Tail wing folding mechanism of folding-wing UAV

Abstract

The present invention discloses a tail folding mechanism of a folding-wing UAV, comprising a fixing part, a torsion spring, a fixing part pressure cover and a rotating movable part, wherein the fixing part is internally sleeved and connected with the rotating movable part, the rotating movable part is internally sleeved and connected with the torsion spring, one end of the torsion spring is fixedly connected with the middle part of the fixing part, and one end of the rotating movable part is interlaced and connected with the middle part of the fixing part pressure cover. The present invention has a simple structure, is easy to install, occupies little space, can be used when the tail is rotated and folded along a certain rotation axis of any plane of the fuselage, has a wider scope of application, and during use, the tail will be quickly unfolded under the torsion of the torsion spring, effectively improving the unfolding efficiency of the tail without additional power loss.

Description

Technical Field

[0001] The invention relates to a tail folding mechanism of an unmanned aerial vehicle, in particular to a tail folding mechanism of a folding-wing unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. Background Art

[0002] In today's society, the application of drones is becoming more and more extensive, and the take-off methods are becoming more and more diverse. Since the runway take-off and landing drones have high requirements for the take-off site, drones with various take-off and landing methods such as vertical take-off and landing, catapult, tube launch, and aerial drop have been developed.

[0003] Many times, a single aircraft cannot independently complete complex tasks, so the idea of ​​swarm UAV collaboration comes into being. Swarm UAVs are mostly launched by tube launch or aerial drop, which requires the UAV to occupy a small space, and each wing surface can be folded, and the wing surface can be quickly unfolded after launch. Usually, there are two folding and unfolding drive methods: electric drive and mechanical drive: electric drive can drive the wing surface movement by controlling the servo or motor, but the disadvantages are obvious, the unfolding speed is slow, and additional power loss is required during flight; mechanical drive is generally driven by spring elastic force, which has a simple structure, fast unfolding speed, and no additional power loss. Summary of the invention

[0004] The purpose of the present invention is to provide a tail folding mechanism for a folding-wing UAV to solve the problem that the electric drive proposed in the above background technology can drive the wing surface to move by controlling a servo or a motor, but has obvious disadvantages, such as a slow unfolding speed and the need for additional power loss during flight.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solution: it includes a fixed part, a torsion spring, a fixed part cover and a rotating movable part, the internal sleeve of the fixed part is connected to the rotating movable part, the internal sleeve of the rotating movable part is connected to the torsion spring, one end of the torsion spring is fixedly connected to the middle part of the fixed part, and one end of the rotating movable part is interlaced and connected to the middle part of the fixed part cover.

[0006] As a preferred technical solution of the present invention, the fixing part includes a fixing part torsion spring mounting hole, a fixing part limiting groove and a fixing part mounting hole, a fixing part torsion spring mounting hole is opened in the middle of one end of the fixing part, fixing part limiting grooves are opened on both sides of one end of the fixing part, and four fixing part mounting holes are opened at equal distances on the side of the fixing part.

[0007] As a preferred technical solution of the present invention, the torsion spring includes a torsion spring fixed end torsion arm and a torsion spring movable end torsion arm, one end of the torsion spring is fixed with a torsion spring fixed end torsion arm, the other end of the torsion spring is fixed with a torsion spring movable end torsion arm, and the torsion spring fixed end torsion arm is interlaced and connected with the torsion spring mounting hole of the fixing member.

[0008] As a preferred technical solution of the present invention, the fixing member gland includes a fixing member gland installation hole, a circular hole is opened at the center of the fixing member gland, and fixing member gland installation holes are opened on four sides of the fixing member gland.

[0009] As a preferred technical solution of the present invention, the rotating movable part includes a movable part torsion spring slot, a movable part limiting protrusion and a movable part tail wing mounting end. A movable part torsion spring slot is opened at the center of the movable part, and the movable part torsion spring slot is embedded and connected with the torsion arm of the movable end of the torsion spring. Two movable part limiting protrusions are symmetrically fixed on both sides of one end of the movable part, and the two movable part limiting protrusions are interlaced and connected with the fixed part limiting slot. A movable part tail wing mounting end is fixed at the center of the other end of the movable part, and the movable part tail wing mounting end is interlaced and connected with the circular hole opened at the center of the fixed part pressure cover.

[0010] As a preferred technical solution of the present invention, the fixing member installation hole is aligned with the fixing member gland installation hole, and the inner diameter of the fixing member installation hole matches the inner diameter of the fixing member gland installation hole.

[0011] As a preferred technical solution of the present invention, the inner diameter of the torsion spring mounting hole of the fixing member matches the size of the torsion arm end of the torsion spring fixed end.

[0012] As a preferred technical solution of the present invention, the internal dimensions of the fixed part match the dimensions of the rotating movable part.

[0013] Compared with the prior art, the present invention has the following beneficial effects:

[0014] The present invention discloses a tail folding mechanism for a folding-wing UAV. The present invention has a simple structure, is easy to install, occupies little space, can be used when the tail is rotated and folded along a certain rotation axis in any plane of the fuselage, and has a wider scope of application. During use, the tail can be quickly unfolded under the torsion of the torsion spring, effectively improving the unfolding efficiency of the tail without any additional power loss. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the structure of the present invention;

[0016] Figure 2 It is a schematic diagram of the assembly structure of the present invention;

[0017] Figure 3 It is a schematic diagram of the torsion spring structure of the present invention.

[0018] In the figure: 1. fixing part; 1-1. fixing part torsion spring mounting hole; 1-2. fixing part limiting groove; 1-3. fixing part mounting hole; 2. torsion spring; 2-1. torsion arm at fixed end of torsion spring; 2-2. torsion arm at movable end of torsion spring; 3. fixing part pressure cover; 3-1. fixing part pressure cover mounting hole; 4. rotating movable part; 4-1. torsion spring slot of movable part; 4-2. movable part limiting groove; 4-3. movable part tail wing mounting end. DETAILED DESCRIPTION

[0019] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0020] See also Figure 1-3 The present invention provides a technical solution for a tail folding mechanism of a folding-wing UAV:

[0021] according to Figure 1-3 As shown, it includes a fixed part 1, a torsion spring 2, a fixed part cover 3 and a rotating movable part 4. The internal sleeve of the fixed part 1 is connected to the rotating movable part 4, and the internal sleeve of the rotating movable part 4 is connected to the torsion spring 2. One end of the torsion spring 2 is fixedly connected to the middle part of the fixed part 1, and one end of the rotating movable part 4 is inserted and connected to the middle part of the fixed part cover 3.

[0022] according to Figure 1 and Figure 2 As shown, the fixing part 1 includes a fixing part torsion spring mounting hole 1-1, a fixing part limiting groove 1-2 and a fixing part mounting hole 1-3. A fixing part torsion spring mounting hole 1-1 is opened in the middle of one end of the fixing part 1 to facilitate fixing one end of the torsion spring 2. Fixing part limiting grooves 1-2 are opened on both sides of one end of the fixing part 1 to limit the rotating movable part 4. Four fixing part mounting holes 1-3 are opened at equal distances on the side of the fixing part 1 to facilitate the installation of the fixing part 1.

[0023] The torsion spring 2 includes a torsion spring fixed end torsion arm 2-1 and a torsion spring movable end torsion arm 2-2. One end of the torsion spring 2 is fixedly provided with the torsion spring fixed end torsion arm 2-1, and the other end of the torsion spring 2 is fixedly provided with the torsion spring movable end torsion arm 2-2. The torsion spring fixed end torsion arm 2-1 is interlaced and connected with the torsion spring mounting hole 1-1 of the fixing part.

[0024] The fixing member gland 3 comprises a fixing member gland installation hole 3 - 1 , a circular hole is opened at the center of the fixing member gland 3 , and fixing member gland installation holes 3 - 1 are opened on the four sides of the fixing member gland 3 , which is convenient for the installation of the fixing member gland 3 .

[0025] The rotating movable part 4 includes a movable part torsion spring slot 4-1, a movable part limiting protrusion 4-2 and a movable part tail wing mounting end 4-3. A movable part torsion spring slot 4-1 is opened at the center of the movable part 4. The movable part torsion spring slot 4-1 is embedded and connected with the torsion spring movable end torsion arm 2-2. Two movable part limiting protrusions 4-2 are symmetrically fixed on both sides of one end of the movable part 4. The two movable part limiting protrusions 4-2 are connected through the fixed part limiting slot 1-2. A movable part tail wing mounting end 4-3 is fixed at the center of the other end of the movable part 4. The movable part tail wing mounting end 4-3 is connected through the circular hole opened at the center of the fixed part pressure cover 3.

[0026] The positions of the fixing part mounting hole 1-3 and the fixing part pressure cover mounting hole 3-1 are aligned, and the inner diameter of the fixing part mounting hole 1-3 matches the inner diameter of the fixing part pressure cover mounting hole 3-1 to ensure the embedding of the fixing part pressure cover mounting hole 3-1, the inner diameter of the fixing part torsion spring mounting hole 1-1 matches the size at the end of the torsion arm 2-1 at the fixed end of the torsion spring, and the size inside the fixing part 1 matches the size of the rotating movable part 4.

[0027] During specific use, the present invention provides a tail folding mechanism for a folding-wing UAV. When the tail folding mechanism needs to be used, first, the torsion spring fixed end torsion arm 2-1 of the torsion spring 2 is inserted into the torsion spring mounting hole 1-1 of the fixing part, and the torsion spring movable end torsion arm 2-2 of the torsion spring 2 is snapped into the movable part torsion spring slot 4-1 of the rotating movable part 4. The intermediate shaft of the rotating movable part 4 passes through the torsion spring 2 and is installed in the fixing part 1. At this time, the movable part limit 4-2 of the rotating movable part 4 is just snapped into the fixed part limit slot 1-2 on the fixing part 1. The movable part limit 4-2 and the fixed part limit slot 1-2 cooperate to limit the rotation angle of the tail folding and unfolding, which is designed to be 90° limit here. The movable part tail wing mounting end 4-3 passes through the through hole at the center of the fixing part pressure cover 3 and is connected to the tail. When the rotating movable part 4 rotates, it can drive the tail wing to rotate and fold together. Then the folding mechanism is installed to the tail wing fitting plane with screws through the fixing part cover mounting hole 3-1 and the fixing part mounting hole 1-3 of the fixing part 1. At this time, the fixing part cover 3 can limit the axial position of the rotating movable part 4, and prevent the rotating movable part 4 from rubbing against the body when rotating. When the UAV is not launched, the tail wing is in a folded state and close to the inner wall of the launching tube. The unfolding of the tail wing is limited by the inner wall of the tube. At this time, the torsion spring 2 is in a torsional limit compression state, and the torque of the two torsion arms is also the largest. After the UAV is launched, the tail wing is no longer constrained by the tube wall, and will quickly unfold under the torque of the torsion spring 2. When the movable part limit 4-2 reaches the limit position of the fixing part limit groove 1-2, the tail wing stops rotating and is fully unfolded.

[0028] In the description of the present invention, it is necessary to understand that the indicated orientation or positional relationship is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0029] In the present invention, unless otherwise clearly stipulated and limited, for example, it can be a fixed connection, a detachable connection, or an integrated one; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. Unless otherwise clearly defined, for ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0030] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A tail folding mechanism for a folding-wing UAV, comprising a fixing member (1), a torsion spring (2), a fixing member gland (3) and a rotating movable member (4), characterized in that: The interior of the fixed part (1) is sleeved with a rotating movable part (4), and the interior of the rotating movable part (4) is sleeved with a torsion spring (2); The fixing member (1) comprises a fixing member torsion spring mounting hole (1-1), a fixing member limiting groove (1-2) and a fixing member mounting hole (1-3); the fixing member torsion spring mounting hole (1-1) is provided in the middle of one end of the fixing member (1), and the fixing member limiting grooves (1-2) are provided on both sides of one end of the fixing member (1); The torsion spring (2) comprises a torsion spring fixed end torsion arm (2-1) and a torsion spring movable end torsion arm (2-2); the torsion spring fixed end torsion arm (2-1) is interlacedly connected with the torsion spring mounting hole (1-1) of the fixing member; The fixing part pressure cover (3) comprises a fixing part pressure cover mounting hole (3-1), and a circular hole is provided at the center of the fixing part pressure cover (3); the rotating movable part (4) comprises a movable part torsion spring slot (4-1), a movable part limiting protrusion (4-2) and a movable part tail wing mounting end (4-3); a movable part torsion spring slot (4-1) is provided at the center of the movable part (4), the movable part torsion spring slot (4-1) is embedded and connected with the torsion spring movable end torsion arm (2-2), two movable part limiting protrusions (4-2) are symmetrically fixed on both sides of one end of the movable part (4), the two movable part limiting protrusions (4-2) are connected through the fixing part limiting slot (1-2), a movable part tail wing mounting end (4-3) is fixed at the center of the other end of the movable part (4), and the movable part tail wing mounting end (4-3) is connected through the circular hole provided at the center of the fixing part pressure cover (3).

2. The tail folding mechanism of a folding-wing UAV according to claim 1, characterized in that: The four sides of the fixing member cover (3) are all provided with fixing member cover mounting holes (3-1).

3. The tail folding mechanism of a folding-wing UAV according to claim 1, characterized in that: The fixing component installation hole (1-3) is aligned with the fixing component pressure cover installation hole (3-1), and the inner diameter of the fixing component installation hole (1-3) matches the inner diameter of the fixing component pressure cover installation hole (3-1).

4. The tail folding mechanism of a folding-wing UAV according to claim 1, characterized in that: The inner diameter of the torsion spring mounting hole (1-1) of the fixing member matches the size of the end of the torsion arm (2-1) at the fixed end of the torsion spring.

5. The tail folding mechanism of a folding-wing UAV according to claim 1, characterized in that: The dimensions inside the fixed part (1) match the dimensions of the rotating movable part (4).

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