Patent Description:
With the development of the times, the composite wing UAV is used increasingly widely. The aircraft has the multi-rotor parachute protection function. In the fixed-wing flight state, if there are large flying attitude, steering gear failure, and thrust motor failure, the aircraft will automatically start the multi-rotor protection function to ensure the safety of the aircraft. The composite wing UAV usually has two long wings to ensure the aircraft's long-term and long-distance cruise, but the long wings increase the difficulty of aircraft transportation and reduce the flexibility and convenience of the aircraft. The locking structures of the existing detachable wings are mostly complex, and to ensure the connection strength, it's a little difficult to disassemble and assemble the UAV. <CIT> relates to an aircraft, where a locking mechanism and a connecting piece are arranged inside the fuselage and the wing, respectively. The locking mechanism includes a fixed base, an elastic element, and a locking plate connected in sequence, as well as a pressing member. The locking plate and the fixed base are provided with a channel for the connecting piece to pass through. The pressing member is provided with a connecting hole in the size of the channel. The connecting piece includes a lock pin and a fixed rod, and the outer circumferential surface of an end of the lock pin is provided with a first annular groove, and the locking plate is locked in the first annular groove. <CIT> relates to a device for rapidly disassembling a wing of a drone. <CIT> relates to a quick-release and quick-lock structure. <CIT> relates to a plug mounting for a detachable fastening of an equipment part.

Therefore, there is an urgent need for a quick-release wing structure and a UAV to solve the above problems.

This invention aims to provide a quick-release wing structure and a UAV. The operation is convenient and fast, and it is convenient for wing to be disassembled and replacement with high stability and reliability.

To solve the above technical problem, the present invention provides a quick-release wing structure, having the features defined in claim <NUM>. Further preferred embodiments are provided in the dependent claims.

An unmanned aerial vehicle comprises the quick-release wing structure according to any one of the preceding solutions.

The invention has the beneficial effects that:
The invention provides a quick-release wing structure, comprising a lock cylinder assembly and a lock head. By installing the lock cylinder assembly in the fuselage and the lock head in the wing, the wing and fuselage can be quickly disassembled and replaced, which is convenient for the replacement and maintenance of the wing. During the process of the rapid installation of the wing, the lock head is extended into the clamping hole, so that the lock head pushes the lock plate to move. When the locking slot on the lock head is facing the lock plate because the lock plate can slide, the lock plate can clamp the locking slot. At the same time, under the limit of the clamping hole, the lock head cannot move freely, and the locking slot cannot separate itself from the lock plate, that is, the lock head and the lock cylinder assembly are clamped, thus completing the installation of the wing. When the wing needs to be removed, just move the lock plate to make it out of the locking slot, and then pull the lock head to exit the lock cylinder assembly along the clamping hole, thus completing the removal. Using the above structure, the lock head in the wing is inserted into the lock cylinder assembly in the fuselage and automatically locked without other operations, and the operation is convenient and fast. After the locking process, the locking plate and the clamping hole jointly limit the movement of the lock head, which has high stability, better locking effect and higher reliability.

In order to more clearly explain the technical solution in the embodiments of the invention, the following will briefly introduce the drawings needed in the description of the embodiments of the invention. Obviously, the drawings in the following description are only some embodiments of the invention. For ordinary technicians in the field, other drawings can also be obtained according to the contents of the embodiments of the invention and these drawings.

In the drawings:
<NUM> fuselage; <NUM> wing; <NUM> Unmanned aerial vehicle; <NUM> lock cylinder assembly; <NUM> shell; <NUM> lock plate; <NUM> bolt; <NUM> clip; <NUM> elastic fragment; <NUM> elastic part; <NUM> lock head; <NUM> installation slot; <NUM> clamping hole; <NUM> locking slot; <NUM> sliding hole; <NUM> locking hole; <NUM> arc-shaped groove; <NUM> limit slot.

The invention will be further described in detail with the attached drawings and embodiments. It can be understood that the specific embodiments described here are only used to explain the invention, not to limit the invention. In addition, it should be noted that for the convenience of description, the attached drawings may only show part of the structure related to the invention, not the whole structure.

In the description of the invention, the terms "connected", "connected" and "fixed" should be understood in a broad sense, unless otherwise specified and limited, for example, they can be fixed connections, detachable connections, or integrated; It can be mechanical connection or electrical connection; It can be directly connected, or indirectly connected through intermediate media, or it can be the internal connection of two components or the interaction between two components. For those skilled in the art, the specific meaning of the above terms in the invention can be understood in a specific case.

In this invention, unless otherwise clearly defined and limitation, the "up" or "down" of the first feature in the second feature can include the direct contact of the first and second features, or the contact of the first and second features through other features between them instead of direct contact. Moreover, the first feature "above" the second feature, including the first feature being directly above and diagonally above the second feature, or only indicates that the horizontal height of the first feature is higher than the second feature. Wherein the first feature being "below" of the second feature include the first feature directly below and diagonally below the second feature, or only indicate that the horizontal height of the first feature is less than the second feature.

In the description of this embodiment, the terms "up", "down", "left", "right" and other orientation or position relations are based on the orientation or position relations shown in the attached drawings, which are only for the convenience of description and simplification of operation, 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, so they can or cannot be understood as restrictions on the invention. In the description of the invention, unless otherwise stated, "multiple" means two or more. In addition, the terms "first" and "second" are only used to distinguish between descriptions and have no special meaning.

As shown in <FIG>, this embodiment provides a quick-release wing structure. The quick-release wing structure includes a lock cylinder assembly <NUM> and a lock head <NUM>. The lock cylinder assembly <NUM> can be installed in the fuselage <NUM>. The lock cylinder assembly <NUM> includes a shell <NUM> and a lock plate <NUM>. The shell <NUM> is internally provided with an installation slot <NUM>. The side wall of the installation slot <NUM> is provided with a clamping hole <NUM> connected with the installation slot <NUM>, and the lock plate <NUM> is sliding in the installation slot <NUM>. The lock head <NUM> is installed in the wing <NUM>. The locking slot <NUM> is set on the periphery of the lock head <NUM>. The lock head <NUM> can pass through the clamping hole <NUM> and drive the lock plate <NUM> to move. When the locking slot <NUM> is facing the lock plate <NUM>, the lock head <NUM> is clamped onto the locking slot <NUM> and fixed, and the lock head <NUM> is limited to the clamping hole <NUM>. In this embodiment, when the lock plate <NUM> is in the initial position, the lock plate <NUM> may partially cover the clamping hole <NUM>, so that when the lock head <NUM> moves into the clamping hole <NUM>, it can push the lock plate <NUM>, and when the lock head <NUM> moves to the locking slot <NUM> directly facing the lock plate <NUM>, the lock plate <NUM> can move towards the locking slot <NUM>, so that the lock plate <NUM> can be able to clamp into the locking slot <NUM>. Optionally, the other side wall of the installation slot <NUM> can also be provided with a clamping hole <NUM>. When the front end of the lock head <NUM> is longer, the lock head <NUM> can pass through the two clamping holes <NUM> in turn.

When rapidly installing the wing <NUM>, extend the lock head <NUM> into the clamping hole <NUM>, so that the lock head <NUM> pushes the lock plate <NUM> to move. When the locking slot <NUM> on the lock head <NUM> is facing the lock plate <NUM>, the lock plate <NUM> clamps the locking slot <NUM>. At the same time, under the limitation of the clamping hole <NUM>, the lock head <NUM> cannot move freely, and the locking slot <NUM> cannot automatically disengage from the lock plate <NUM>, that is, the lock head <NUM> is clamped with the lock cylinder assembly <NUM> to complete the installation of the wing <NUM>. When the wing <NUM> needs to be removed, just move the lock plate <NUM> to make it separate from the locking slot <NUM>, and then pull the lock head <NUM> to exit the lock cylinder assembly <NUM> along the clamping hole <NUM> to complete the removal. Under the above quick-release structure, the lock head <NUM> in the wing <NUM> is inserted into the lock cylinder assembly <NUM> in the fuselage <NUM> and then automatically locked, without other operations, which is convenient and fast. After the locking process, the lock plate <NUM> and the clamping hole <NUM> jointly limit the movement of the lock head <NUM>, which has high stability, better locking effect and higher reliability.

Preferably, the front end of the lock head <NUM> is cone-shaped, which facilitates the front end of the lock head <NUM> to contact the lock plate <NUM> and push the lock plate <NUM> to move. For example, the lock head <NUM> moves in the first direction. When the conical front end of the lock head <NUM> contacts the lock plate <NUM> and continues to move, the lock plate <NUM> moves in the second direction along the conical front end, and the first direction is perpendicular to the second direction, thus improving the smoothness of disassembly and assembly of the wing <NUM> and the fuselage <NUM>.

Preferably, the lock plate <NUM> and the lock head <NUM> are made of metal materials with high strength and high bearing capacity, thus improving the connection between the wing <NUM> and the fuselage <NUM>.

As shown in <FIG>, the locking process of lock head <NUM> and lock cylinder assembly <NUM> is shown. Specifically, the lock cylinder assembly <NUM> includes a bolt <NUM> and an elastic part <NUM>. The bolt <NUM> slides along the groove depth direction of the installation slot <NUM> and is arranged in the installation slot <NUM>. The inner wall of the bolt <NUM> is provided with a through hole for installation, the lock plate <NUM> is embedded in the through hole for installation, and the lock plate <NUM> is fixedly connected to the bolt <NUM>. The two ends of the elastic part <NUM> are respectively connected to the bottom of the installation slot <NUM> and one end of the bolt <NUM>. Under the action of the elastic part <NUM>, the bolt <NUM> is pressed to the initial position. When the lock head <NUM> extends into the clamping hole <NUM> and moves, the lock head <NUM> pushes the lock plate <NUM>, drives the bolt <NUM> to move, and the bolt <NUM> compresses the elastic part <NUM>. When the lock head <NUM> moves to the locking slot <NUM> facing the lock plate <NUM>, under the reset action of the elastic part <NUM>, the bolt <NUM> faces the initial position, moving the lock plate <NUM> to clamp the locking slot <NUM>. When the end of the bolt <NUM> which is away from the elastic part <NUM> is pushed to move towards the elastic part <NUM>, the lock plate <NUM> is driven to disengage from the locking slot <NUM>, so that the lock head <NUM> can be pulled out from the clamping hole <NUM>, and the removal of the wing <NUM> is completed, which is easy to operate. And because the lock plate <NUM> needs to be matched with the locking slot <NUM>, so the lock plate <NUM> is thin. The lock plate <NUM> is embedded in the bolt <NUM> to improve the strength and pressure bearing capacity of the lock plate <NUM>, ensuring the stability of the lock plate <NUM>, and avoid the shaking of the lock plate <NUM> caused by stress, improving the lifespan and safety of the lock plate <NUM>. The elastic part <NUM> is optional but not limited to compression spring, which is cheap and easy to obtain, and has good structural strength and elastic force.

Preferably, the end of the bolt <NUM> that is away from the elastic part <NUM> extends out of the installation slot <NUM> and protrudes from the fuselage <NUM>, which is convenient to directly push the bolt <NUM>, and the removal of the wing <NUM> can be realized without the help of tools. More preferably, the end face of the bolt <NUM> away from the elastic part <NUM> is set as an inclined plane to match the shape of the fuselage <NUM> and improve the appearance beauty and smoothness of the fuselage <NUM>.

Preferably, a limit slot <NUM> is clamped at the bottom of the installation slot <NUM>, and one end of the elastic part <NUM> is embedded in the limit slot <NUM>. The setting of the limit slot <NUM> avoids the bending of the elastic part <NUM> during the movement and ensures the normal operation of the elastic part <NUM>, thus ensuring the normal operation of the bolt <NUM>, and improving the reliability of the quick-release wing structure in the using process. For example, the bottom of the installation slot <NUM> is provided with a through hole, the cover of the through hole is provided with a limit cap, and the limit slot <NUM> is limited in the limit cap. The limit slot <NUM> is connected with the through hole and the installation slot <NUM>. The setup of limit slot <NUM> can be achieved by the limit cap to avoid being limited by the thickness of the shell <NUM>, otherwise it will be resulting in the smaller depth of the limit slot <NUM> or the reduced strength of the shell <NUM>.

In this embodiment, the circumferential wall of the through-hole is provided with a clamping slot, the lock plate <NUM> is clamped in the clamping slot, the lock plate <NUM> is provided with a locking hole <NUM>, the part of the circumferential wall of the locking hole <NUM> is provided with an arc-shaped groove <NUM>, and the arc-shaped groove <NUM> is matched with the bottom of the locking slot <NUM>. By setting the slot, the lock plate <NUM> can be fixed in the slot with high stability. The four sides of the lock plate <NUM> are embedded in the slot to improve the force uniformity of the lock plate <NUM>, thus improving the reliability of the lock plate <NUM>. The contact area between the lock plate <NUM> and the locking slot <NUM> is increased and the pressure bearing capacity is improved by setting the arc-shaped groove <NUM> that is suitable for the locking slot <NUM>.

Preferably, part of the arc-shaped groove <NUM> is arranged on the lock plate <NUM>, which protrudes from the clamping slot, and the rest of the lock plate <NUM> is located in the clamping slot, so that the bearing force by this part can be transferred to other parts of the lock plate <NUM> and to the bolt <NUM>, further improving the stability of the quick-release wing structure.

Furthermore, the opposite sides of the shell <NUM> are respectively provided with sliding holes <NUM>, the sliding holes <NUM> are connected with the installation slots <NUM>, the opposite sides of the bolt <NUM> are respectively provided with clips <NUM>, and the two clips <NUM> are respectively connected to the two sliding holes <NUM> and can slide along the sliding holes <NUM>. The clip <NUM> is clamped in the sliding hole <NUM> so that the bolt <NUM> can not only be installed in the shell <NUM>, but also be moved. In addition, due to the elastic part <NUM>, when the clip <NUM> abuts against one end of the sliding hole <NUM>, the bolt <NUM> is in the initial position, that is, the initial position of the bolt <NUM> is determined by the fit of the clip <NUM> and the sliding hole <NUM>.

Specifically, the two opposite sides of the bolt <NUM> are respectively provided with collision avoidance slots, one end of the elastic fragment <NUM> is connected to the surrounding wall of the collision avoidance slot, and the other end is protruding outward and is provided with the above-mentioned clip <NUM>. Under the above structure, one end of the clip <NUM> set on the elastic fragment <NUM> can be pushed into the collision avoidance slot, so that the bolt <NUM> can be inserted into the installation slot <NUM>. When the elastic fragment <NUM> is released, the clip <NUM> will pop out automatically, until the clip <NUM> moves to the sliding hole <NUM>, the clip <NUM> will snap into the sliding hole <NUM> to realize the installation of the bolt <NUM> and the shell <NUM>. When the clip <NUM> is pressed again and the bolt <NUM> is pulled outward, the clip <NUM> exits the sliding hole <NUM>, and the bolt <NUM> exits along the installation slot <NUM> to realize the removal of the bolt <NUM>. It is not only simple in structure and convenient in operation, but also convenient for the replacement and maintenance of the bolt <NUM>, saving costs.

As shown in <FIG>, this embodiment also provides a UAV, which includes the above quick-release wing structure. First, install the lock cylinder assembly <NUM> in the fuselage <NUM>, the lock head <NUM> in the wing <NUM>, then insert the lock head <NUM> into the lock cylinder assembly <NUM> to achieve automatic locking, and push the bolt <NUM> to achieve the removal of the wing <NUM>. It is not only easy to operate, firm and stable to connect, but also convenient to transport the UAV with disassembled wing <NUM>, saving transportation costs.

Claim 1:
A quick-release wing structure, comprising:
a lock cylinder assembly (<NUM>) installed in a body (<NUM>), and the lock cylinder assembly (<NUM>) comprises a shell (<NUM>) and a lock plate (<NUM>);
the shell (<NUM>) is internally provided with an installation slot (<NUM>);
a side wall of the shell is provided with a clamping hole (<NUM>) which is connected with the installation slot (<NUM>), and the lock plate (<NUM>) is set in the installation slot (<NUM>) in a sliding manner;
a lock head (<NUM>) installed in a wing (<NUM>);
the lock head (<NUM>) is provided with a locking slot (<NUM>) on a periphery of the lock head;
wherein the lock head (<NUM>) passes through the clamping hole (<NUM>) to drive the lock plate (<NUM>) to move;
when the locking slot (<NUM>) is facing the lock plate (<NUM>), the lock head (<NUM>) is clamped onto the locking slot (<NUM>) and fixed,
the lock cylinder assembly (<NUM>) further comprising:
a bolt (<NUM>), which slides along the installation slot in its depth direction and is arranged in the installation slot (<NUM>);
the inner wall of the bolt (<NUM>) is provided with an installation through hole, the lock plate (<NUM>) is embedded in the installation through hole, and the lock plate (<NUM>) is fixedly connected to the bolt (<NUM>);
an elastic part (<NUM>) having two ends, wherein the two ends of the elastic part (<NUM>) are respectively connected with one end of the lock plate (<NUM>) and one end of the bolt (<NUM>),
wherein a circumferential wall of the installation through hole is provided with a clamping slot, the lock plate (<NUM>) is clamped in the clamping slot, the lock plate (<NUM>) is provided with a locking hole (<NUM>),
characterized in that,
a part of the circumferential wall of the locking hole (<NUM>) is provided with an arc-shaped groove (<NUM>), and the arc-shaped groove (<NUM>) is matched with a bottom of the locking slot (<NUM>), and wherein
a part of the arc-shaped groove (<NUM>) is arranged on the lock plate (<NUM>), which protrudes from the clamping slot, and the rest of the lock plate (<NUM>) is located in the clamping slot.