Automatic wing rotating and unfolding device for fixed-wing unmanned aerial vehicle and unmanned aerial vehicle

Abstract

The invention provides a fixed-wing unmanned aerial vehicle wing automatic rotating and unfolding device and an unmanned aerial vehicle, the fixed-wing unmanned aerial vehicle wing automatic rotating and unfolding device comprises a wing connecting seat assembly, a fuselage connecting seat assembly and a center locking bolt, one end of the wing connecting seat assembly is connected with an unmanned aerial vehicle wing, and the other end is connected with the fuselage connecting seat assembly through the center locking bolt; the fuselage connecting seat assembly is connected with an unmanned aerial vehicle fuselage; the wing connecting seat assembly comprises a wing connecting seat, a spacer sleeve and a guide pin, and the fuselage connecting seat assembly is provided with a torsional spring and a guide groove; a torsion spring arm at the rotating end of the torsion spring is inserted into the wing connecting seat, the guide pin is embedded into the guide groove, the pre-tightening force between the wing connecting seat assembly and the fuselage connecting seat assembly meets the preset requirement after the guide pin is gradually screwed into the guide groove, and the wing connecting seat assembly is in a rotatable state after the fuselage connecting seat assembly and the spacer sleeve are pressed tightly through the center locking bolt. The problems that a low-speed fixed-wing unmanned aerial vehicle is large in storage space and clustering is difficult to achieve can be solved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and particularly to a fixed-wing unmanned aerial vehicle wing automatic rotation and deployment device and an unmanned aerial vehicle.

Background Art

[0002] In recent years, with the development of unmanned aerial vehicle cooperation technology, unmanned aerial vehicle clusters have received extensive attention. Cluster unmanned aerial vehicles have been applied in fields such as agriculture, logistics, urban management, and rescue. For low-speed fixed-wing aircraft, due to their large aspect ratio, the wingspan is usually large, requiring a large storage space.

[0003] In the prior art, in order to store fixed-wing unmanned aerial vehicles, the form of manually installing and disassembling the wings is usually adopted, which cannot fully save the take-off time of the unmanned aerial vehicle, reduce the workload of the operator, and is difficult to achieve a high degree of intelligent clustering. Some of the existing rotating wing structures are complex and difficult to be applied to various models of unmanned aerial vehicles.

[0004] Therefore, it is necessary to study a fixed-wing unmanned aerial vehicle wing automatic rotation and deployment device and an unmanned aerial vehicle to address the deficiencies of the prior art and solve or mitigate one or more of the above problems.

Summary of the Invention

[0005] In view of this, the present invention provides a fixed-wing unmanned aerial vehicle wing automatic rotation and deployment device and an unmanned aerial vehicle, aiming to solve the problems of large storage space for low-speed fixed-wing unmanned aerial vehicles and difficulty in achieving clustering.

[0006] On the one hand, the present invention provides a fixed-wing unmanned aerial vehicle wing automatic rotation and deployment device, which includes a wing connection seat assembly, a fuselage connection seat assembly, and a central locking bolt. One end of the wing connection seat assembly is connected to the unmanned aerial vehicle wing, and the other end is connected to the fuselage connection seat assembly through the central locking bolt. The fuselage connection seat assembly is connected to the unmanned aerial vehicle fuselage;

[0007] The wing connection seat assembly includes a wing connection seat, a spacer sleeve, and a guide pin. The fuselage connection seat assembly is provided with a torsion spring and a guide groove; the rotating end torsion spring arm of the torsion spring is inserted into the wing connection seat, the guide pin is embedded in the guide groove, and after gradually screwing in, the pre-tightening force between the wing connection seat assembly and the fuselage connection seat assembly meets the preset requirements. After the fuselage connection seat assembly and the spacer sleeve are pressed by the central locking bolt, the wing connection seat assembly is in a rotatable state.

[0008] For the aspects and any possible implementation manners described above, a further implementation manner is provided. The wing connection seat assembly further includes a wing connection seat and a steel ball track. The spacer sleeve is arranged at the top center of the wing connection seat. The spacer sleeve is used to control the installation clearance between the fuselage connection seat assembly and the wing connection seat assembly, ensuring that the wing connection seat assembly can rotate. The steel ball track is arranged at the bottom of the wing connection seat.

[0009] For the aspects and any possible implementation manners described above, a further implementation manner is provided. An observation hole and a rotation-in-place stop block are arranged at the top of the wing connection seat. A guide pin is arranged on the outer side wall of the wing connection seat, and a torsion spring arm slot is arranged on the inner side wall of the wing connection seat.

[0010] For the aspects and any possible implementation manners described above, a further implementation manner is provided. Spring pins are installed on both sides of the wing connection seat and are used for fixing and locking after the wing rotates in place. When the wing is retracted, the pull ring of the spring pin is pulled up and the wing is rotated.

[0011] For the aspects and any possible implementation manners described above, a further implementation manner is provided. The fuselage connection seat assembly further includes a fuselage connection base and a connection seat sleeve. The fuselage connection base and the connection seat sleeve are connected to form the main part of the fuselage connection seat assembly.

[0012] For the aspects and any possible implementation manners described above, a further implementation manner is provided. A torsion spring positioning post is arranged at the center of the fuselage connection base and is used for the positioning and installation of the torsion spring.

[0013] For the aspects and any possible implementation manners described above, a further implementation manner is provided. A ring of steel balls and a steel ball cage are installed at the top of the connection seat sleeve. During the rotation process, the steel balls contact the steel ball track at the bottom of the wing connection seat, reducing the frictional force generated during the rotation process.

[0014] For the aspects and any possible implementation manners described above, a further implementation manner is provided. The guide groove is arranged on the inner wall of the connection seat sleeve. The guide groove cooperates with the guide pin of the wing connection seat and is used to guide the installation of the wing connection seat. An extended-in-place wedge stop block and a folded-in-place wedge stop block are arranged at the upper part of the connection seat sleeve and are used to achieve the locking in the extended and folded states.

[0015] For the aspects and any possible implementation manners described above, a further implementation manner is provided. The front ends of both the extended-in-place wedge stop block and the folded-in-place wedge stop block are wedge-shaped, and positioning holes for the spring pins are arranged on the upper surface, and are used to guide the spring pins to be inserted into the positioning holes after the wing rotates in place.

[0016] In the aspects and any possible implementation manners described above, a drone is further provided, and the drone includes the fixed-wing drone wing automatic rotation and deployment device described above.

[0017] Compared with the prior art, the present invention can achieve the following technical effects:

[0018] Compared with traditional fixed-wing drones, the present invention can be folded and stored, thus minimizing the occupied space, improving the space utilization rate, and at the same time can be stored in a launch tube and automatically deployed during takeoff, which is conducive to the realization of fixed-wing drone clustering. In addition, the present invention also has the characteristics of simple structure, easy manufacturing, low cost, and convenient operation.

[0019] Of course, it is not necessary for any product implementing the present invention to achieve all the above-mentioned technical effects simultaneously.

Description of the Drawings

[0020] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present invention, and those of ordinary skill in the art can obtain other drawings based on these drawings without creative efforts.

[0021] Figure 1 It is a schematic diagram of the deployed state after the installation of a fixed-wing drone wing automatic rotation and deployment device provided by an embodiment of the present invention on the fuselage and wings;

[0022] Figure 2 It is a schematic diagram of the folded state after the installation of a fixed-wing drone wing automatic rotation and deployment device provided by an embodiment of the present invention on the fuselage and wings;

[0023] Figure 3 It is a schematic diagram of the deployed state of a fixed-wing drone wing automatic rotation and deployment device provided by an embodiment of the present invention;

[0024] Figure 4 It is a schematic diagram of the folded state of a fixed-wing drone wing automatic rotation and deployment device provided by an embodiment of the present invention;

[0025] Figure 5 It is a schematic diagram of the structural composition of a fixed-wing drone wing automatic rotation and deployment device provided by an embodiment of the present invention;

[0026] Figure 6 It is a sectional view of the split surface of a fixed-wing drone wing automatic rotation and deployment device provided by an embodiment of the present invention;

[0027] Figure 7It is a schematic structural diagram of a wing connection seat assembly provided by an embodiment of the present invention;

[0028] Figure 8 It is a schematic diagram of a mid-plane section of the structure of a wing connection seat assembly provided by an embodiment of the present invention;

[0029] Figure 9 It is a schematic structural diagram of a fuselage connection seat assembly provided by an embodiment of the present invention;

[0030] Figure 10 It is a schematic diagram of a mid-plane section of the structure of a fuselage connection seat assembly provided by an embodiment of the present invention;

[0031] Figure 11 It is a schematic structural diagram of a fuselage connection base provided by an embodiment of the present invention;

[0032] Figure 12 It is a schematic structural diagram of a connection seat sleeve provided by an embodiment of the present invention.

[0033] In the figure: 1. Fixed-wing UAV wing automatic rotation and deployment device; 2. Wing; 3. Fuselage; 11. Wing connection seat assembly; 12. Fuselage connection seat assembly; 13. Locking bolt; 111. Wing connection seat; 112. Spring pin; 113. Steel ball track; 114. Spacer sleeve; 1111. Rotation-in-place stop block; 1112. Observation hole; 1113. Torsion spring arm rotation end slot; 1114. Guide pin; 1115. Intermediate positioning shaft of wing connection seat; 121. Fuselage connection base; 122. Connection seat sleeve; 123. Torsion spring; 124. Self-locking nut; 125. Steel ball; 126. Steel ball cage; 1211. Fuselage connection base adapter flange; 1212. Torsion spring positioning post; 1221. Torsion spring arm fixed end slot; 1222. Deployment-in-place wedge stop block; 1223. Folding-in-place wedge stop block; 1224. Guide groove.

Detailed implementation manners

[0034] In order to better understand the technical solution of the present invention, the embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0035] It should be clear that the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present invention.

[0036] The terms used in the embodiments of the present invention are only for the purpose of describing specific embodiments, and are not intended to limit the present invention. The singular forms of "a", "the" and "said" used in the embodiments of the present invention and the appended claims are also intended to include the plural forms, unless the context clearly indicates otherwise.

[0037] The present invention provides a fixed-wing UAV wing automatic rotation and deployment device. The fixed-wing UAV wing automatic rotation and deployment device includes a wing connection seat assembly, a fuselage connection seat assembly, and a central locking bolt. One end of the wing connection seat assembly is connected to the UAV wing, and the other end is connected to the fuselage connection seat assembly through the central locking bolt. The fuselage connection seat assembly is connected to the UAV fuselage;

[0038] The wing connection seat assembly includes a wing connection seat, a spacer sleeve, and a guide pin. The fuselage connection seat assembly is provided with a torsion spring and a guide groove; the rotating end torsion spring arm of the torsion spring is inserted into the wing connection seat, the guide pin is embedded in the guide groove, and after being gradually screwed in, the pre-tightening force between the wing connection seat assembly and the fuselage connection seat assembly meets the preset requirements. After the fuselage connection seat assembly and the spacer sleeve are pressed by the central locking bolt, the wing connection seat assembly is in a rotatable state.

[0039] The wing connection seat assembly further includes a wing connection seat and a steel ball track. The spacer sleeve is arranged at the top center of the wing connection seat. The spacer sleeve is used to control the installation gap between the fuselage connection seat assembly and the wing connection seat assembly to ensure that the wing connection seat assembly is rotatable. The steel ball track is arranged at the bottom of the wing connection seat.

[0040] An observation hole and a rotation-in-place stop block are arranged at the top of the wing connection seat. The guide pin is arranged on the outer side wall of the wing connection seat, and a torsion spring arm slot is arranged on the inner side wall of the wing connection seat.

[0041] Spring pins are installed on both sides of the wing connection seat for fixing and locking after the wing rotates in place. When the wing is retracted, the pull ring of the spring pin is pulled up to rotate the wing.

[0042] The fuselage connection seat assembly further includes a fuselage connection base and a connection seat sleeve. The fuselage connection base and the connection seat sleeve are connected to form the main part of the fuselage connection seat assembly.

[0043] A torsion spring positioning post is arranged at the center of the fuselage connection base for positioning and installing the torsion spring.

[0044] A circle of steel balls and a steel ball cage are installed at the top of the connection seat sleeve. During rotation, the steel balls contact the steel ball track at the bottom of the wing connection seat to reduce the friction generated during rotation.

[0045] The guiding groove is arranged on the inner wall of the connecting seat sleeve. The guiding groove cooperates with the guiding pin of the wing connecting seat and is used to guide the installation of the wing connecting seat. An unfolding-in-place wedge-shaped stop block and a folding-in-place wedge-shaped stop block are arranged on the upper part of the connecting seat sleeve to realize the locking in the unfolding and folding states. The front ends of the unfolding-in-place wedge-shaped stop block and the folding-in-place wedge-shaped stop block are both wedge-shaped, and positioning holes for spring pins are arranged on the upper surface to guide the spring pins to be inserted into the positioning holes after the wing rotates in place.

[0046] The present invention also provides an unmanned aerial vehicle, which includes the automatic rotation and unfolding device for the wing of the fixed-wing unmanned aerial vehicle described above.

[0047] In a specific embodiment, the present invention is used for automatically unfolding the wing of a fixed-wing unmanned aerial vehicle, mainly including a wing connecting seat assembly and a fuselage connecting seat assembly, specifically including a wing connecting seat, a fuselage connecting base, a connecting seat sleeve, a spacer sleeve, a spring pin, a steel ball track, a torsion spring, steel balls, a steel ball cage, etc.

[0048] A spacer sleeve is installed at the center of the top of the wing connecting seat assembly to control the gap between the fuselage connecting seat and the wing connecting seat and ensure the normal rotation of the wing connecting seat.

[0049] In a specific embodiment, the wing connecting seat is made of aluminum alloy, and an observation hole is arranged at the top to observe the internal situation of the device.

[0050] In a specific embodiment, rotation-in-place stop blocks are arranged on both sides of the wing connecting seat, a guiding pin is arranged on the outer side wall, and a torsion spring arm slot is arranged on the inner side wall.

[0051] In a specific embodiment, a steel ball track is arranged on the bottom end face of the wing connecting seat to enhance the stability and wear resistance during the rotation of the wing connecting base.

[0052] In a specific embodiment, spring pins are installed on both sides of the wing connecting seat to ensure that the wing can be fixed and locked after rotating in place. When the wing is retracted, the pull ring of the spring pin needs to be pulled up and then the wing is rotated.

[0053] The fuselage connecting seat assembly is composed of a fuselage connecting base and a connecting seat sleeve.

[0054] In a specific embodiment, a torsion spring positioning post is arranged at the center of the fuselage connecting base for torsion spring positioning and installation.

[0055] In a specific embodiment, a circle of steel balls and a steel ball cage are installed at the top of the connecting seat sleeve and contact the steel ball track at the bottom of the fuselage connecting seat assembly during the rotation process, which can reduce the friction during the rotation process and improve the wear resistance of the connecting seat sleeve and the fuselage connecting seat at the same time.

[0056] In a specific embodiment, a guiding groove is provided on the inner wall of the connecting seat sleeve, which cooperates with the positioning pin of the wing connecting seat to guide the installation of the wing connecting seat, ensuring that there is a pre-tightening force between the wing connecting seat assembly and the fuselage connecting seat assembly after deployment, and preventing the wing from swaying and shaking during flight.

[0057] In a specific embodiment, wedge-shaped stop blocks are provided on both sides of the upper part of the connecting seat sleeve. After rotation in place, they collide with the stop blocks on the wing connecting seat to achieve the stop function. The front end of the wedge-shaped stop block is wedge-shaped, and a spring pin positioning hole is provided on the upper surface to guide the spring pin to insert into the positioning hole after the wing rotates in place, preventing the wing from rotating.

[0058] In a specific embodiment, after the wing connecting seat assembly, the fuselage connecting seat assembly and their parts are installed, the torsion spring arm is inserted into the wing connecting seat, and the guiding pin of the wing connecting seat is embedded in the guiding groove of the fuselage connecting seat and gradually screwed in. After installation, the wing connecting seat assembly and the fuselage connecting seat assembly are connected by the locking bolt in the center.

[0059] Embodiment 1

[0060] The present invention provides a fixed-wing UAV wing automatic rotation and deployment device, which is used for automatically deploying the fixed-wing UAV wing, and mainly includes a wing connection seat assembly 11 and a fuselage connection seat assembly 12, and specifically includes a wing connection seat 111, a fuselage connection base 121, a connection seat sleeve 122, a distance sleeve 114, a spring pin 112, a steel ball track 113, a torsion spring 123, a steel ball 125, a steel ball retainer 126, etc. After the wing connection seat assembly 11, the fuselage connection seat assembly 12 and the parts thereon are installed, the rotation end torsion spring arm of the torsion spring 123 is inserted into the wing connection seat 111, and the guide pin 1114 of the wing connection seat assembly 11 is embedded in the guide groove 1224 of the fuselage connection seat assembly 12, and gradually screwed in, so as to ensure that the preload force between the wing connection seat assembly 11 and the fuselage connection seat assembly 12 meets the requirements after deployment. After installation is completed, the distance sleeve 114 on the fuselage connection seat assembly 12 and the wing connection seat assembly 11 is pressed by the central locking bolt 13 to ensure that the wing connection seat assembly 11 can rotate normally. A distance sleeve 114 is installed at the top center of the wing connection seat assembly 11 to control the installation gap between the fuselage connection seat assembly 12 and the wing connection seat assembly 11 to ensure that the wing connection seat assembly 11 can rotate normally. The top of the wing connection seat 111 is provided with an observation hole 1112 and a rotation stop block 1111, the outer side wall is provided with a guide pin 1114, and the inner side wall is provided with a torsion spring arm slot 1113. Spring pins 112 are installed on both sides of the wing connection seat 111 to ensure that the wing can be fixed and locked after being rotated into place. When the wing is folded, it is necessary to pull up the spring pin 112 pull ring and then rotate the wing. The main body of the fuselage connection seat assembly 12 is composed of a fuselage connection base 121 and a connection seat sleeve 122. A torsion spring positioning column 1212 is provided at the center of the fuselage connection base 121 for positioning and installing the torsion spring 123. A circle of steel balls 125 and a steel ball holder 126 are installed on the top of the connection seat sleeve 122. During the rotation process, the steel balls 125 contact the steel ball track 113 at the bottom of the wing connection seat 111, which can reduce the friction generated during the rotation process. A guide groove 1224 is provided on the inner wall of the connection seat sleeve 122, which cooperates with the guide pin 1114 of the wing connection seat 111 to guide the installation of the wing connection seat 111. The upper part of the connection seat sleeve 122 is provided with a wedge-shaped stop block 1222 for unfolding in place and a wedge-shaped stop block 1223 for folding in place to achieve locking in the unfolded and folded states. The front ends of the wedge-shaped stop block 1222 for unfolding in place and the wedge-shaped stop block 1223 for folding in place are wedge-shaped, and the upper surface is provided with a positioning hole for the spring pin 112, which is used to guide the spring pin 112 to be inserted into the positioning hole after the wing rotates in place. The wing automatic rotation and unfolding device can ensure that there is a pre-tightening force between the wing connecting seat assembly 11 and the fuselage connecting seat assembly 12 after unfolding, thereby preventing the wing from swaying during flight.

[0061] like Figure 1 and Figure 2As shown in the figure, an automatic rotating and deploying device for the wing of a fixed-wing unmanned aerial vehicle is used to connect the wing 2 to the fuselage 1. On the one hand, when the wing 2 is in the folded position, the pull ring of the spring pin 112 is pulled. At this time, relying on the elastic potential energy of the torsion spring, the wing is driven to quickly rotate to the deployed position and fixed, reaching the take-off state. When the wing is in the deployed position, the pull ring of the spring pin 112 is pulled, and the wing is manually rotated to the folded position. After being locked by the spring pin 112, rapid folding and recovery can be achieved.

[0062] As Figure 3 and Figure 4 shown, the relative position states of the wing connecting seat assembly 11 and the fuselage connecting seat assembly 12 of the automatic rotating and deploying device for the wing of the fixed-wing unmanned aerial vehicle are respectively shown in the deployed and folded positions.

[0063] As Figure 5 shown, the wing connecting seat assembly 11 and the fuselage connecting seat assembly 12 need to be pre-assembled and then connected by the locking bolt 13. During flight, the aerodynamic force generated by the wing is mainly borne by the locking bolt 13. Therefore, the size of the locking bolt 13 should be selected according to the aerodynamic load of the wing.

[0064] As Figure 6 shown, after the wing connecting seat assembly 11 and the fuselage connecting seat assembly 12 are connected by the locking bolt 13, during the deployment and folding processes of the automatic rotating and deploying device for the wing of the fixed-wing unmanned aerial vehicle, the wing connecting seat assembly 11 and the fuselage connecting seat assembly 12 are in contact only through a circle of steel balls 125 of the fuselage connecting seat assembly 12, converting sliding friction into rolling friction and greatly reducing the friction during rotation.

[0065] As Figure 7 and Figure 8 shown, the wing connecting seat assembly 11 is composed of a wing connecting seat 111, a spring pin 112, a steel ball track 113, and a spacer sleeve 114.

[0066] The wing connecting seat 111 includes a rotation-in-place stop block 1111, an observation hole 1112, a torsion spring arm rotation end slot 1113, a guide pin 1114, a wing connecting seat intermediate positioning shaft 1115, etc. The rotation-in-place stop block 1111 is used to collide and contact with the deployment-in-place wedge stop block 1222 on the fuselage connecting seat 12 when the wing automatically unfolds in place, to stop and position the rotating wing connecting seat 111. The observation hole 1112 is used to check whether the rotation end torsion spring arm of the torsion spring 123 is installed in place or has rotated out of the torsion spring arm rotation end slot 1113. The torsion spring arm rotation end slot 1113 is used to limit the rotation end torsion spring arm to prevent the torsion spring arm from rotating out during the rotation of the wing connecting seat 111. The guide pin 1114 cooperates with the guide groove 1224 on the fuselage connecting seat 12 to guide the installation of the wing connecting seat 111. The wing connecting seat intermediate positioning shaft 1115 is used for the central positioning of the wing connecting seat assembly 11.

[0067] The spring pin 112 can be a ready-made component. Pulling the ring of the spring pin 112 or pressing the cylindrical pin at the front end can retract the cylindrical pin.

[0068] The contact surface between the steel ball track 113 and the steel ball 125 is an arc-shaped ring groove. Compared with a flat track without an arc-shaped ring groove, it can not only increase the contact area between the steel ball track 113 and the steel ball 125, reduce the local pressure, but also assist in positioning between the wing connection seat assembly 11 and the fuselage connection seat assembly 12. The steel ball track 113 is made of alloy steel, which can increase the wear resistance of the steel ball track 113 and improve the service life.

[0069] The top of the spacer sleeve 114 contacts the locking bolt 13, and the bottom of the spacer sleeve 114 contacts the end face of the torsion spring positioning post 1212 of the fuselage connection base 121. The spacer sleeve 114 can ensure that there is a certain gap between the wing connection seat 111 and the spacer sleeve 114 after the locking bolt 13 is locked. The locking force is transmitted to the fuselage connection seat assembly 12 through the spacer sleeve 114, thereby preventing excessive pressure between the wing connection seat assembly 11 and the fuselage connection seat assembly 12 and ensuring that the wing connection seat assembly 11 can rotate flexibly.

[0070] As Figure 9 and Figure 10 shown, the fuselage connection seat assembly 12 is composed of a fuselage connection base 121, a connection seat sleeve 122, a torsion spring 123, a self-locking nut 124, a steel ball 125, and a steel ball cage 126.

[0071] As Figure 11 shown, the fuselage connection base 121 is composed of a fuselage connection base adapter flange 1211 and a torsion spring positioning post 1212. The inner ring bolt holes of the fuselage connection base adapter flange 1211 are used to connect the connection seat sleeve 122, and the outer ring bolt holes are used to connect the fuselage 3. The torsion spring positioning post 1212 is used for the central positioning of the torsion spring 123. When in use, according to the actual torque requirement, the number of torsion springs 123 is determined, and at most 2 torsion springs 123 can be placed. The small central circular groove at the top of the torsion spring positioning post 1212 is used for the central positioning of the spacer sleeve 114, and the large central circular groove cooperates with the middle positioning shaft 1115 of the wing connection seat for the central positioning of the wing connection seat assembly 11.

[0072] As Figure 12As shown in the figure, the connecting seat sleeve 122 is composed of a torsion spring arm fixed-end card slot 1221, an unfolded-in-place wedge-shaped stop block 1222, a folded-in-place wedge-shaped stop block 1223, and a guide groove 1224. Among them, the torsion spring arm fixed-end card slot 1221 is used to limit the fixed-end torsion spring arm of the torsion spring 123 to prevent it from loosening during rotation. The wedge-shaped surface of the unfolded-in-place wedge-shaped stop block 1222 is used to push the front cylindrical pin of the spring pin 112 to retract during unfolding. When reaching the set position, the rotation-in-place stop block 1111 on the wing connecting seat 111 collides with the unfolded-in-place wedge-shaped stop block 1222 to stop, and the front cylindrical pin of the spring pin 112 extends and falls into the positioning hole of the wedge-shaped stop block 1222 to achieve locking after unfolding. The folded-in-place wedge-shaped stop block 1223 is used to lock the wing after folding, and its principle is the same as that of the unfolded-in-place wedge-shaped stop block 1222. If it is necessary to achieve automatic unfolding after the aircraft leaves the launch tube during takeoff, the folded-in-place wedge-shaped stop block 1223 can be removed. A guide groove 1224 is opened on the inner wall of the connecting seat sleeve 122 and cooperates with the guide pin 1114 to guide the installation of the wing connecting seat 111, ensuring that the pre-tightening force between the wing connecting seat assembly 11 and the fuselage connecting seat assembly 12 meets the requirements when the wing automatic rotation unfolding device is in the unfolded state.

[0073] In this embodiment, the rotatable angle between the wing connecting seat assembly 11 and the fuselage connecting seat assembly 12 is 90°, which can be adjusted to other angles according to needs. To ensure a certain pre-tightening force between the wing connecting seat assembly 11 and the fuselage connecting seat assembly 12 in the unfolded state and reduce the shaking of the wing in the unfolded state, the angle between the fixed-end torsion spring arm and the rotating-end torsion spring arm of the torsion spring 123 is greater than 90°, and in this example, it is designed to be 135°.

[0074] The self-locking nut 124 is nested in the torsion spring positioning column 1212 to prevent the locking bolt 13 from loosening under the flight vibration load.

[0075] The steel balls 125 are placed in the cylindrical grooves of the steel ball cage 126 to achieve in-situ rotation of the steel balls. The steel ball cage 126 is made of alloy steel material to increase wear resistance and extend service life.

[0076] The present invention provides an automatic rotating and deploying device for the wings of a fixed-wing unmanned aerial vehicle, belonging to the technical field of unmanned aerial vehicles, and solving the problems of large storage space requirements for medium-sized fixed-wing unmanned aerial vehicles and difficulty in achieving clustering. The automatic rotating and deploying device for the wings of a fixed-wing unmanned aerial vehicle according to the present invention includes a wing connection seat assembly and a fuselage connection seat assembly. The wing connection seat assembly includes a wing connection seat, a spring pin, a steel ball track, and a distance sleeve. The fuselage connection seat assembly includes a fuselage connection base, a connection seat sleeve, a torsion spring, a self-locking nut, steel balls, and a steel ball retainer. The wing connection seat assembly and the fuselage connection seat assembly are connected by a locking bolt at the center. After installation, the wing connection seat assembly can rotate relative to the fuselage connection seat assembly and is automatically deployed under the action of the torsion spring. By utilizing the elastic potential energy of the torsion spring, the present invention realizes the automatic deployment function of the wings of the fixed-wing unmanned aerial vehicle, minimizes the storage space, and is conducive to the clustering of unmanned aerial vehicles.

[0077] The above has introduced in detail an automatic rotating and deploying device for the wings of a fixed-wing unmanned aerial vehicle and the unmanned aerial vehicle provided by an embodiment of the present application. The description of the above embodiments is only used to help understand the method and its core idea of the present application; at the same time, for those of ordinary skill in the art, according to the idea of the present application, there will be changes in the specific implementation manners and application scopes. In summary, the content of this specification should not be construed as a limitation to the present application.

[0078] As used in the specification and claims, certain terms are used to refer to specific components. Those skilled in the art should understand that hardware manufacturers may use different terms to refer to the same component. The specification and claims do not use the difference in names as a way to distinguish components, but use the difference in functions of components as a criterion for distinction. As mentioned throughout the specification and claims, "comprising" and "including" are open-ended terms, so they should be interpreted as "including / including but not limited to". "Substantially" means within an acceptable error range. Those skilled in the art can solve the technical problem within a certain error range and basically achieve the technical effect. The subsequent description of the specification is for the purpose of describing the preferred embodiments of the present application, but the description is for the purpose of explaining the general principles of the present application and is not intended to limit the scope of the present application. The protection scope of the present application shall be determined by the scope defined by the appended claims.

[0079] It should also be noted that the term "including", "comprising" or any other variant thereof is intended to cover non-exclusive inclusion, so that a commodity or system including a series of elements not only includes those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such a commodity or system. Without further limitation, the element defined by the statement "including one..." does not exclude the existence of another identical element in the commodity or system including the said element.

[0080] It should be understood that the term "and / or" used herein is merely a description of the associated relationship of associated objects, indicating that three relationships may exist. For example, A and / or B may represent three cases: A exists alone, A and B exist simultaneously, and B exists alone. In addition, the character " / " herein generally indicates that the associated objects before and after are in an "or" relationship.

[0081] The above description shows and describes several preferred embodiments of the present application. However, as mentioned above, it should be understood that the present application is not limited to the form disclosed herein, and should not be regarded as excluding other embodiments. Instead, it can be used in various other combinations, modifications, and environments, and can be changed within the scope of the application concept described herein through the above teachings or the technology or knowledge in the relevant field. Any changes and variations made by those skilled in the art without departing from the spirit and scope of the present application shall fall within the protection scope of the appended claims of the present application.

Claims

1. A device for automatically rotating and unfolding the wings of a fixed-wing UAV, characterized in that: The fixed-wing UAV wing automatic rotation and deployment device comprises a wing connection seat assembly, a fuselage connection seat assembly and a central locking bolt, wherein one end of the wing connection seat assembly is connected to the UAV wing, and the other end is connected to the fuselage connection seat assembly through the central locking bolt, and the fuselage connection seat assembly is connected to the UAV fuselage; The wing connecting seat assembly includes a wing connecting seat, a distance sleeve and a guide pin, and the fuselage connecting seat assembly is provided with a torsion spring and a guide groove; the torsion spring arm at the rotating end of the torsion spring is inserted into the wing connecting seat, and the guide pin is embedded in the guide groove. After being gradually screwed in, the preload force between the wing connecting seat assembly and the fuselage connecting seat assembly meets the preset requirements, and the wing connecting seat assembly is in a rotatable state after the fuselage connecting seat assembly and the distance sleeve are pressed by the center locking bolt.

2. The fixed-wing UAV wing automatic rotation and deployment device according to claim 1 is characterized in that: The wing connecting seat assembly also includes a wing connecting seat and a steel ball track. The distance sleeve is set at the top center of the wing connecting seat. The distance sleeve is used to control the installation gap between the fuselage connecting seat assembly and the wing connecting seat assembly to ensure that the wing connecting seat assembly can rotate. The steel ball track is set at the bottom of the wing connecting seat.

3. The fixed-wing UAV wing automatic rotation and deployment device according to claim 2 is characterized in that: The top of the wing connection seat is provided with an observation hole and a rotation-in-place stop block, the guide pin is arranged on the outer side wall of the wing connection seat, and the inner side wall of the wing connection seat is provided with a torsion spring arm slot.

4. The fixed-wing UAV wing automatic rotation and deployment device according to claim 2 is characterized in that: Spring pins are installed on both sides of the wing connecting seat, which are used to fix and lock the wing after it is rotated into place. When the wing is folded, the pull ring of the spring pin is pulled up to rotate the wing.

5. The fixed-wing UAV wing automatic rotation and deployment device according to claim 2 is characterized in that: The fuselage connection seat assembly also includes a fuselage connection base and a connection seat sleeve, and the fuselage connection base and the connection seat sleeve are connected to form the main body of the fuselage connection seat assembly.

6. The fixed-wing UAV wing automatic rotation and deployment device according to claim 5 is characterized in that: A torsion spring positioning column is arranged at the center of the fuselage connection base for positioning and installing the torsion spring.

7. The fixed-wing UAV wing automatic rotation and deployment device according to claim 5 is characterized in that: A circle of steel balls and a steel ball retainer are installed on the top of the connecting seat sleeve. During the rotation process, the steel balls contact the steel ball track at the bottom of the wing connecting seat to reduce the friction generated during the rotation process.

8. The fixed-wing UAV wing automatic rotation and deployment device according to claim 7 is characterized in that: The guide groove is arranged on the inner wall of the connecting seat sleeve, and the guide groove cooperates with the guide pin of the wing connecting seat to guide the installation of the wing connecting seat. The upper part of the connecting seat sleeve is provided with a wedge-shaped stop block for unfolding and a wedge-shaped stop block for folding, which are used to realize locking in the unfolded and folded states.

9. The fixed-wing UAV wing automatic rotation and deployment device according to claim 8, characterized in that: The front ends of the unfolded wedge-shaped stop block and the folded wedge-shaped stop block are both wedge-shaped, and the upper surfaces are provided with positioning holes for spring pins, which are used to guide the spring pins to be inserted into the positioning holes after the wing is rotated into position.

10. A drone, characterized in that: The UAV comprises the fixed-wing UAV wing automatic rotation and deployment device as described in any one of claims 1-9 above.

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