A wing folding mechanism for a drone

Abstract

This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and provides a UAV wing folding mechanism, including: a pivot assembly, a first wing embedded part, a second wing embedded part, an energy storage spring, and a bidirectional limiting block; the wing pivot is fixed to the fuselage end, the first wing embedded part is embedded in the root of the first wing, the second wing embedded part is embedded in the root of the second wing, and spring receiving cavities are respectively provided in the first and second wing embedded parts. The energy storage spring is placed in the spring receiving cavity, and its two ends are fixedly connected to the first and second wing embedded parts respectively. The first and second wing embedded parts are respectively fitted onto the wing pivot. When the wing is folded, the spring is compressed and stores energy by the embedded parts. When unfolded, the spring releases energy to drive the wing to unfold synchronously to the position limited by the bidirectional limiting block. The structure is compact and lightweight, reducing the number of parts, highly convenient, and the folded wing fits snugly against the fuselage, making it easy to carry.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically a folding mechanism for UAV wings, applicable to fixed-wing UAVs and other aircraft requiring wing folding functionality. Background Technology

[0002] With the widespread application of drones in surveying, logistics, and border patrol, the demand for portable and rapid deployment capabilities is becoming increasingly prominent. Fixed-wing drones have become the mainstream type due to their advantages such as long endurance and high-speed cruising, but their high aspect ratio wings face severe challenges in transportation and storage. Traditional folding mechanisms mostly use hydraulic drive or electric linkage systems, achieving wing folding through complex transmission chains. This not only significantly increases the overall weight of the aircraft, but also leads to asynchronous unfolding due to accumulated errors from multiple kinematic pairs, making them prone to jamming in harsh conditions such as sandstorms and low temperatures in the field.

[0003] Existing folding solutions, in order to balance structural strength, often employ external hinges and latches, resulting in a significant gap between the folded wing and the fuselage. This not only reduces space utilization—making the drone unsuitable for standard transport containers—but also disrupts the aerodynamic shape during flight, inducing turbulence and noise. Although newer solutions such as magnetic locking and shape memory alloy actuation have emerged in recent years, the former has the safety hazard of insufficient locking force, while the latter is limited by temperature sensitivity, leading to a sharp drop in reliability in complex environments. The industry urgently needs a lightweight, power-free folding mechanism that can tightly fit the fuselage to balance the core requirements of portability, reliability, and aerodynamic performance. Utility Model Content

[0004] This invention aims to provide a wing folding mechanism for unmanned aerial vehicles (UAVs). Through the coordinated action of a pivot assembly, double-sided embedded parts, and an energy storage spring, the wing can be rapidly deployed and retracted without power. The energy storage spring stores mechanical energy under pressure in the folded state, and upon release, drives the wing to synchronously deploy to an aerodynamically optimized position. The bidirectional limiting blocks and embedded parts work together to control the deployment limit. This mechanism is compact and lightweight, with few components, resulting in a small gap between the wing and fuselage after folding, optimized aerodynamic performance, and suitability for harsh operating conditions such as catapult takeoff.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a wing folding mechanism for a drone, comprising: a pivot assembly, a first wing embedded part, a second wing embedded part, an energy storage spring, and a bidirectional limiting block; the pivot assembly includes a wing pivot and a fixing cover plate; the wing pivot is fixed to the fuselage end, the first wing embedded part is embedded in the root of the first wing, the second wing embedded part is embedded in the root of the second wing, the first wing embedded part and the second wing embedded part are respectively mounted on the wing pivot and fixed to the wing pivot by the fixing cover plate, thereby fixing the first wing to the second wing and the fuselage.

[0006] The first wing embedded part and the first wing embedded part are respectively provided with spring receiving cavities. The energy storage spring is placed in the spring receiving cavity. Each spring receiving cavity is provided with a limiting boss, which is used to limit and fix the energy storage spring.

[0007] The two ends of the energy storage spring are fixedly connected to the limiting bosses of the first wing embedded part and the second wing embedded part, respectively, and the middle section of the energy storage spring is wound around the outer surface of the rotating shaft assembly.

[0008] When the wings are folded, the energy storage spring is compressed and stores energy by the first wing embedded part and the second wing embedded part. When the wings are unfolded, the energy storage spring releases energy to drive the first wing and the second wing to unfold synchronously to the position defined by the bidirectional limiting block. The bidirectional limiting block is fixed to the fuselage by a flange frame.

[0009] The pivot assembly is made of hollow carbon fiber tubing, and the bidirectional limiting block restricts the included angle between the first wing and the second wing to 120°-150°.

[0010] The beneficial effects of the technical solution in this application are as follows:

[0011] 1. Simplified structure enhances reliability: The wing-folding function can be achieved with only a pivot assembly, bidirectional limit blocks, and a pair of pre-embedded parts, completely eliminating the hydraulic lines or electric drive chains of traditional mechanisms. The significant reduction in the number of components significantly reduces the risk of mechanical failure, especially avoiding jamming problems caused by multiple moving parts, allowing the mechanism to work stably in harsh environments such as sandstorms and humidity.

[0012] 2. Passive Deployment Enhances Adaptability: The energy storage spring automatically compresses and stores energy when the wings are folded, and releases it to instantly deploy the wings without the need for external power or hydraulic drive. This design overcomes the limitations of power dependence, enabling the drone to respond quickly even in extreme conditions such as power outages and low temperatures, making it particularly suitable for scenarios with stringent time requirements, such as catapult takeoff.

[0013] 3. Compact Compact Design for Optimized Portability: When folded, the embedded parts slide along the pivot axis, allowing the wing root to fit snugly against the fuselage sidewall, significantly reducing redundant gaps caused by traditional hinge structures. The overall outline of the folded drone closely resembles the fuselage body, allowing it to be directly packed into standard transport containers, significantly improving space utilization for individual soldier carrying or vehicle transport.

[0014] 4. Undamaged Aerodynamic Integrity: The design of the embedded parts at the wing root ensures that the mechanism is completely enclosed within the airfoil, with no exposed protruding parts after folding. During flight, the wing surface remains continuously smooth, fundamentally eliminating the airflow segmentation and disturbance caused by traditional external hinges, and maintaining optimal lift-to-drag ratio characteristics. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 A three-dimensional exploded view of a drone wing folding mechanism provided by the present invention;

[0017] Figure 2 A cannon wing folding mechanism is provided by the present invention. (Axonometric view of the folded wing state of the wing.)

[0018] Figure 3 A cannon wing folding mechanism is shown in the wing deployment state according to the present invention.

[0019] Figure 4 A schematic diagram showing the positions of the first and second wing embedded parts of a drone wing folding mechanism provided by the present invention;

[0020] Figure 5 This invention provides a schematic diagram of a bidirectional limiting block structure for a drone wing folding mechanism.

[0021] Figure 6 This invention provides a schematic diagram of a flange frame structure for a drone wing folding mechanism.

[0022] Explanation of the labels in the diagram:

[0023] 1. Fuselage; 2. First wing; 3. Second wing; 4. Rotating shaft assembly; 5. Embedded part of the first wing; 6. Embedded part of the second wing; 7. Energy storage spring; 8. Bidirectional limiting block; 9. Spring receiving cavity; 10. Limiting boss; 11. Wing rotating shaft; 12. Fixed cover plate; 13. Flange frame. Detailed Implementation

[0024] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0025] To make the above-mentioned objectives, features and advantages of this application more apparent and understandable, the application will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0026] Combination Figures 1-6 As shown, this utility model provides a wing folding mechanism for a drone, comprising: a pivot assembly 4, a first wing embedded part 5, a second wing embedded part 6, an energy storage spring 7, and a bidirectional limiting block 8; the pivot assembly 4 includes a wing pivot 11 and a fixing cover plate 12; the wing pivot 11 is fixed to the end of the fuselage 1, the first wing embedded part 5 is embedded in the root of the first wing 2, the second wing embedded part 6 is embedded in the root of the second wing 3, the first wing embedded part 5 and the second wing embedded part 6 are respectively fitted on the wing pivot 11, and fixed on the wing pivot 11 by the fixing cover plate 12, thereby fixing the first wing 2 to the second wing 3 and the fuselage 1.

[0027] The first wing embedded part 5 and the first wing embedded part 5 are respectively provided with spring receiving cavities 9. The energy storage spring 7 is placed in the spring receiving cavity 9. The spring receiving cavity 9 is provided with a limiting boss 10, which is used to limit and fix the energy storage spring 7.

[0028] The two ends of the energy storage spring 7 are fixedly connected to the limiting bosses 10 of the first wing embedded part 5 and the second wing embedded part 6, respectively, and the middle section of the energy storage spring 7 is wrapped around the outer surface of the rotating shaft assembly 4.

[0029] When the wings are folded, the energy storage spring 7 is compressed and stored by the first wing embedded part 5 and the second wing embedded part 6. When unfolded, the energy storage spring 7 releases energy to drive the first wing 2 and the second wing 3 to unfold synchronously to the position limited by the bidirectional limiting block 8. The bidirectional limiting block 8 is fixed to the fuselage 1 by the flange frame 13.

[0030] The pivot assembly 4 is made of hollow carbon fiber tubing, and the bidirectional limiting block 8 restricts the deployment angle of the first wing 2 and the second wing 3 to 120°-150°. It is worth noting that the deployment angle of the first wing 2 and the second wing 3 of 120°-150° is the optimal range for UAV flight, but it is not an absolute limitation.

[0031] Specifically, this application realizes an integrated energy storage-release mechanism: the energy storage spring 7 is compressed and stored by the first wing embedded part 5 and the second wing embedded part 6 when the wing is folded, and the energy is released instantaneously when it is unfolded, achieving millisecond-level response; abandoning the traditional transmission chain, mechanical energy storage is used to achieve rapid unfolding without power.

[0032] A specific embodiment provided in this application is as follows:

[0033] Folding process: Manually rotate the first wing 2 and the second wing 3 toward the fuselage centerline. The first wing embedded part 5 and the second wing embedded part 6 move axially along the wing pivot 11 to compress the energy storage spring 7. When they reach the folding position, they are temporarily fixed by the fuselage buckle; the fuselage buckle can also be a Velcro strap.

[0034] Deployment process: After the buckle is released, the energy storage spring 7 pushes the first wing embedded part 5 and the second wing embedded part 6 to move in opposite directions, and the first wing 2 and the second wing 3 deploy. Finally, the bidirectional limiting block 8 completes the hard limiting.

[0035] It is worth mentioning that the illustrations provided in this application are only one application example of the organization, including but not limited to the structures shown in the illustrations.

[0036] In the following description, specific details such as particular system architectures and techniques are set forth for illustrative purposes and not for limitation, in order to provide a thorough understanding of the embodiments of this application. However, those skilled in the art will understand that this application may also be implemented in other embodiments without these specific details. In other instances, detailed descriptions of well-known systems, apparatuses, circuits, and methods have been omitted so as not to obscure the description of this application with unnecessary detail.

[0037] It should be noted that in the description of this invention, relational terms such as first and second are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations.

[0038] Unless otherwise explicitly specified and limited, the terms “fixed,” “set,” and “connected” should be interpreted broadly, for example, as a fixed connection, a detachable connection, or an integral connection; those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0039] The above embodiments are merely preferred embodiments of this application and are not intended to limit the scope of this application. Any modifications and improvements made by those skilled in the art to the technical solutions of this application without departing from the spirit of this application shall fall within the protection scope defined by the claims of this application.

Claims

1. A wing folding mechanism for a drone, characterized in that, include: The system comprises a pivot assembly, a first wing embedded part, a second wing embedded part, an energy storage spring, and a bidirectional limiting block; the pivot assembly includes a wing pivot and a fixing cover plate; the wing pivot is fixed to the fuselage end, the first wing embedded part is embedded in the root of the first wing, the second wing embedded part is embedded in the root of the second wing, the first wing embedded part and the second wing embedded part are respectively fitted on the wing pivot and fixed on the wing pivot by the fixing cover plate, thereby fixing the first wing to the second wing and the fuselage.

2. The wing folding mechanism for a drone according to claim 1, characterized in that, The first wing embedded part and the first wing embedded part are respectively provided with spring receiving cavities. The energy storage spring is placed in the spring receiving cavity. Each spring receiving cavity is provided with a limiting boss, which is used to limit and fix the energy storage spring.

3. The wing folding mechanism for a drone according to claim 2, characterized in that, The two ends of the energy storage spring are fixedly connected to the limiting bosses of the first wing embedded part and the second wing embedded part, respectively, and the middle section of the energy storage spring is wound around the outer surface of the rotating shaft assembly.

4. The wing folding mechanism for a drone according to claim 3, characterized in that, When the wings are folded, the energy storage spring is compressed and stores energy by the first wing embedded part and the second wing embedded part. When the wings are unfolded, the energy storage spring releases energy to drive the first wing and the second wing to unfold synchronously to the position defined by the bidirectional limiting block. The bidirectional limiting block is fixed to the fuselage by a flange frame.

5. The wing folding mechanism for a drone according to claim 4, characterized in that, The pivot assembly is made of hollow carbon fiber tubing, and the bidirectional limiting block restricts the included angle between the first wing and the second wing to 120°-150°.

Images