Portable folding wing unmanned aerial vehicle structure

Abstract

The utility model discloses a portable folding wing unmanned aerial vehicle structure, and relates to the technical field of unmanned aerial vehicles, the portable folding wing unmanned aerial vehicle structure comprises an unmanned aerial vehicle main body, the top of the unmanned aerial vehicle main body is provided with a group of upper wings, the bottom of the unmanned aerial vehicle main body is provided with a group of lower wings, and two sides of the unmanned aerial vehicle main body are respectively provided with a side wing. Supporting pieces are arranged on the two sides of the unmanned aerial vehicle body, push rods are arranged on the inner sides of the two supporting pieces, pressing plates are arranged on the sides, close to each other, of the push rods, and upper clamping rods and lower clamping rods are arranged on the inner sides of the two supporting pieces. The two upper clamping rods and the two lower clamping rods can be pushed to fix the upper wing and the lower wing, meanwhile, the side wings can be fixed, and the upper wing, the lower wing and the side wings are prevented from shaking towards the two sides in the launching process.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically a portable folding-wing UAV structure. Background Technology

[0002] The RY9D unmanned aerial vehicle (UAV) system is a 5kg-class cannon-launched folding-wing UAV system, consisting of a UAV flight platform, portable ground equipment, and a launch cannon system. The portable ground equipment comprises a portable planning and control terminal, a portable data link device, an external battery, a charger, and carrying gear; the launch cannon system consists of the launch cannon and its related accessory systems. The mission and operational methods of the RY9D UAV dictate that the overall design must meet the requirements of cannon-mounted storage, easy portability, cannon-launch, loitering flight, and parachute recovery.

[0003] Canister launch refers to the process of launching a UAV from a launch canister and rapidly deploying it into a stable flight state. The canister launch process is divided into three parts: the boost phase, the separation phase, and the deployment phase. The boost phase needs to ensure the launch attitude and flight speed of the UAV; the separation phase needs to ensure the reliability of the separation between the booster piston and the UAV and minimize the impact of separation on the UAV's attitude; and the deployment phase needs to ensure the flight stability of the aircraft during deployment.

[0004] In existing technologies, drones rely solely on the motor that drives their rotation for positioning. However, when launching a drone through a launch tube, this method is insufficient to withstand the powerful impact of launch. It hinders wing stability, causing the upper, lower, and side wings to vibrate during launch, making it difficult to maintain a correct attitude and significantly increasing the likelihood of flight deviation. This severely reduces launch accuracy. Furthermore, the motor's inability to evenly distribute launch stress makes the drone's components within the launch tube more susceptible to damage due to uneven stress, weakening structural stability. Moreover, continuous motor involvement in positioning significantly increases energy consumption, shortening the drone's flight time and accelerating motor aging due to frequent current fluctuations, increasing maintenance costs and frequency, and impacting the overall lifespan and reliability of the drone. Utility Model Content

[0005] The purpose of this invention is to provide a portable folding-wing drone structure that can solve the technical problem in the prior art that the main body of the drone is difficult to cope with the strong impact force at the moment of launch and is not easy to stabilize the wings.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a portable folding-wing drone structure, comprising a drone body, an upper wing at the top of the drone body, a lower wing at the bottom of the drone body, a side wing on each side of the drone body, support members on both sides of the drone body, push rods on the inner sides of the two support members, pressure plates on the sides of the push rods, and upper and lower locking rods on the inner sides of the two support members.

[0007] Furthermore, the two upper wings are a group, and the two upper wings are rotatably connected to the top of the drone body, and the two upper wings are arranged in upper and lower layers. The two lower wings are a group, and the two lower wings are rotatably connected to the bottom of the drone body, and the two lower wings are arranged in upper and lower layers. The two side wings are rotatably connected to both sides of the drone body.

[0008] Furthermore, slide bars are fixed on both sides of the drone body, and two push rods are slidably connected to the outside of the two slide bars. Spring 1 is fixed on both sides of the drone body, and anti-detachment plate is fixed on the other end of spring 1. The anti-detachment plate is fixed to the outside of the push rod near the drone body.

[0009] Furthermore, the support includes two sets of support rods, with the two support rods forming a set. Each support rod is fixed to one side of the drone body, and a slide rail is fixed to the side of each set of support rods away from the drone body. The push plate is fixed to the outside of the push rod.

[0010] Furthermore, the upper locking rod is slidably engaged with the inner side of the two slide rails, and the lower locking rod is engaged with the inner side of the two slide rails, with the upper locking rod located on top of the lower locking rod. The push plate is located inside the upper and lower locking rods. Springs are fixed to the bottom of the top wall and the top of the bottom wall of the two slide rails. The other ends of the two springs at the bottom of the top wall of the two slide rails are fixedly connected to the upper locking rod, and the other ends of the two springs at the top of the bottom wall of the two slide rails are fixedly connected to the lower locking rod.

[0011] Furthermore, two round rods are fixed to the other end of the drone body. Support plates are fixed to the ends of the two round rods located on the same side of the drone body away from the drone body. Two springs are fixed to both sides of the drone body. The springs are located on the outside of the round rods. Pressure plates are fixed to the other ends of the two springs. The pressure plates are slidably engaged with the outside of the round rods, and the pressure plates are located on the side of the wing away from the drone body.

[0012] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0013] 1. This utility model, by setting up a push rod, an upper clamping rod, and a lower clamping rod, squeezes two push plates, which can not only push the two upper clamping rods and the lower clamping rod to fix the upper and lower wings, but also fix the side wings, preventing the upper wings, lower wings and side wings from shaking to both sides during launch. Compared with the prior art, it prevents the wing and side wing shaking from causing attitude changes and turbulence, improves launch accuracy, reduces wind interference, enhances structural reliability, evenly distributes launch stress, protects connecting parts, and avoids the risk of component damage and loss of control.

[0014] 2. During the launch phase, this invention effectively prevents the upper wing, lower wing, and side wings from shaking to the sides by fixing the push rod in the launch tube. This ensures the wings maintain the correct attitude at launch, reduces directional deviation, and improves launch accuracy. Simultaneously, it makes the force on the aircraft more even within the launch tube, enhancing structural stability. After launch, the push rod returns to its original position, releasing the restriction on the wings and side wings, allowing them to freely exert their aerodynamic effects. This enables the aircraft to flexibly adjust its attitude and achieve optimal flight performance. It also avoids the additional friction and stress caused by continuous restriction, reducing component wear and extending service life. Attached Figure Description

[0015] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0016] Figure 2 This is a schematic cross-sectional view of the upper wing of this utility model.

[0017] Figure 3 This is a three-dimensional structural diagram of the support component of this utility model;

[0018] Figure 4 This is a three-dimensional structural diagram of the push rod of this utility model;

[0019] Figure 5 This is a cross-sectional structural diagram of the push rod of this utility model.

[0020] In the diagram: 1. Main body of the drone; 2. Upper wing; 3. Side wing; 4. Lower wing; 5. Push rod; 51. Slide rod; 52. Anti-detachment plate; 6. Support component; 61. Support rod; 62. Slide rail; 63. Push plate; 7. Pressure plate; 71. Round rod; 72. Support plate; 8. Upper locking rod; 9. Lower locking rod. Detailed Implementation

[0021] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0022] In the description of this utility model, it should be noted that the terms "upper," "lower," "inner," "outer," "front end," "rear end," "both ends," "one end," and "the other end," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0023] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," "connected," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0024] Please see Figures 1-5 A portable folding-wing drone structure includes a drone body 1, an upper wing 2 on the top of the drone body 1, a lower wing 4 on the bottom of the drone body 1, a side wing 3 on each side of the drone body 1, support members 6 on both sides of the drone body 1, push rods 5 on the inner side of the two support members 6, pressure plates 7 on the side of the push rods 5 that are close to each other, upper locking rods 8 and lower locking rods 9 on the inner side of the two support members 6, the two upper wings 2 are a set and are rotatably connected to the top of the drone body 1, and the two upper wings 2 are arranged in upper and lower layers, the two lower wings 4 are a set and are rotatably connected to the bottom of the drone body 1, and the two lower wings 4 are arranged in upper and lower layers, and the two side wings 3 are rotatably connected to the two sides of the drone body 1 respectively.

[0025] In this embodiment, after launch, when the two push rods 5 are removed from the launch tube, the two springs 1 push the two push rods 5 back to their original positions through the two anti-detachment plates 52, the two springs 2 push the two upper locking rods 8 and the two lower locking rods 9 back to their original positions, and the two springs 3 push the pressure plate 7 back to its original position, thus releasing the restriction on the upper wing 2, the lower wing 4 and the side wing 3. When the UAV body 1 reaches the designated position, the UAV body 1 controls the upper wing 2, the lower wing 4 and the side wing 3 to open, and then performs the mission.

[0026] Specifically, slide rods 51 are fixed on both sides of the drone body 1, and two push rods 5 are slidably connected to the outer sides of the two slide rods 51. Springs 1 are fixed on both sides of the drone body 1, and anti-detachment plates 52 are fixed to the other end of the springs 1. The anti-detachment plates 52 are fixed to the outer side of the push rods 5 near the drone body 1. The support member 6 includes two sets of support rods 61, and the two support rods 61 form a set. Each support rod 61 is fixed to one side of the drone body 1, and a slide rail 62 is fixed to the side of each set of support rods 61 away from the drone body 1. The push plate 63 is fixed to the outside of the push rod 5. The upper locking rod 8 is slidably locked to the inside of the two slide rails 62. The lower locking rod 9 is locked to the inside of the two slide rails 62, and the upper locking rod 8 is located on top of the lower locking rod 9. The push plate 63 is located inside the upper locking rod 8 and the lower locking rod 9. The bottom of the top wall and the top of the bottom wall of the two slide rails 62 are both fixed with springs II. The other ends of the two springs II at the bottom of the top wall of the two slide rails 62 are fixedly connected to the upper locking rod 8. The other ends of the two springs II at the top of the bottom wall of the two slide rails 62 are fixedly connected to the lower locking rod 9.

[0027] In this embodiment, the operator pushes the two push rods 5 towards the side closer to the main body 1 of the drone. The two push rods 5 press the two springs 1 along the outside of the two slide rods 51 through the two anti-detachment plates 52. The two push rods 5 push the two push plates 63 to move towards the side closer to the main body 1 of the drone. The two push plates 63 push the upper clamping rod 8 and the lower clamping rod 9 to move along the inside of the slide rail 62. The upper clamping rod 8 and the lower clamping rod 9 move towards the side away from each other. The upper clamping rod 8 and the lower clamping rod 9 press the spring 2 that is fixedly connected to them. When the spring 1 is compressed to its limit, the push plate 63 is located on the side close to the upper clamping rod 8 and the lower clamping rod 9. At this time, the two upper clamping rods 8 are located on both sides of the two upper wings 2, and the two lower clamping rods 9 are located on both sides of the two lower wings 4, thereby restricting the upper wings 2 and the lower wings 4.

[0028] Specifically, two round rods 71 ​​are fixed to the other end of the drone body 1. The two round rods 71 ​​located on the same side of the drone body 1 have support plates 72 fixed to the ends away from the drone body 1. Two springs 3 are fixed to both sides of the drone body 1. The springs 3 are located on the outside of the round rods 71. The other ends of the two springs 3 are fixed with pressure plates 7. The pressure plates 7 are slidably engaged with the outside of the round rods 71, and the pressure plates 7 are located on the side of the side wing 3 away from the drone body 1.

[0029] In this embodiment, after the push plate 63 contacts the pressure plate 7, the push plate 63 pushes the pressure plate 7 to move closer to the side of the UAV body 1. The push plate 63 compresses the spring 3 along the outside of the round rod 71. When the spring 1 is compressed to the limit, the pressure rod is located outside the side wing 3, thereby restricting the side wing 3. Then, this device is placed inside the launch tube. The launch tube fixes the two push rods 5, thereby preventing the launch failure caused by the vibration and collision with the launch tube during launch.

[0030] Working principle: Before using the device, check whether there are any problems that may affect its use. The operator pushes the two push rods 5 towards the side closer to the main body 1 of the drone. The two push plates 63 push the upper locking rod 8 and the lower locking rod 9 towards the side away from each other. When the push plate 63 contacts the pressure plate 7, the push plate 63 pushes the pressure plate 7 towards the side closer to the main body 1 of the drone. When the spring is compressed to its limit, the push plate 63 is located on the side close to the upper locking rod 8 and the lower locking rod 9. At this time, the two upper locking rods 8 are located on both sides of the two upper wings 2, the two lower locking rods 9 are located on both sides of the two lower wings 4, and the pressure rod is located on the outside of the side wing 3. Then, the device is placed inside the launch tube. The launch tube fixes the two push rods 5, thereby preventing the upper wings 2, lower wings 4 and side wings 3 from shaking and colliding with the launch tube during launch, which would cause launch failure.

[0031] After launch, when the two push rods 5 are removed from the launch tube, the two springs push the two push rods 5 back to their original positions through the two anti-detachment plates 52, releasing the restriction on the upper wing 2, lower wing 4 and side wing 3. When the UAV body 1 reaches the designated position, the UAV body 1 controls the upper wing 2, lower wing 4 and side wing 3 to open, and then carries out the mission.

[0032] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

Claims

1. A portable folding-wing drone structure, comprising a drone body (1), characterized in that: The top of the drone body (1) is provided with a set of upper wings (2), the bottom of the drone body (1) is provided with a set of lower wings (4), and a side wing (3) is provided on each side of the drone body (1). Support members (6) are provided on both sides of the drone body (1). Push rods (5) are provided on the inner side of the two support members (6). A pressure plate (7) is provided on the side of the push rods (5) that are close to each other. An upper clamping rod (8) and a lower clamping rod (9) are provided on the inner side of the two support members (6).

2. The portable folding-wing drone structure according to claim 1, characterized in that: The two upper wings (2) are a group, and the two upper wings (2) are rotatably connected to the top of the UAV body (1), and the two upper wings (2) are arranged in upper and lower layers. The two lower wings (4) are a group, and the two lower wings (4) are rotatably connected to the bottom of the UAV body (1), and the two lower wings (4) are arranged in upper and lower layers. The two side wings (3) are rotatably connected to the two sides of the UAV body (1).

3. The portable folding-wing UAV structure according to claim 1, characterized in that: Both sides of the drone body (1) are fixed with slide rods (51), and two push rods (5) are slidably connected to the outside of the two slide rods (51). Both sides of the drone body (1) are fixed with springs, and the other end of the springs is fixed with anti-detachment plates (52). The anti-detachment plates (52) are fixed to the outside of the push rods (5) near the drone body (1).

4. The portable folding-wing UAV structure according to claim 3, characterized in that: The support member (6) includes two sets of support rods (61), and the two support rods (61) form a set. Each support rod (61) is fixed to one side of the UAV body (1). Each set of support rods (61) has a slide rail (62) fixed on the side away from the UAV body (1). The push plate (63) is fixed to the outside of the push rod (5).

5. The portable folding-wing drone structure according to claim 4, characterized in that: The upper locking rod (8) is slidably locked to the inner side of the two slide rails (62), and the lower locking rod (9) is locked to the inner side of the two slide rails (62). The upper locking rod (8) is located on top of the lower locking rod (9), and the push plate (63) is located inside the upper locking rod (8) and the lower locking rod (9). The bottom of the top wall and the top of the bottom wall of the two slide rails (62) are both fixed with springs II. The other ends of the two springs II at the bottom of the top wall of the two slide rails (62) are fixedly connected to the upper locking rod (8), and the other ends of the two springs II at the top of the bottom wall of the two slide rails (62) are fixedly connected to the lower locking rod (9).

6. The portable folding-wing drone structure according to claim 5, characterized in that: Two round rods (71) are fixed to the other end of the main body (1) of the drone. The two round rods (71) located on the same side of the main body (1) are respectively fixed with a support plate (72) at the end away from the main body (1). Two springs are fixed to both sides of the main body (1). The springs are located on the outside of the round rods (71). The other end of the two springs is fixed with a pressure plate (7). The pressure plate (7) is slidably engaged with the outside of the round rods (71), and the pressure plate (7) is located on the side of the wing (3) away from the main body (1).

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