aircraft

Abstract

This application relates to the field of flight equipment technology and discloses an aircraft. The aircraft includes multiple wing assemblies, a fuselage, and a cover. The fuselage comprises multiple segments, each segment being fixedly connected to at least one wing assembly. The multiple segments circumferentially enclose the fuselage to form it. An opening is formed at one end of the fuselage along a first direction. Each segment has a first connecting portion. The first connecting portions on adjacent segments are arranged along the first direction and fit together. A fixing hole is formed on the first connecting portion, the axis of which is parallel to the first direction. The opening allows fasteners to enter the fuselage and pass through the fixing hole along the first direction to fix adjacent segments together. The cover covers the opening along the first direction and engages with the fuselage. This method eliminates the need for threaded holes and screws on the fuselage surface, improving the aircraft's appearance and flight stability.

Description

Technical Field

[0001] This application relates to the field of flight equipment technology, specifically to an aircraft. Background Technology

[0002] An aircraft is a machine or device capable of flight, such as a drone or an impact vehicle. Currently, aircraft assembly primarily involves drilling threaded holes in the fuselage surface, inserting screws through these holes from the outside of the fuselage, and then tightening the screws. However, the assembled aircraft has numerous exposed holes and screws on its surface, which not only affects its aesthetics but also increases air resistance during flight, thus impacting its performance. Utility Model Content

[0003] In view of the above problems, this application provides an aircraft that can improve the appearance of the aircraft and enhance flight stability.

[0004] According to one aspect of the embodiments of this application, an aircraft is provided, the aircraft comprising: a plurality of wing assemblies; a fuselage comprising a plurality of segments, each segment being fixedly connected to at least one wing assembly, the plurality of segments surrounding the fuselage in a circumferential direction, an opening being formed at one end of the fuselage along a first direction, the first direction being the axial direction of the fuselage, each segment being provided with a first connecting portion, the first connecting portions on two adjacent segments being arranged along the first direction and fitting together, the first connecting portions being provided with fixing holes, the axial direction of the fixing holes being parallel to the first direction, the opening being used for fasteners to enter the interior of the fuselage, and for fasteners to pass through the fixing holes of the plurality of fitting first connecting portions along the first direction, so as to fix two adjacent segments together; a cover member covering the opening along the first direction and engaging with the fuselage.

[0005] In one alternative embodiment, a head assembly is provided at one end of the back opening of the body, and each split back opening is provided at one end with a first through hole; the first through hole is used for fasteners that enter the body through the opening to pass through and be fixedly connected to the head assembly, so as to fix the head assembly to the body.

[0006] In one alternative approach, each component has a recess at its edge away from the opening, and the head assembly has a protrusion at its edge facing the body, the protrusion extending into the recess to radially limit each component.

[0007] In one alternative approach, the aircraft is used to strike the drone, with the nose assembly made of metal.

[0008] In one alternative embodiment, a mounting groove is provided on the outer side of the split body, and a second connecting part is provided on the wing assembly, which is inserted into the mounting groove; the wall of the mounting groove is provided with a plurality of second through holes that connect the internal space of the mounting groove and the internal space of the split body, and the second through holes are used for fasteners to pass through the inside of the split body and be fixedly connected to the second connecting part in the mounting groove, so as to fix the wing assembly to the split body.

[0009] In one alternative embodiment, the fuselage is formed by two parts fastening together. Each part has a mounting groove at both ends of its circumferential edge, and a second connecting part of a wing assembly is inserted into each mounting groove. The mounting groove has a fan-shaped cross-section along the radial direction of the fuselage. The mounting groove has a first wall and a second wall protruding from the surface of the part inside the part. Both the first wall and the second wall have a plurality of second through holes arranged along a first direction. Each second through hole allows a fastener to pass through and be fixedly connected to the wing assembly.

[0010] In one alternative embodiment, the plurality of components include a first component and a second component arranged adjacent to each other; the first component has at least two first connecting portions spaced apart, and the second component has at least one first connecting portion. The first connecting portions on the second component are inserted into the gap between two adjacent first connecting portions on the first component, such that the plurality of first connecting portions are attached to each other and arranged along a first direction, so that fasteners can be inserted and connected sequentially along the first direction.

[0011] In one alternative embodiment, a receiving cavity is formed inside the fuselage, and a power module is disposed on the cover. The power module is inserted into the receiving cavity through the opening in a first direction when the cover covers the opening.

[0012] In one alternative embodiment, a latching member is slidably disposed on the end of the cover facing the opening along the radial direction of the body. The latching member includes a pressing portion extending radially to the outside of the cover and a latching portion extending in a first direction toward the outside of the cover. An elastic member is disposed between the latching member and the cover. The elastic member is used to provide an elastic force radially toward the body to the latching portion after the latching portion is inserted into the opening, so as to latch and fix the latching portion to the body. The pressing portion is used to compress the elastic member and drive the latching member to slide radially away from the body when pressed, so as to separate the latching portion from the body.

[0013] In one alternative embodiment, the snap-fit ​​components include at least two and are positioned opposite each other at the edges of the cover component.

[0014] This embodiment of the application provides an opening at one end of the fuselage along its axial direction and a first connecting part with a fixing hole on the split body, with the axis of the fixing hole parallel to the axis of the fuselage. This allows fasteners and other fixing tools to enter the interior of the fuselage through the opening when the split bodies are assembled together, and the first connecting parts on adjacent split bodies are arranged and fitted together along the axis of the fuselage. They then pass through the fixing hole of the first connecting part along the axis of the fuselage, fixing the fitted first connecting parts together, thereby achieving fixation of adjacent split bodies from within the fuselage. In an aircraft assembled in this way, the outer surface of the fuselage lacks threaded holes and screws, which not only improves the appearance of the aircraft but also avoids the impact of threaded holes and screws on flight, improving flight stability.

[0015] The above description is only an overview of the technical solution of this application. In order to better understand the technical means of this application and to implement it in accordance with the contents of the specification, and to make the above and other objects, features and advantages of this application more obvious and understandable, the following are specific embodiments of this application. Attached Figure Description

[0016] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0017] Figure 1 A perspective view of the aircraft provided in an embodiment of the present invention is shown;

[0018] Figure 2 An exploded view of the aircraft provided in an embodiment of the present invention is shown;

[0019] Figure 3 An exploded view of the aircraft provided in an embodiment of the present invention is shown;

[0020] Figure 4 A cross-sectional view of the aircraft provided in an embodiment of the present invention is shown in one direction;

[0021] Figure 5 A cross-sectional view of the aircraft provided in an embodiment of the present invention is shown from another direction;

[0022] Figure 6 This image shows a partial exploded view of the aircraft provided in an embodiment of the present invention.

[0023] Figure 7This shows a partial exploded view of the aircraft provided in another embodiment of the present invention;

[0024] Figure 8 It shows Figure 4 Enlarged view of point M in the middle;

[0025] Figure 9 It shows Figure 5 A magnified diagram of point N in the diagram.

[0026] The reference numerals in the detailed embodiments are as follows:

[0027] 1. Aircraft;

[0028] 100. Wing assembly; 200. Fuselage; 300. Canopy assembly; 400. Nose assembly;

[0029] 110. Second connecting part;

[0030] 210. Split body; 220. Opening; 230. Positioning part;

[0031] 211. First connecting part; 212. Fixing hole; 213. First split part; 214. Second split part; 215. First through hole; 216. Recess; 217. Mounting groove; 218. Second through hole; 219. Receiving cavity;

[0032] 310. Power module; 320. Snap-fit ​​component; 321. Pressing part; 322. Snap-fit ​​component; 330. Elastic component;

[0033] 410. Mounting hole; 420. Protrusion;

[0034] 51. First wall; 52. Second wall. Detailed Implementation

[0035] The embodiments of the technical solution of this application will now be described in detail with reference to the accompanying drawings. These embodiments are only used to more clearly illustrate the technical solution of this application and are therefore merely examples, and should not be used to limit the scope of protection of this application.

[0036] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains; the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the application; the terms “comprising” and “having”, and any variations thereof, in the specification, claims, and foregoing description of the drawings are intended to cover non-exclusive inclusion.

[0037] In the description of the embodiments of this application, technical terms such as "first" and "second" are used only to distinguish different objects and should not be construed as indicating or implying relative importance or implicitly specifying the number, specific order, or primary and secondary relationship of the indicated technical features. In the description of the embodiments of this application, "multiple" means two or more, unless otherwise explicitly defined.

[0038] In this document, the term "embodiment" means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0039] In the description of the embodiments in this application, the term "and / or" is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent three cases: A exists, A and B exist simultaneously, and B exists. In addition, the character " / " in this document generally indicates that the related objects before and after it have an "or" relationship.

[0040] In the description of the embodiments of this application, the term "multiple" refers to two or more (including two), similarly, "multiple sets" refers to two or more (including two sets), and "multiple pieces" refers to two or more (including two pieces).

[0041] In the description of the embodiments of this application, the technical terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of this application and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of this application.

[0042] In the description of the embodiments of this application, unless otherwise expressly specified and limited, technical terms such as "installation," "connection," "joining," and "fixing" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. For those skilled in the art, the specific meaning of the above terms in the embodiments of this application can be understood according to the specific circumstances.

[0043] To improve the appearance of an aircraft, this application provides an aircraft whose fuselage comprises multiple parts, and each part has a connecting part on its inner side. When assembling the aircraft, after the multiple parts are enclosed, the connecting parts on two adjacent parts are fixedly connected from the inside of the fuselage to achieve a fixed connection between the two adjacent parts. In this way, the surface of the assembled fuselage does not have threaded holes or screws, which not only improves the appearance of the aircraft but also reduces air resistance and avoids the impact of threaded holes and screws on the flight of the aircraft.

[0044] Furthermore, to ensure proper assembly of the aircraft, when multiple components are circumferentially joined to form the fuselage, an opening is formed at one end of the fuselage along the axial direction, and fixing holes with axial directions parallel to the fuselage's axis are provided on the connecting parts. During aircraft assembly, the connecting parts on adjacent components are arranged along the fuselage's axis and fit together. Fasteners such as screws, pins, or rivets are inserted into the fuselage through the opening and pass through the fixing holes of the multiple fitting connecting parts on the adjacent components along the fuselage's axis, thus stably connecting the two adjacent components together. Finally, a cover is installed at the opening using a snap-fit ​​method to seal it, separating the internal space of the fuselage from the external environment and preventing the opening from affecting the aircraft's flight.

[0045] Please refer to the following first. Figure 1 , Figure 1 A perspective view of an aircraft provided in an embodiment of this application is shown. The aircraft 1 includes multiple wing assemblies 100, a fuselage 200, and a canopy 300.

[0046] Please refer to the following: Figure 2 and Figure 3 , Figure 2 and Figure 3 The explosion structure of the aircraft is shown from two different perspectives. The fuselage 200 includes multiple parts 210, each of which is fixedly connected to at least one wing assembly 100. The multiple parts 210 are arranged circumferentially to form the fuselage 200.

[0047] An opening 220 is formed at one end of the fuselage 200 along a first direction (i.e., the direction indicated by the double arrow Z in the figure). The first direction is the axial direction of the fuselage. Each component 210 is provided with a first connecting part 211. The first connecting parts 211 on two adjacent components 210 are arranged along the first direction and fit together. A fixing hole 212 is provided on the first connecting part 211. The axial direction of the fixing hole 212 is parallel to the first direction. The opening 220 is used to allow fasteners to enter the interior of the fuselage 200 and to allow the fasteners to pass through the fixing holes 212 of the multiple fitting first connecting parts 211 along the first direction, so as to fix two adjacent components 210 together. The cover 300 covers the opening 220 along the first direction and is snapped into the fuselage 200.

[0048] The fuselage 200 is the main structure of aircraft 1, such as Figure 1 As shown, a wing assembly 100 is arranged around the outer periphery of the fuselage 200 to control the flight of the fuselage 200. Specifically, slots or holes can be made in the fuselage 200, and the wing assembly 100 can be inserted into the slots or holes in the fuselage 200 and finally fixed by screws, clips or other structures.

[0049] Since the fuselage 200 is assembled from multiple components 210, when assembling the fuselage 200, the wing assembly 100 can be connected to the corresponding component 210 first, and then the multiple components 210 can be assembled together. Figure 2 and Figure 3 Taking the aircraft shown as an example, the fuselage 200 includes two parts 210 (part A and part B in the figure), and each part 210 is provided with two wing assemblies 100. Figure 2 Taking the shown perspective as an example, when assembling aircraft 1, first connect the upper left and upper right wing components 100 to the left and right sides of component A respectively, and connect the lower left and lower right wing components 100 to the left and right sides of component B respectively. Finally, fasten the two components 210 together. Of course, the fuselage 200 can also be formed by two or more components 210. When assembling the fuselage 200, connect the wing components 100 to the corresponding components 210 respectively, and then connect two or more components 210 one by one around the circumference.

[0050] like Figure 2 and Figure 3 As shown, the first connecting part 211 can be a protrusion located inside the split body 210. When the two split bodies 210 in the figure are fastened together, the first connecting part 211 on split body A will extend into the interior of split body B, and the first connecting part 211 on split body B will extend into the interior of split body A, and so on. Figure 4 and Figure 5 As shown, the parts are arranged and fitted together in the direction indicated by the double arrow Z. Fasteners are then inserted and connected to the fitted first connecting parts 211 in the same direction as the double arrow Z, thus fixing parts A and B together. Figure 4 and Figure 5 The cross-sectional structures of the aircraft are shown from two different directions.

[0051] Furthermore, to facilitate the connection between the two components 210, such as Figure 3 and Figure 4As shown, the multiple components 210 include a first component 213 (i.e., component A in the figure) and a second component 214 (i.e., component B in the figure) arranged adjacent to each other. The first component 213 is provided with at least two first connecting parts 211 spaced apart, and the second component 214 is provided with at least one first connecting part 211. The first connecting parts 211 on the second component 214 are inserted into the gap between two adjacent first connecting parts 211 on the second component 214, so that the multiple first connecting parts 211 are attached to each other and arranged along a first direction (i.e., the direction shown by the double arrow Z in the figure), so that fasteners can be inserted and connected sequentially along the first direction.

[0052] Specifically, such as Figure 4 As shown, split body A has a first connecting part C and a first connecting part E spaced apart, while split body B has a first connecting part D. After split body A and split body B are fastened together, the first connecting part D will be inserted between the first connecting part C and the first connecting part E. That is, the first connecting part C, the first connecting part D and the first connecting part E are arranged in the direction shown by the double arrow Z and fit together with each other. Fasteners can be inserted into the first connecting part E, the first connecting part D and the first connecting part C in sequence in the direction shown by the double arrow Z to achieve a fixed connection between split body A and split body B.

[0053] Of course, multiple first connecting parts 211 can be provided on the first part 213 and the second part 214 respectively. When connecting the first part 213 and the second part 214, the first connecting part 211 on one part 210 will be inserted into the gap between two adjacent first connecting parts 211 on the other part 210, so that the first connecting parts 211 on the first part 213 and the second part 214 are arranged in the direction indicated by the double arrow Z and fit together.

[0054] In this structure, on the one hand, the first connecting part 211 on the second part 214 can be positioned by the gap between the multiple first connecting parts 211 on the first part 213, thereby pre-positioning the first part 213 and the second part 214 when assembling the body 200, so as to facilitate the assembly of the body 200; on the other hand, after the first part 213 and the second part 214 are connected, the first connecting part 211 on the first part 213 can also restrict the first connecting part 211 on the second part 214 from moving along the first direction, so as to prevent the second part 214 from moving relative to the first part 213 along the first direction, and ensure the stability of the connection between the first part 213 and the second part 214.

[0055] Since the first connecting portion 211 between the split parts 210 needs to be fixed inside the body 200, after the split parts 210 are assembled to form the body 200, an opening 220 needs to be reserved on the body 200 so that the fasteners can enter the body 200 through the opening 220 and fix the first connecting portion 211. Figure 6 As shown, Figure 6 The diagram shows a partial explosion structure of the aircraft from one perspective. When the first connecting parts 211 on two adjacent parts 210 are aligned in the direction indicated by the double arrow Z, at least one side of the fixing hole 212 on the first connecting part 211 will face the opening 220. At this time, after the fastener enters the fuselage 200 from the opening 220, it passes through the fixing hole 212 on the first connecting part 211 in the direction indicated by the double arrow Z, so that the two adjacent parts 210 can be fixedly connected together inside the fuselage 200.

[0056] Furthermore, the fixing holes 212 on the multiple first connecting parts 211 that fit together can all be set as through holes, so that the multiple first connecting parts 211 can be fixed together by passing fasteners such as pins and rivets through the through holes in sequence. Alternatively, the fixing holes 212 on the first connecting part 211 that is away from the opening 220 can be set as blind holes, and the fixing holes on the other first connecting parts 211 can be set as through holes. Then, the multiple first connecting parts 211 can be fixed together by passing fasteners such as screws and bolts through the through holes in sequence and connecting them to the blind hole on the last first connecting part 211.

[0057] Finally, by covering the opening 220 with the cover 300, the space inside the fuselage 200 can be sealed off. Specifically, the connection between the cover 300 and the fuselage 200 can be achieved by a structure such as a cantilever beam buckle, a ring buckle, or a torsion buckle.

[0058] In the above embodiment, by providing an opening 220 at one end of the fuselage 200 along its axial direction and providing a first connecting portion 211 with a fixing hole 212 on the split body 210, with the axial direction of the fixing hole 212 parallel to the axial direction of the fuselage 200, when the split bodies 210 are assembled together and the first connecting portions 211 on two adjacent split bodies 210 are arranged along the axial direction of the fuselage 200 and fit together, fasteners and other fixing tools can enter the interior of the fuselage 200 through the opening 220 and pass through the fixing hole 212 of the first connecting portion 211 along the axial direction of the fuselage 200, fixing the fitted first connecting portions 211 together, thereby achieving the fixation of two adjacent split bodies 210 inside the fuselage 200. In the aircraft 1 assembled in this way, there are no threaded holes or screws on the outer surface of the fuselage 200, which on the one hand improves the appearance of the aircraft, and on the other hand avoids the impact of threaded holes and screws on the flight of the aircraft, improving the flight stability of the aircraft 1.

[0059] To improve the stability of the fuselage 200 structure, in some embodiments, such as Figure 6 and Figure 7 As shown, a head assembly 400 is provided at one end of the body 200 away from the opening 220, and each component 210 is provided with a first through hole 215 at one end away from the opening 220. The first through hole 215 is used for fasteners that enter the body 200 through the opening 220 to pass through and be fixedly connected to the head assembly 400, so as to fix the head assembly 400 to the body 200.

[0060] The nose assembly 400 can be made of various materials, such as metal, plastic, and rubber. The specific material selection depends on the function of the aircraft 1. As an example, if the aircraft 1 is used to collide with a drone, the nose assembly 400 is the main component used to directly impact the drone and cause physical damage. Therefore, the nose assembly 400 needs to be made of a high-hardness material, such as stainless steel or alloy steel, to ensure that after the aircraft 1 impacts the drone, it causes physical damage to the drone while not suffering serious damage itself.

[0061] When installing the head assembly 400, such as Figure 6 and Figure 7As shown, multiple components 210 are first assembled to form the fuselage 200. That is, the multiple components 210 are first assembled together to form the component located in the middle position in the figure. Then, the nose assembly 400 is placed over the fuselage 200 at the end opposite the opening 220. Finally, fasteners enter the fuselage 200 through the opening 220 and pass through the first through hole 215 to be fixedly connected to the nose assembly 400. As an example, after passing through the first through hole 215, the fasteners can be inserted into the mounting holes 410 on the nose assembly 400, and the mounting holes 410 are blind holes. This not only ensures that there are no threaded holes, screws, or other structures on the outer surface of the aircraft 1, but also allows the nose assembly 400 to further fix and connect the multiple components together, improving the structural stability of the aircraft.

[0062] Furthermore, in order to improve the structural stability of the fuselage 200, in some embodiments, such as Figure 4 , Figure 7 and Figure 8 As shown, Figure 8 It shows Figure 4 In the enlarged structure at point M, each component 210 has a recess 216 at the edge position away from the opening 220, and the head assembly 400 has a protrusion 420 at the edge position facing the body 200. The protrusion 420 extends into the recess 216 to limit each component 210 radially.

[0063] After the head assembly 400 is placed over the end of the fuselage 200 away from the opening 220, as an example, such as Figure 8 As shown, the multiple components 210 include components A and B located on the left and right sides respectively. The protrusion 420 on the right edge of the head assembly 400 extends into the recess 216 located at the upper right corner of component A, thereby preventing component A from moving to the right. The protrusion 420 on the left edge of the head assembly 400 extends into the recess 216 located at the upper left corner of component B, thereby preventing component B from moving to the left.

[0064] The head assembly 400 can be like Figure 7 As shown, each component 210 has an independent protrusion 420, and each component 210 has a recess 216 only at the position corresponding to the protrusion 420. This allows for pre-positioning of the head assembly 400 during installation using the protrusion 420 and the recess 216, facilitating the installation of the head assembly 400. Alternatively, the head assembly 400 can have a complete ring of protrusions 420 around its edge, and a ring of continuous recesses 216 at the edge of the body 200 away from the opening 220. This allows the head assembly 400 to limit the component 210 along any radial direction, thereby improving the structural stability of the body 200.

[0065] In the above embodiments, by providing a protrusion 420 at the edge of the head assembly 400 and a corresponding recess 216 at the edge of the split body 210, after the head assembly 400 is fixedly connected to the body 200, the protrusion 420 of the head assembly 400 can extend into the recess 216 on the split body 210, thereby preventing each split body 210 from moving radially and improving the structural stability of the body 200.

[0066] Furthermore, to ensure the stability of the connection between the wing assembly 100 and the split body 210, such as Figure 2 and Figure 3 As shown, a mounting groove 217 is provided on the outer side of the split body 210, and a second connecting part 110 is provided on the wing assembly 100. The second connecting part 110 is inserted into the mounting groove 217. A plurality of second through holes 218 are provided on the wall of the mounting groove 217, which connect the internal space of the mounting groove 217 and the internal space of the split body 210. The second through holes 218 are used for fasteners to pass through the inside of the split body 210 and be fixedly connected to the second connecting part 110 in the mounting groove 217, so as to fix the wing assembly 100 to the split body 210.

[0067] The mounting slot 217 is the main structure on the split body 210 used to connect the wing assembly 100. The second through hole 218 can be set on any wall of the mounting slot 217, and can be along... Figure 2 The walls at both ends of the direction indicated by the double arrow Z can also be... Figure 2 On a wall parallel to the direction indicated by the double arrow Z. As an example, such as... Figure 2 and Figure 3 As shown, multiple second through holes 218 can be opened on the wall of the mounting slot 217 parallel to the direction indicated by the double arrow Z in the figure, and each second through hole 218 allows a fastener to pass through and connect to the wing assembly, thereby fixing the same wing assembly 100 with multiple fasteners and ensuring the structural stability between the wing assembly 100 and the fuselage 200.

[0068] To further improve the stability of the connection between the wing assembly 100 and the fuselage 200, second through holes 218 can be opened on multiple walls of the mounting slot 217 to lock and fix the wing assembly 100 in multiple directions. Specifically, it is possible to... Figure 2 and Figure 3The mounting groove 217 shown has second through holes 218 on both ends of its walls along the direction indicated by the double arrow Z. Alternatively, second through holes 218 can be provided on multiple walls of the mounting groove 217 parallel to the direction indicated by the double arrow Z. For example, if the mounting groove 217 has multiple walls parallel to the direction indicated by the double arrow Z, second through holes 218 can be provided on at least two walls. Of course, if the walls of the mounting groove 217 are curved, multiple second through holes 218 can be provided along the circumference of the curved surface to achieve locking and fixing of the wing assembly 100 in multiple directions.

[0069] In the above embodiment, by opening a mounting groove 217 and a second through hole 218 on the wall of the mounting groove 217, the fastener can pass through the second through hole 218 from the inside of the split body 210 and connect with the second connecting part 110 on the wing assembly 100 inside the mounting groove 217. After the aircraft 1 is assembled, the second through hole 218 on the fuselage 200 can be covered by the wing assembly 100, and the fastener is located inside the fuselage 200. Thus, there are no through holes and fasteners on the outer surface of the fuselage 200, which further beautifies the appearance of the aircraft 1.

[0070] Furthermore, in order to reduce the number of components 210 in the fuselage 200, such as... Figure 2 and Figure 3 As shown, the fuselage 200 can be formed by fastening together two separate parts 210. Therefore, when assembling the aircraft 1, simply fasten these two parts 210 together and pass the fasteners through the fixing holes 212 on the first connecting portions 211 on opposite sides of the parts 210 to complete the assembly of the fuselage 200. The assembly process of the fuselage 200 is simple and easy to operate. Furthermore, to ensure that the wing components 100 can provide sufficient power for the flight of the aircraft 1, multiple mounting slots 217 can be provided on each of the two parts 210, and a second connecting portion 110 of a wing component 100 can be inserted into each mounting slot 217. This allows multiple wing components 100 to be connected to one part 210. This reduces the number of parts 210, lowers the difficulty of assembling the fuselage 200, and ensures that the fuselage 200 has enough wing components 100 to provide power for the aircraft 1.

[0071] When the fuselage 200 is formed by fastening together two separate parts 210, in order to ensure that the wing assembly 100 can be fixed from multiple directions, such as... Figure 2 and Figure 3As shown, the split body 210 has mounting grooves 217 at both ends of its circumferential direction, and the mounting grooves 217 have a fan-shaped cross section along the radial direction of the fuselage 200. The mounting grooves 217 have a first wall 51 and a second wall 52 protruding from the surface of the split body 210 inside the split body 210. The first wall 51 and the second wall 52 are provided with a plurality of second through holes 218 arranged along a first direction (i.e., the direction shown by the double arrow Z in the figure). Each second through hole 218 allows a fastener to pass through and be fixedly connected to the wing assembly 100.

[0072] For example Figure 2 Taking the mounting slot 217 on the B-section as an example, after the wing assembly 100 located in the lower left corner of the figure is inserted into the mounting slot 217 located on the left side of the B-section through the second connecting part 110, some fasteners can pass through the second through hole 218 on the first wall 51 along the positive X-axis direction and be fixedly connected to the second connecting part 110, and other fasteners can pass through the second through hole 218 on the second wall 52 along the negative Y-axis direction and be fixedly connected to the second connecting part 110. Thus, the wing assembly 100 in the lower left corner of the figure is fixed to the B-section from both the positive X-axis direction and the negative Y-axis direction, thereby improving the stability of the connection between the wing assembly 100 and the section 210.

[0073] Furthermore, considering that aircraft 1 consumes energy during operation, in order to ensure the stable flight of aircraft 1, in some embodiments, such as Figure 6 and Figure 7 As shown, a receiving cavity 219 is formed inside the body 200, and a power module 310 is provided on the cover 300. When the cover 300 covers the opening 220, the power module 310 is inserted into the receiving cavity 219 from the opening 220 along the first direction (i.e., the direction shown by the double arrow Z in the figure).

[0074] When assembling the housing 200, after the parts 210 are assembled, a receiving cavity 219 is formed inside the housing 200. The receiving cavity 219 provides operating space for fasteners to pass through the fixing holes 212, making it convenient for users to fix the parts 210. In addition, when assembling the power module 310, the power module 310 can be pre-positioned on the cover 300, and then directly assembled into the receiving cavity 219 as the cover 300 is snapped into the housing 200. The installation of the power module 310 is simple and convenient.

[0075] Furthermore, to facilitate the installation and removal of the power module, in some embodiments, such as Figure 5 , Figure 7 and Figure 9 As shown, Figure 9 It shows Figure 5In the enlarged structure at point N, a latching member 320 is slidably disposed radially along the body 200 at one end of the cover 300 facing the opening 220. The latching member 320 includes a pressing portion 321 extending radially to the outside of the cover 300, and a latching portion 322 extending radially away from the body 200 to the outside of the cover 300. An elastic member 330 is disposed between the latching portion 322 and the cover 300. The elastic member 330 is used to provide an elastic force radially toward the body 200 to the latching portion 322 after it extends into the opening 220, so that the latching portion 322 is latched and fixed to the body 200. When pressed, the pressing portion 321 compresses the elastic member 330 and drives the latching member 320 to slide radially away from the body 200, so that the latching portion 322 is separated from the body 200.

[0076] like Figure 7 As shown, the cover 300 is inserted into the body 200 from the opening 220 in the direction indicated by the double arrow Z, so that the snap-fit ​​part 322 is as shown. Figure 9 The cover 300 is inserted into a groove on the inner wall of the body 200. At this time, the elastic element 330 provides an elastic force along the positive Y-axis to the locking part 322, so that the locking part 322 is locked and fixed to the body 200. When it is necessary to remove the cover 300 from the body 200, it is only necessary to apply pressure along the negative Y-axis to the pressing part 321, so that the pressing part 321 slides inward into the cover 300. At this time, the pressing part 321 will drive the locking part 322 to slide along the negative Y-axis, so that the locking part 322 separates from the body 200, and then the cover 300 can be moved away from the body 200 in the direction indicated by the double arrow Z, and removed from the body 200.

[0077] In addition, such as Figure 5 As shown, at least one snap-fit ​​member 320 can also be provided at the edges of opposite sides of the cover 300, so that after the cover 300 is installed, the snap-fit ​​member 320 can be snapped and fixed to the body 200 at multiple positions. That is, the snap-fit ​​member 320 located on the left side of the figure will be subjected to the elastic force applied by the elastic member 330 in the positive direction of the Y-axis, thereby snapping with the left wall of the body 200, while the snap-fit ​​member 320 located on the right side of the figure will be subjected to the elastic force applied by the elastic member 330 in the negative direction of the Y-axis, and snapping with the right wall of the body 200, thereby improving the stability of the connection between the cover 300 and the body 200.

[0078] In the above embodiments, by providing a snap-fit ​​member 320 on the cover 300 and an elastic member 330 abutting between the snap-fit ​​member 320 and the cover 300, the snap-fit ​​member 320 can automatically snap into the body 200 under the elastic force of the elastic member 330 after the cover 300 is inserted into the body 200, thereby realizing the quick installation of the power module 310. When it is necessary to replace or maintain the power module 310, the power module 310 can be quickly removed from the body 200 by applying pressure to the pressing part 321.

[0079] Furthermore, to facilitate the installation of the cover component 300, such as Figure 2 and Figure 3 As shown, a positioning part 230 is provided at the edge of the opening 220 on the body 200. When installing the cover 300, the cover 300 is fitted onto the positioning part 230 to ensure that the cover 300 can completely cover the opening 220.

[0080] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and not to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. These modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application, and they should all be covered within the scope of the claims and specification of this application. In particular, as long as there is no structural conflict, the various technical features mentioned in the embodiments can be combined in any way. This application is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. An aircraft, characterized in that The aircraft includes: Multiple wing components; The fuselage includes multiple segments, each segment being fixedly connected to at least one wing assembly. The multiple segments are circumferentially enclosed to form the fuselage. An opening is formed at one end of the fuselage along a first direction, the first direction being the axial direction of the fuselage. Each segment is provided with a first connecting portion. The first connecting portions on two adjacent segments are arranged along the first direction and fit together. A fixing hole is provided on the first connecting portion. The axial direction of the fixing hole is parallel to the first direction. The opening is used to allow fasteners to enter the interior of the fuselage and to allow the fasteners to pass through the fixing holes of the multiple fitted first connecting portions along the first direction, so as to fix two adjacent segments together. The cover covers the opening along the first direction and engages with the body.

2. The aircraft of claim 1, wherein, An organic head assembly is provided on one end of the body away from the opening, and each of the separate parts is provided with a first through hole on one end away from the opening. The first through hole is used for fasteners that enter the interior of the body through the opening to pass through and be fixedly connected to the head assembly, so as to fix the head assembly to the body.

3. The aircraft according to claim 2, characterized in that, Each of the split components has a recess at the edge opposite to the opening, and the head assembly has a protrusion at the edge facing the body. The protrusion extends into the recess to limit each of the split components radially.

4. The aircraft according to claim 2, characterized in that, The aircraft is designed to strike drones, and the nose assembly is made of metal.

5. The aircraft according to claim 1, characterized in that, The outer side of the split body is provided with a mounting groove, and the wing assembly is provided with a second connecting part, which is inserted into the mounting groove; The wall of the mounting groove is provided with a plurality of second through holes that connect the internal space of the mounting groove and the inner space of the split body. The second through holes are used for fasteners to pass through the inside of the split body and be fixedly connected to the second connecting part in the mounting groove to fix the wing assembly to the split body.

6. The aircraft according to claim 5, characterized in that, The fuselage is formed by two parts being fastened together. Each part has a mounting groove at both ends of its circumferential direction. A second connecting part of the wing assembly is inserted into each mounting groove. The mounting groove has a fan-shaped cross-section along the radial direction of the fuselage. The mounting groove has a first wall and a second wall protruding from the inner side of the split body surface. Both the first wall and the second wall have a plurality of second through holes arranged along the first direction. Each second through hole allows a fastener to pass through and be fixedly connected to the wing assembly.

7. The aircraft according to claim 1, characterized in that, The plurality of said components includes a first component and a second component arranged adjacent to each other; The first split body is provided with at least two first connecting parts at intervals, and the second split body is provided with at least one first connecting part. The first connecting parts on the second split body are inserted into the gap between two adjacent first connecting parts on the first split body, so that multiple first connecting parts are attached to each other and arranged along the first direction, so that fasteners can be inserted and connected sequentially along the first direction.

8. The aircraft according to claim 1, characterized in that, The body has an internal cavity, and a power module is provided on the cover. When the cover covers the opening, the power module is inserted into the cavity from the opening along the first direction.

9. The aircraft according to claim 8, characterized in that, The cover has a snap-fit ​​component that is slidably disposed on one end of the cover facing the opening along the radial direction of the body. The snap-fit ​​component includes a pressing part that extends radially to the outside of the cover and a snap-fit ​​part that extends along the first direction toward the outside of the cover. An elastic element is provided between the snap-fit ​​member and the cover member. The elastic element is used to provide an elastic force to the snap-fit ​​member in the radial direction toward the body after the snap-fit ​​member extends into the opening, so that the snap-fit ​​member is snapped and fixed to the body. The pressing part is used to compress the elastic element when pressed and drive the locking member to slide in the radial direction away from the body, so as to separate the locking part from the body.

10. The aircraft according to claim 9, characterized in that, The snap-fit ​​components include at least two, and are disposed opposite to each other at the edges of the cover component.

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