 moves along the guide groove 1421, and the mating protrusion 175 undergoes elastic deformation. The mating protrusion 175 disengages from one first locking portion 144 in the front-rear direction and moves across the protrusion between two adjacent first locking portions 144 to move into another first locking portion 144. When the mating protrusion 175 of the locking member 17 moves into the first locking portion 144 at the set position, the downward pressing force on the locking member 17 can be released. The locking member 17 moves upward under the action of the first elastic member 177. When the abutting protrusion of the locking member 17 abuts against the second fixing seat 19, the locking member 17 no longer moves upward. At this time, the second locking portion 174 of the locking member 17 cooperates with the first locking portion 144 at the corresponding position, and the mating protrusion 175 and the second locking portion 174 of the locking member 17 cooperate with the same first locking portion 144. Thus, the change and adjustment of the center of gravity of the aircraft can be achieved.

[0121] Refer to Figure 1 、 Figure 2 and Figure 6, each fixed wing 3 includes a first wing segment 31 and a second wing segment 32 that are connected to each other, and the first wing segment 31 and the second wing segment 32 are connected by a fixing part 33. There are two support rods 311 on the first wing segment 31, and the two support rods 311 penetrate the first wing segment 31 in the left-right direction. One end of the first wing segment 31 adjacent to the fuselage 1 is detachably connected to the fuselage 1 through the support rod 311, and one end of the first wing segment 31 away from the fuselage 1 is detachably connected to the fixing part 33 through the support rod 311. The fixing part 33 is provided with two first connection holes respectively cooperating with the two support rods 311. One end of the second wing segment 32 adjacent to the fuselage 1 is detachably connected to the fixing part 33. There are two connecting rods 321 on the second wing segment 32, and the fixing part 33 is provided with two second connection holes 331 respectively cooperating with the two connecting rods 321. Thus, by detachably connecting the fixed wing 3 to the fuselage 1 and setting the fixed wing 3 to include two wing segments that are detachably connected, when the aircraft 100 is in a non-use state, the fixed wing 3 can be removed, and the fixed wing 3 can be further disassembled into two parts, so as to reduce the occupied space of the aircraft 100 and facilitate the transportation and storage of the aircraft 100. One end of the second wing segment 32 away from the fuselage 1 is provided with a winglet. The winglet forms an angle with the second wing segment 32 to hinder the air flow around the upper and lower surfaces of the second wing segment 32 and reduce the damage of the flow around to the lift force.

[0122] Among them, among the above four wing arms 4, two of the wing arms 4 are connected to the front and back sides of one of the fixing parts 33, and the other two wing arms 4 are connected to the front and back sides of the other fixing part 33.

[0123] Optionally, the wing surface of the fixed wing 3 can be made of lightweight materials such as foam to reduce the weight of the aircraft 100. During production and processing, the wing surface of the fixed wing 3 and the fuselage shell 11 can be integrally formed, and a streamlined transition is formed between the wing surface of the fixed wing 3 and the fuselage shell 11, which can reduce the air resistance during flight.

[0124] Furthermore, a pitot tube can be provided at the front edge of the first wing segment 31. The pitot tube can be used to measure the air flow velocity during the flight of the aircraft 100 to provide flight parameters for the flight of the aircraft 100. A communication cable is also connected between the first wing segment 31 and the fuselage 1 so that the pitot tube on the first wing segment 31 can be communicatively connected to the electronic components on the fuselage 1. Preferably, this communication cable can not only realize the communication between the fixed wing 3 and the fuselage 1 but also provide power for the first power component 81 on the fixed wing 3.

[0125] Refer to Figure 1 and Figure 6, ailerons 34 are also provided at the trailing edge position of the second wing segment 32. The ailerons 34 can be turned up and down relative to the fixed wing 3 to control the flight attitude of the aircraft 100. The ailerons 34 include opposite upper and lower surfaces. The upper surface of the ailerons 34 is substantially flush with the top surface of the second wing segment 32, and the lower surface of the ailerons 34 is substantially flush with the bottom surface of the second wing segment 32. A servo for driving the ailerons 34 to turn is provided inside the first wing segment 31 or on the fixing part 33. The servo can control the wing surface of the ailerons 34, thereby controlling the flight direction of the aircraft 100. Specifically, the servo for driving the ailerons 34 to turn is provided inside the first wing segment 31 or on the fixing part 33. The output shaft of the servo passes through the side wall of the fixing part 33 and is connected to the ailerons 34 through a connecting component to drive the ailerons 34 to rotate.

[0126] The first power component 81 is used to provide the flight power for the vertical takeoff and landing of the aircraft 100, enabling the unmanned aircraft 100 to take off and land vertically. Specifically, the first power component 81 includes a first power unit 811 connected to the wing arm 4 and a first propeller 812 connected to the first power unit 811. Further, a line channel is provided inside each wing arm 4, and the line channel is used to accommodate the cable connecting the first power unit 811 and the first wing segment 31, so as to supply power to the first power unit 811 through the circuit inside the first wing segment 31. In addition, the cable also includes a communication cable, and the connection through the communication cable enables the fuselage 1 to obtain information such as the rotation speed of the propeller. The second power component 82 includes a second power unit 821 and a second propeller 822 connected to the second power unit 821. The second power unit 821 is fixed at the rear side of the second fixing frame 15.

[0127] Refer to Figure 1 and Figure 6 , each tail strut 6 assembly includes a tail strut 6 extending in the front-rear direction and a tail support 7. The tail support 7 is sleeved on the rear end of the tail strut 6, and the front end of the tail strut 6 is connected to the corresponding wing arm 4. The tail fin 5 includes two tail fin plates 51 arranged in an inverted V shape. The inverted V-shaped tail fin 5 combines the functions of the vertical fin and horizontal stabilizer of a common fixed wing 3, with a small structural weight and high control efficiency. Two plug-in protrusions are provided at the first end of each tail fin plate 51, and corresponding plug-in holes are provided on the corresponding tail support 7 to cooperate with the two plug-in protrusions respectively, so that the tail fin 5 can be disassembled to reduce the occupied space of the aircraft 100. Further, the second ends of the two tail fin plates 51 are rotatably connected, so that the two tail fin plates 51 can be folded with each other, reducing the storage space of the disassembled tail fin 5.

[0128] Refer to Figure 1 and Figure 6, first pivot joints are provided on both wing arms 4 located at the rear side of the fixed wing 3, and second pivot joints are provided at the front ends of each tail strut 6. The first pivot joint and the second pivot joint are rotatably connected. A buckle is provided on the first pivot joint, and a slot is provided on the second pivot joint. The buckle and the slot are oppositely arranged at the rotational connection position of the first pivot joint and the second pivot joint. Thus, after the tail wing 5 is removed, by relatively rotating the second pivot joint and the first pivot joint, the relative rotation of the tail strut assembly with respect to the wing arm 4 can be achieved, so that the tail strut assembly rotates to the storage position to further reduce the occupied space of the aircraft 100.

[0129] Referring to Figure 1 and Figure 6 , the tail wing component further includes a movable control surface 52 provided on the tail wing 5. A servo motor for driving the movable control surface 52 to rotate is provided in the tail strut base 7. By controlling the rotation angle of the movable control surface 52, the flight attitude of the aircraft 100 can be controlled. The output shaft of the servo motor passes through the side wall of the tail strut base 7 and is detachably connected to the movable control surface 52. Thus, by arranging the servo motor for driving the movable control surface 52 to rotate on the tail strut 6 assembly and simultaneously detachably connecting the output shaft of the servo motor to the movable control surface 52, when the tail wing 5 is removed from the tail strut 6 assembly or when the tail wing 5 is installed on the tail strut 6 assembly, it is convenient for the servo motor and the movable control surface 52 to be quickly separated and connected, avoiding the setting of communication cables on the tail wing 5, reducing the processing cost of the tail wing 5, and at the same time avoiding the need to add communication cable connectors between the tail wing 5 and the tail strut 6 assembly during the disassembly and assembly process, greatly increasing the reliability of the aircraft 100.

[0130] In the description of this specification, the description with reference to terms such as "one embodiment", "some embodiments", "illustrative embodiments", "examples", "specific examples", or "some examples" means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0131] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and purposes of the present invention. The scope of the present invention is defined by the claims and their equivalents.

Claims

1. The fuselage of an aircraft, characterized in that, Comprising: A fuselage frame, within which a receiving cavity adapted to accommodate functional components is defined. The upper end of the receiving cavity is open. Flanging portions are respectively formed on the left side wall and the right side wall of the receiving cavity. Guide grooves penetrating the flanging portions in the vertical direction are formed on the flanging portions. The guide grooves extend in the front-rear direction. A plurality of first locking portions arranged at intervals in the front-rear direction are formed on the fuselage frame. A plurality of the first locking portions are respectively formed at positions corresponding to the guide grooves on the left and right outer wall surfaces of the receiving cavity. An adjusting assembly for adjusting the position of the functional components, the adjusting assembly comprising: A connecting seat, which is movably arranged on the fuselage frame in the front-rear direction. The functional component is adapted to be connected to the connecting seat. The left and right ends of the connecting seat are respectively supported on the flanging portions. A first mounting groove opposite to and communicating with the guide groove is formed on the connecting seat. A first stop portion is formed on the inner peripheral wall of the first mounting groove. A locking assembly for locking the connecting seat on the fuselage frame, the locking assembly comprising a locking member, which is movably arranged on the connecting seat in the vertical direction. A second locking portion is formed on the locking member. The second locking portion is adapted to cooperate with any one of the plurality of first locking portions to lock the connecting seat on the fuselage frame. The locking member can be moved up and down to disengage the second locking portion from the first locking portion. The locking member penetrates through the corresponding guide groove and can move back and forth along the corresponding guide groove. The second locking portion extends downward out of the corresponding guide groove and is adapted to cooperate with the corresponding first locking portion. The locking member is movably arranged in the first mounting groove. The locking member includes a locking member body and a stop projection formed on the locking member body. The locking assembly includes a first elastic member, which is telescopable in the vertical direction. The upper end of the first elastic member abuts against or is connected to the stop projection, and the lower end of the first elastic member abuts against or is connected to the first stop portion.

2. The fuselage of the aircraft according to claim 1, characterized in that, The adjusting assembly includes: a first fixing seat, which is arranged directly below the flanging portion and connected to the connecting seat.

3. The fuselage of the aircraft according to claim 1, characterized in that, The adjusting assembly includes: a second fixing seat, which is arranged on the top of the connecting seat and connected to the connecting seat. In the vertical direction, the upper end surface of the stop projection is adapted to abut against the second fixing seat.

4. The fuselage of the aircraft according to claim 1, characterized in that, A receiving groove is formed on the locking member. The stop projection constitutes the top wall of the receiving groove. The bottom of the receiving groove is open. The first elastic member is received in the receiving groove.

5. The fuselage of the aircraft according to claim 1, characterized in that A first guiding rib extending in the front-rear direction is formed on the upper surface of the flanging portion. There are multiple first guiding ribs arranged at intervals in the left-right direction. The connecting seat is supported on the multiple first guiding ribs.

6. The fuselage of the aircraft according to claim 1, characterized in that, The locking member includes a locking member body, and a second locking portion is formed on the locking member body. The second locking portion is a locking projection formed on the locking member body. The first locking portion is a locking groove formed on the fuselage frame.

7. The fuselage of the aircraft according to claim 6, characterized in that, The surfaces of the locking protrusions and the locking grooves that cooperate with each other are all cylindrical surfaces.

8. The fuselage of the aircraft according to claim 6, characterized in that, The locking member includes a mating protrusion. The mating protrusion is connected to the locking member body through an elastic arm. The mating protrusion is located directly above the second locking portion. The mating protrusion and the second locking portion both cooperate with the same first locking portion. When the connecting seat moves, the mating protrusion can move from one of the multiple first locking portions to another of the multiple first locking portions.

9. The fuselage of the aircraft according to claim 8, characterized in that, The surface of the mating protrusion that cooperates with the first locking portion is a spherical surface.

10. The fuselage of the aircraft according to claim 1, characterized in that, The functional component is a battery module.

11. The fuselage of the aircraft according to claim 1, characterized in that, The functional component is detachably connected to the connecting seat.

12. The fuselage of the aircraft according to claim 11, characterized in that, The connecting seat includes: A connecting portion that extends in the left-right direction; Mounting portions, there are two mounting portions and they are respectively provided at the left and right ends of the connecting portion. A part of the functional component is located in the fitting space defined by the two mounting portions and the connecting portion. Second guiding ribs extending in the up-down direction are respectively formed on the left and right side walls of the fitting space.

13. The fuselage of the aircraft according to claim 11, characterized in that, The functional component is a battery module. The battery module includes a battery housing and a battery provided in the battery housing. A stepped portion is formed on one side of the battery housing. The stepped portion is adapted to be supported on the connecting seat. Limiting grooves are respectively formed on the opposite two side walls of the stepped portion. Limiting protrusions that cooperate with the limiting grooves are provided on the connecting seat.

14. The fuselage of the aircraft according to claim 13, characterized in that, The connecting seat includes: A connecting portion that extends in the left-right direction. The stepped portion is adapted to be supported on the connecting portion; Mounting portions, there are two mounting portions and they are respectively provided at the left and right ends of the connecting portion. A part of the battery module is located in the fitting space defined by the two mounting portions and the connecting portion. Guide holes are respectively provided on the left and right side walls of the fitting space. The limiting protrusions are telescopically inserted into the corresponding guide holes.

15. The fuselage of the aircraft according to claim 14, characterized in that, Including: a second elastic member. A second mounting groove is formed on the mounting portion. The second elastic member is provided in the second mounting groove and the second elastic member is telescopable along the central axis direction of the guide hole. One end of the second elastic member is connected to the limiting protrusion, and the other end of the second elastic member is connected to the side wall of the second mounting groove.

16. The fuselage of the aircraft according to claim 14, characterized in that, A positioning protrusion is formed on one of the top of the connecting portion and the bottom of the stepped portion, and a positioning groove that cooperates with the positioning protrusion is formed on the other.

17. The fuselage of the aircraft according to claim 14, characterized in that, A first through hole through which the male end of the electrical connector is adapted to pass is formed on the connecting portion. A second through hole through which the female end of the electrical connector is adapted to pass is formed on the stepped portion. The first through hole and the second through hole are oppositely arranged.

18. An aircraft, characterized in that, Including: A fuselage, the fuselage is the fuselage according to any one of claims 1-17.

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