Unmanned aerial vehicle with folding fins

Abstract

The invention discloses an unmanned aerial vehicle with a folding wing panel, which belongs to the technical field of aircrafts and comprises an unfolding mechanism, a wing panel and a locking mechanism. The unfolding mechanism comprises a wing seat and an energy accumulator. One end of the fin is hinged to the wing base, and the execution end of the energy accumulator is matched with the fin. And an execution action of switching from a limiting state to a release state exists between the locking mechanism and the wing panel. The wing seat is a connecting part between the wing panel and the unmanned aerial vehicle body, and the energy accumulator serves as an element for providing energy in a manner of storing energy in advance. When an unfolding mechanism is triggered, the energy accumulator releases the stored energy, and the fins are pushed to be unfolded rapidly. By means of the design, complexity of a traditional motor or servo mechanism is avoided. The locking mechanism locks the wing panel before the wing panel is unfolded, and it is ensured that the wing panel is kept in a folded state in the storage or transportation process of the unmanned aerial vehicle. The locking mechanism is unlocked by the trigger mechanism when the wing panel is unfolded, thereby allowing the wing panel to be freely unfolded.

Description

Technical Field

[0001] This invention belongs to the field of aircraft technology, specifically a drone with folding wings. Background Technology

[0002] In the application of drone swarm technology, multiple small drones can work collaboratively to complete complex tasks such as swarm flight and task sharing. The key advantages of this swarm application model are efficiency, flexibility, and large-scale deployment. Currently, reducing the size of drones and improving their convenience and reliability have become research hotspots in drone technology.

[0003] The introduction of foldable wing technology provides an effective solution for reducing the size of small drones. By designing foldable wings, the space occupied during drone transportation or storage can be reduced, thus facilitating efficient deployment and high-altitude delivery. During swarm deployment from an aircraft platform, drones can be deployed while locked, with the wings unfolding only after a certain period to ensure stable flight. Existing foldable wing systems typically release the lock and unfold the wing at a designated time via a linkage, motor, or other actuator connected to the wing's pivot axis.

[0004] However, for small drones, while using small actuators can reduce weight and save space, their lower power often results in slower wing deployment speeds, making it difficult to meet the requirements for rapid wing deployment. Especially in applications where rapid wing deployment is crucial for aircraft stability, slow-deploying winglets may prevent the drone from quickly reaching a stable flight state, thus affecting mission performance and flight safety.

[0005] Conversely, if a large actuator is chosen, although it can provide greater power to compensate for the deployment speed problem, due to the size limitations of the small drone itself, an overly large actuator is often difficult to place in a limited space, which leads to an unreasonable overall design of the drone and even increases the weight and complexity of the aircraft.

[0006] Furthermore, for single-use aircraft, the choice of the structure that triggers wing deployment must consider not only deployment speed and size, but also cost control. While complex actuators can meet the requirements for wing deployment, their high cost may conflict with the single-use design philosophy. Summary of the Invention

[0007] The purpose of this invention is to provide a drone with folding wings to solve the problems mentioned in the prior art.

[0008] A drone with folding wings is provided, comprising: The deployment mechanism includes a wing mount and an energy storage device; The winglet has one end hinged to the wing base, and the actuating end of the accumulator is engaged with the winglet. The locking mechanism has an action that switches from a limited state to a released state with respect to the wing.

[0009] As a further aspect of the present invention: a joint support is provided on the wing, and a pin shaft seat is provided on the wing seat that is hinged to the joint support; the accumulator is an elastic element.

[0010] The joint support and the wing mount are hinged together, forming a reliable movable connection point that allows the wing to rotate and deploy smoothly around the hinge point. The accumulator is designed as an elastic element, that is, a component with elasticity. The elastic element accumulates a certain amount of energy in the folded state, and when deployment is needed, this energy is rapidly released, propelling the wing from the folded state into the deployed state.

[0011] As a further aspect of the present invention: there are two winglets, and gears are respectively provided between the two joint supports and the winglets, and the two gears mesh with each other.

[0012] Gears mesh between the two winglets to ensure they deploy synchronously. This gear design not only guarantees winglet synchronicity but also improves deployment balance, preventing asymmetrical torques during deployment. Through gear meshing, the two winglets move in a coordinated manner during deployment, ensuring the drone maintains balance in flight and preventing uneven winglet deployment that could lead to flight instability.

[0013] As a further aspect of the present invention: the accumulator is a torsion spring or a clock spring, the accumulator is disposed on the periphery of the pin shaft seat, and the two ends of the accumulator are respectively engaged with the pin shaft seat and the connector support.

[0014] Torsion springs or clockwork springs can store energy. When the locking mechanism is released, the energy of the torsion spring or clockwork spring is released rapidly. The wing is pushed to unfold by rotating and releasing torque. The advantage is that it can occupy less space in small drones and can provide a lot of redundant potential energy. After the wing is unfolded, it is still subject to the unfolding traction of the clockwork spring, which improves the stability of the wing during flight.

[0015] As a further aspect of the present invention: with the normal direction of the wing's rotation surface as the height direction, the two winglets are staggered in the height direction.

[0016] The staggered design allows the two wings to be completely overlapped and stored relative to the drone fuselage when the wings are folded, thus providing a basis for the miniaturization of the drone fuselage.

[0017] As a further aspect of the present invention: the ends of the two winglets are respectively provided with locking grooves that cooperate with the locking mechanism for limiting.

[0018] The locking groove engages with the locking mechanism to ensure the flaps are securely held in the folded state. When deployment is required, the locking mechanism disengages, allowing the flaps to unfold smoothly. The locking groove provides a secure anchor point for the flaps, preventing accidental unlocking or unfolding during transport, storage, or other non-deployed states.

[0019] As a further aspect of the present invention: when the two winglets are in a folded state, the projections of the locking grooves on the two winglets onto the winglet rotation plane coincide with each other.

[0020] The overlapping design of the locking grooves allows the locking mechanism to constrain two winglets simultaneously by restraining a single locking point, thereby reducing structural redundancy and decreasing the overall weight and size of the UAV.

[0021] As a further aspect of the present invention: the locking mechanism includes a rotating shaft, a trigger, and a locking hook. The trigger is used to trigger the rotation of the rotating shaft, and the locking hook is disposed on the rotating shaft and can cooperate with the wing for limiting.

[0022] The trigger is used to activate the shaft to rotate, releasing the locking mechanism between the locking hook and the winglet, thereby activating the locking hook to complete the unlocking action and deploying the winglet. Compared to unlocking by translation, the rotational action requires less space and reduces the risk of mechanical jamming.

[0023] As a further aspect of the present invention: the trigger includes an electromagnetic drive assembly and an unlocking end, and an unlocking latch is provided on the rotating shaft. The electromagnetic drive assembly is used to drive the unlocking end and the unlocking latch to interact.

[0024] The electromagnetic triggering principle enables a faster and more precise response, thereby ensuring the reliability and deployment speed of the locking mechanism.

[0025] As a further aspect of the present invention: a limiting groove unlocking buckle is provided on the unlocking end to limit the engagement of the limiting groove, and an excitation spring is provided between the rotating shaft and the mounting base.

[0026] The design of the limiting groove and unlocking latch ensures the stability of the drone during daily storage, preventing the winglets from being accidentally triggered due to external factors. The excitation spring provides rotational potential energy to the shaft, which can improve the response speed of the shaft rotation and reduce the risk of shaft jamming.

[0027] Compared with the prior art, the beneficial effects of the present invention are as follows: The wing mount is the connecting component between the wing and the drone fuselage. An energy accumulator acts as the energy supply element by pre-storing energy. When the deployment mechanism is triggered, the energy accumulator releases the stored energy, propelling the wing to deploy rapidly. This design avoids the complexity of traditional motors or servo mechanisms. A locking mechanism locks the wing before deployment, ensuring it remains folded during drone storage or transportation. The locking mechanism is released by a trigger mechanism when the wing deploys, allowing the wing to deploy freely.

[0028] This design improves the deployment speed and reliability of the drone's winglets. The energy storage design allows the winglets to release energy and deploy rapidly in a short time, while the locking mechanism ensures that the winglets remain compactly folded before the aircraft is put into use, facilitating transportation and storage. This design not only reduces the size of the drone but also improves deployment efficiency, especially in swarm applications, ensuring that the drone can be deployed quickly. Attached Figure Description

[0029] To more clearly illustrate the technical solutions in the embodiments of this drawing or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this drawing. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0030] Figure 1 A structural diagram of the wing deployment state of a drone; Figure 2 This is a structural diagram of the folded wing of a drone. Figure 3 This is one of the structural diagrams showing the cooperation between the winglet and the deployment mechanism; Figure 4 for Figure 3 Enlarged view of region B in the middle; Figure 5 This is the second diagram showing the cooperation structure between the winglet and the deployment mechanism; Figure 6 for Figure 1 Enlarged view of region A in the middle; Figure 7 This is a cross-sectional schematic diagram of the locking mechanism; Figure 8 This is a partial structural diagram of the drone in its locked state.

[0031] In the diagram: 1. Deployment mechanism; 11. Wing mount; 12. Accumulator; 13. Pin shaft mount; 14. Gear; 2. Wing; 21. Connector support; 22. Locking groove; 3. Locking mechanism; 31. Rotating shaft; 32. Trigger; 321. Electromagnetic drive assembly; 322. Unlocking end; 323. Limiting groove; 33. Locking hook; 34. Unlocking buckle; 35. Excitation spring. Detailed Implementation

[0032] To make the objectives, technical solutions, and advantages of this application clearer, the application is described and illustrated below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application. All other embodiments obtained by those skilled in the art based on the embodiments provided in this application without inventive effort are within the scope of protection of this application.

[0033] Obviously, the accompanying drawings described below are merely some examples or embodiments of this application. Those skilled in the art can apply this application to other similar scenarios based on these drawings without any inventive effort. Furthermore, it is understood that although the efforts made in this development process may be complex and lengthy, for those skilled in the art related to the content disclosed in this application, any changes to design, manufacturing, or production based on the technical content disclosed in this application are merely conventional technical means and should not be construed as insufficient disclosure of the content of this application.

[0034] However, there may be instances where unnecessary detailed descriptions are omitted. For example, detailed descriptions of well-known matters or repetitive descriptions of essentially the same structures may be omitted. This is to avoid unnecessarily lengthy descriptions and to facilitate understanding by those skilled in the art. Furthermore, the accompanying drawings and the following description are provided to enable those skilled in the art to fully understand this application and are not intended to limit the subject matter of the claims.

[0035] Please see Figures 1-4 As shown in the illustration, in this embodiment of the invention, a drone with folding wings includes a deployment mechanism 1, winglets 2, and a locking mechanism 3. The deployment mechanism 1 includes a wing base 11 and an energy storage device 12. One end of the winglet 2 is hinged to the wing base 11, and the actuating end of the energy storage device 12 cooperates with the winglet 2. The locking mechanism 3 has an actuating action that switches from a limited state to a released state with the winglet 2.

[0036] The deployment mechanism 1 is the power source for the deployment of the wing 2. The wing mount 11 is connected to the UAV fuselage and provides hinge support for the wing 2. The hinge point between the wing mount 11 and the wing 2 is the rotation axis of the wing 2, allowing the wing 2 to deploy and fold around this point.

[0037] The accumulator 12 is an energy storage element. Its function is to store a certain amount of elastic energy when the wing 2 is in a folded state, and release the stored energy when it needs to be unfolded. During the unfolding process, it generates a rapid and continuous force, which makes the wing 2 quickly change from a folded state to an unfolded state.

[0038] The locking mechanism 3 ensures that the winglet 2 remains securely in a fixed position when folded, preventing accidental deployment during storage or transportation due to external forces or unforeseen interference. When the drone needs to deploy the winglet 2, the locking mechanism 3 switches the winglet 2 from the limited state to the released state. After switching to the released state, the accumulator 12 releases the stored energy, and the winglet 2 begins to deploy.

[0039] This design employs a simple accumulator 12 and locking mechanism 3, which reduces system weight and cost compared to complex direct-drive electric actuator systems. Multiple drones can be stored and transported in a compact folded state, and upon release, the wings 2 quickly unfold to enter flight mode. It is less affected by environmental factors and has excellent flexibility and adaptability.

[0040] In some embodiments, please refer to Figure 4 , Figure 5 As shown, a joint support 21 is provided on the wing 2, and a pin bearing 13 is provided on the wing 11, which is hinged to the joint support 21. The pin bearing 13 provides reliable support and a rotation axis.

[0041] In one specific embodiment, the joint support 21 is detachably connected to the blade 2. The blade 2 composite material is produced through a prepreg molding process. By using different prepreg layup methods and resin ratios, the performance of the parts can be improved to meet the usage requirements of the blade 2. The detachable connection method structurally decouples the blade 2, which is used to achieve aerodynamic effects, from the joint support 21, which is used to bear the loads of key nodes, and achieves the combined linkage of the two manufactured parts through post-assembly.

[0042] Specifically, the energy accumulator 12 is designed as an elastic element, capable of storing energy in the folded state of the wing 2 and releasing sufficient force to propel the wing 2 out when needed. Compared to traditional electric actuators, the elastic element has the advantages of small size, light weight, and low cost, and can quickly release energy to propel the wing 2 out rapidly, thus meeting the UAV's requirement to quickly enter flight mode. This design not only simplifies the system structure and reduces complexity, but also effectively improves the deployment speed, avoiding the problem of slow deployment speed when using small-volume electric actuators.

[0043] In one embodiment, the energy accumulator 12 is a torsion spring. When the torsion spring rotates about its central axis, it stores energy proportional to the rotation angle. This energy can be rapidly released when needed to generate a corresponding rotational torque. Furthermore, the torsion spring has a rapid and intense energy release characteristic; when released, the stored energy can be quickly converted into rotational torque, thereby driving the vane 2 to rotate rapidly, making it suitable for systems requiring high torque and fast response.

[0044] However, for torsion springs, since they need to maintain a certain rotation angle to store energy, long-term energy accumulation may cause the spring torque to gradually decay, increasing the risk of material fatigue, reducing work efficiency, affecting the deployment effect, and making it unsuitable for long-term storage of drones.

[0045] In one embodiment, the accumulator 12 is a spring-loaded mechanism. The spring-loaded mechanism is designed to drive the vane 2 through the unfolding of its spiral structure. The energy release of the spring-loaded mechanism is relatively uniform, a gradual process, making it more suitable for systems requiring continuous and stable power output. Furthermore, because the spring-loaded mechanism can provide power output for a longer period, the unfolding process of the vane 2 is more gentle and smooth, reducing impact on mechanical components.

[0046] Furthermore, the spring stores energy through the linear deformation of a metal strip, allowing for a relatively smooth energy release without placing excessive strain on the spring itself. During long-term storage, the spring does not exhibit significant fatigue, effectively maintaining its performance and thus benefiting the long-term storage of drones.

[0047] Furthermore, the energy storage device 12 needs to provide redundant potential energy to ensure that the wing 2 has a certain amount of excess clamping force after it is deployed, thereby ensuring the stability of the wing 2 in flight and preventing the wing 2 from becoming loose or unstable due to external airflow or vibration.

[0048] Because the torsion spring has a limited rotation angle, most of its stored energy is consumed when it extends to near its maximum angle, resulting in a relatively small amount of redundant potential energy. In contrast, the clockwork spring, with its wound metal strip structure, can maintain a large amount of redundant potential energy even after the wing 2 is fully extended. This structure allows the clockwork spring to store more excess energy, meaning that even after the wing 2 has extended to a predetermined angle, it can still provide excess compressive force to ensure the stability of the wing 2 during flight.

[0049] In one specific embodiment, the outer straight edge circular hole of the accumulator 12 is aligned with the screw hole of the inner groove wall of the connector support 21 and the corresponding screw is installed. The inner straight edge of the accumulator 12 passes through the slit groove of the pin shaft seat 13 and is fixed to achieve the assembly of the accumulator 12.

[0050] Furthermore, there are two winglets 2, and gears 14 are respectively provided between the two joint supports 21 and the winglet 11, and the two gears 14 mesh with each other.

[0051] First, during the deployment of the winglets 2, the winglets 2 are connected to the energy storage unit 12 via a hinged structure, and the energy stored in the energy storage unit 12 begins to drive the deployment of the winglets 2. Each winglet 2 has a gear 14 on its joint support 21, and these gears 14 mesh with each other. When one winglet 2 is deployed by the drive of the energy storage unit 12, the rotational meshing of the gears 14 synchronously transmits this power to the other winglet 2. Due to the mechanical transmission characteristics of the gears 14, the two winglets 2 will deploy synchronously within the same timeframe.

[0052] The meshing structure of the gear 14 ensures that the deployment angle and deployment time of the two winglets 2 are consistent. This synchronous deployment not only improves the stability of the UAV flight, but also effectively reduces the unbalanced torque caused by asynchronous deployment, thereby ensuring the mechanical balance of the winglets 2 during flight.

[0053] Furthermore, the meshing effect of gear 14 is not limited to the deployment of winglets 2. During flight, gear 14 ensures that the two winglets 2 maintain a consistent displacement through continuous mechanical transmission. Specifically, the gear 14 structure, through mechanical connection, ensures that the two winglets 2 maintain the same phase synchronously even in flight. This continuous consistency of winglet 2 during flight effectively prevents problems such as uneven lift, aerodynamic instability, or flight attitude incoordination caused by asynchronous displacement of different winglets 2.

[0054] In some embodiments, please refer to Figures 2-4 As shown, with the normal direction of the rotation surface of winglet 2 as the height direction, the two winglets 2 are staggered in the height direction. If the two winglets 2 are folded in the same layer, they will be arranged side by side, and the total width of the entire folding wing assembly will be at least equal to the width of the two winglets 2 plus the necessary gap. However, with the staggered design, one winglet 2 can partially or completely overlap the space above or below the other winglet 2. This causes the two winglets 2 to overlap on the projection plane in the thickness direction, thereby significantly reducing the overall width of the entire folding wing assembly in the folded state.

[0055] Furthermore, in accordance with the shape of the drone fuselage, the staggered design allows the winglets 2 to fold more closely to the contours of the fuselage, avoiding the winglets 2 protruding outward relative to the fuselage due to being arranged in the same layer, thus maximizing the use of the space around the fuselage.

[0056] In one specific embodiment, the length of the connection area between the wing 2 and the connector support 21 is about half the width of the wing 2, and the width of the wing support 11 is the same as or close to the width of the wing 2. That is, when the two wing 2 are folded and overlapped, the overall width is the same as or close to the width of the fuselage, thereby maximizing the reduction of the fuselage volume.

[0057] In some embodiments, the ends of the two flaps 2 are respectively provided with locking grooves 22 that cooperate with the locking mechanism 3 for limiting. The locking groove 22 is a notch or groove of a specific shape machined at the end of the flap 2, and its core function is to provide a precise and reliable gripping point or insertion point for the locking mechanism 3.

[0058] Specifically, when the locking mechanism 3 enters the locking groove 22, the inner wall of the groove forms a tight contact surface with the surface of the locking hook 33 of the locking mechanism 3. In the folded state, the potential energy stored in the accumulator 12 attempts to drive the wing 2 to unfold, and the resulting rotational torque is converted into normal pressure and friction on the contact surface between the locking hook 33 and the locking groove 22. The structural design of the locking groove 22 ensures that these forces are stably and evenly borne, thereby firmly restraining the wing 2 in the folded position and preventing any accidental loosening or release.

[0059] The locking mechanism 3 and the locking groove 22 engage at the tail end of the winglet 2. This design ensures that the locking mechanism 3 does not occupy the width of the fuselage; furthermore, the locking hook 33 has ample room to move at the tail end of the winglet 2. During unlocking, the locking mechanism 3 simply disengages from the locking groove 22 in a direction away from it, thus deploying the winglet 2 with a short stroke. This reduces the driving force and energy required for unlocking, allowing the trigger 32 to be designed to be smaller, more flexible, and respond more quickly.

[0060] Furthermore, in the staggered structure, since the two winglets 2 can partially or completely overlap, their locking grooves 22 can coincide. In other words, when the winglets 2 are folded, the projections of the locking grooves 22 of the two winglets 2 onto the rotation plane of the winglets 2 will overlap. This design allows a single locking hook 33 to simultaneously enter the locking grooves 22 of both winglets 2, achieving synchronous locking of the two winglets 2. Because the locking grooves 22 coincide, the locking mechanism 3 can simultaneously constrain the unfolding of the two winglets 2 with a simple action, avoiding the complexity of needing two independent locking mechanisms 3.

[0061] Furthermore, by using overlapping locking slots 22, the design requires only one locking hook 33 and one unlocking mechanism to control the two winglets 2, instead of requiring a separate locking device for each winglet 2. This reduces structural redundancy and lowers the overall weight and complexity. Due to the overlap of the locking slots 22, unlocking requires only a simple triggering action to release both winglets 2 simultaneously, ensuring the high efficiency of the deployment process.

[0062] In some embodiments, please refer to Figure 1 , Figures 6-8 As shown, the locking mechanism 3 includes a rotating shaft 31, a trigger 32, and a locking hook 33. The rotating shaft 31 is the core rotating component of the locking mechanism 3, carrying and transmitting the driving action of the trigger 32. The rotation of the rotating shaft 31 directly causes the movement of the locking hook 33, thereby locking or releasing the flap 2. The function of the trigger 32 is to trigger the rotation of the rotating shaft 31 through a driving source. The locking hook 33 engages with the flap 2 to lock the flap 2 in its folded position.

[0063] The locking mechanism 3 unlocks via rotation, rather than a linear or translational unlocking method. The rotating shaft 31 releases the lock through rotation, a design that occupies less space and offers higher space utilization compared to traditional translational unlocking mechanisms, making it suitable for the compact design of small UAVs. Since the locking hook 33 directly contacts the locking groove 22 of the wing 2, the rotational unlocking method avoids the risk of mechanical jamming, thereby improving system reliability.

[0064] Furthermore, the trigger 32 includes an electromagnetic drive assembly 321 and an unlocking end 322. An unlocking latch 34 is provided on the rotating shaft 31. The electromagnetic drive assembly 321 is used to drive the unlocking end 322 and the unlocking latch 34 to interact.

[0065] The electromagnetic drive assembly 321 can rapidly generate a magnetic field through current to push the unlocking end 322. Compared with traditional mechanical drives, such as springs or motor drives, this method is faster and can activate the rotation of the shaft 31 in a very short time, ensuring that the winglet 2 unlocks and deploys quickly.

[0066] The unlocking latch 34 is a protruding part on the rotating shaft 31, used to cooperate with the unlocking end 322. Under the action of the electromagnetic drive assembly 321, the unlocking end 322 engages or disengages from the unlocking latch 34, ensuring that the rotating shaft 31 can rotate smoothly, thereby releasing the locking mechanism 3.

[0067] In one embodiment, upon receiving a command, the electromagnetic drive assembly 321 activates and pushes the unlocking end 322 forward. The forward movement of the unlocking end 322 directly impacts the unlocking latch 34, applying a rotational torque to it. The unlocking latch 34 transmits this torque to the rotating shaft 31, causing it to rotate. As the shaft 31 rotates, the locking hook 33 connected to it disengages from the locking groove 22. At this point, the locking groove 22 is no longer in contact with the locking hook 33, and the locking state of the flap 2 is released.

[0068] A torsion spring is provided on the pivot 31. In the normal locked state, the torsion spring maintains the contact between the locking hook 33 and the locking groove 22, and keeps the wing 2 folded when not triggered. The function of the torsion spring is to provide the necessary elastic force to the locking hook 33 to ensure that the wing 2 will not be accidentally deployed during storage or transportation.

[0069] In one embodiment, a limiting groove 323 is provided on the unlocking end 322, and the unlocking latch 34 is engaged with the limiting groove 323. An excitation spring 35 is provided between the rotating shaft 31 and the mounting base. The function of the limiting groove 323 on the unlocking end 322 is to provide a positioning and blocking mechanism for the unlocking latch 34. When the unlocking end 322 retracts under the action of the electromagnetic drive assembly 321, the engagement between the limiting groove 323 and the unlocking latch 34 changes from being fixed to being disengaged.

[0070] Specifically, when the system receives an unlock signal, the electromagnetic drive assembly 321 is activated and drives the unlocking end 322 to retract backward via electromagnetic force. As the unlocking end 322 retracts, the unlocking latch 34 is subjected to the elastic restoring force of the excitation spring 35, causing the unlocking latch 34 to move and releasing the engagement force between the limiting groove 323 and the unlocking latch 34. Simultaneously, under the elastic restoring force of the excitation spring 35, the rotating shaft 31 drives the locking hook 33 to rotate, thereby disengaging the locking groove 22, and the locking groove 22 no longer constrains the winglet 2.

[0071] Specifically, the electromagnetic drive assembly 321 is an electromagnet, which generates electromagnetic force to drive the movement of the unlocking end 322. The electromagnet's coil generates a magnetic field through current, attracting or pushing the iron core or other moving parts, thus controlling the precise movement of the unlocking end 322. The unlocking end 322 consists of a sliding component and a limiting part, responsible for converting the power provided by the electromagnetic drive assembly 321 into actual mechanical action. Under the action of electromagnetic force, the sliding component slides forward or backward, and by engaging or disengaging with the unlocking latch 34, unlocking the locking mechanism 3 is completed. The limiting part provides precise positioning for the movement of the sliding component, ensuring the correct operation of the unlocking latch 34 during movement.

[0072] In one specific embodiment, the electromagnetic drive assembly 321 is equipped with an electromagnet and a slide bar. One end of the slide bar is controlled by the electromagnet, and the other end is connected to the slider of the unlocking end 322. The electromagnet generates a magnetic field to drive the slide bar to slide, and the slide bar causes the unlocking end 322 to retract and disengage from the unlocking latch 34. In normal operation, the slide bar, driven by a spring, tends to continuously press the unlocking end 322 against the unlocking latch 34.

[0073] It should be noted that this application is not limited to the above-described embodiments. The above embodiments are merely examples, and any embodiments with the same structure and effect as the technical concept within the scope of this application are included in the technical scope of this application. Furthermore, various modifications that can be conceived by those skilled in the art to the embodiments, and other ways of constructing by combining some of the constituent elements of the embodiments, without departing from the spirit of this application, are also included in the scope of this application.

Claims

1. A drone with folding wings, characterized in that, include: The deployment mechanism (1) includes a wing mount (11) and an energy storage device (12), wherein the energy storage device (12) is an elastic element; The wing (2) is provided with a joint support (21), and the wing seat (11) is provided with a pin shaft seat (13) hinged to the joint support (21). There are two wing (2), and gears (14) are respectively provided between the two joint supports (21) and the wing seat (11). The two gears (14) mesh with each other. The ends of the two wing (2) are respectively provided with locking grooves (22) that cooperate with the locking mechanism (3) for limiting. The accumulator (12) is provided between the joint support (21) and the pin shaft seat (13). The locking mechanism (3) has an action to switch from the limit state to the release state with the wing (2). The locking mechanism (3) includes a rotating shaft (31), a trigger (32) and a locking hook (33). The trigger (32) is used to trigger the rotation of the rotating shaft (31). The locking hook (33) is set on the rotating shaft (31) and can be limited and cooperated with the locking groove (22).

2. The UAV with folding wings according to claim 1, characterized in that, The accumulator (12) is a torsion spring or a clock spring. The accumulator (12) is located on the periphery of the pin seat (13). The two ends of the accumulator (12) are respectively engaged with the pin seat (13) and the connector support (21).

3. The UAV with folding wings according to claim 1, characterized in that, With the normal direction of the rotation surface of the winglet (2) as the height direction, the two winglets (2) are staggered in the height direction.

4. A drone with folding wings according to claim 1, characterized in that, When the two winglets (2) are in a folded state, the projections of the locking grooves (22) on the two winglets (2) on the rotation plane of the winglets (2) coincide with each other.

5. A drone with folding wings according to claim 1, characterized in that, The trigger (32) includes an electromagnetic drive assembly (321) and an unlocking end (322). An unlocking latch (34) is provided on the rotating shaft (31). The electromagnetic drive assembly (321) is used to drive the unlocking end (322) and the unlocking latch (34) to interact.

6. A drone with folding wings according to claim 5, characterized in that, The unlocking end (322) is provided with a limit groove (323), the unlocking buckle (34) is in a limiting fit with the limit groove (323), and an excitation spring (35) is provided between the rotating shaft (31) and the mounting base.

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