Pneumatic catapult foldable UAV self-locking device and method

Abstract

This invention relates to the field of unmanned aerial vehicle (UAV) technology, and provides a self-locking device and method for a pneumatically launched foldable UAV. The device includes a locking baffle, a locking connector, a locking support, a button connector, a button support, and a locking button. The locking baffle is used for limiting the movement of the UAV arm. The locking connector connects the locking baffle and the button connector, and also connects to the locking support to form a rotating joint. The button connector passes through the button support and connects to the two locking connectors. The button support is coaxially assembled with the locking button, the fuselage connector, and the locking column, and is connected to the fuselage connector by bolts. The fuselage connector has a threaded hole in the middle, which is threadedly connected to the locking column. This invention achieves two working modes of the self-locking mechanism by adjusting the position of the locking button: when the locking button is in the relaxed state, the arm can be folded to achieve the self-locking function; when the locking button is in the locked state, the arm can automatically unfold under the action of a spring.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a pneumatically launched foldable UAV self-locking device and method. Background Technology

[0002] With the development of modern technology, cannon-launched foldable drones are playing an increasingly important role on the battlefield. Improving the transport efficiency of drones is of great operational significance for expanding the application advantages of cannon-launched foldable drones. For cannon-launched foldable drones, it is required that during peacetime transport, the arms be in a folded, limited state to save transport space and facilitate carrying. During combat, after takeoff from the launch device, the folded arms should automatically unfold and return to flight mode.

[0003] Existing drone folding devices either have complex structures that are not conducive to practical use, or they do not require a power unit for propulsion, making it difficult to meet the practical needs of lightweight and combat application. Summary of the Invention

[0004] The purpose of this section is to outline some aspects of embodiments of the present invention and to briefly describe some preferred embodiments. Simplifications or omissions may be made in this section, as well as in the abstract and title of this application, to avoid obscuring the purpose of these documents; however, such simplifications or omissions should not be construed as limiting the scope of the invention.

[0005] In view of the above and / or existing problems, the present invention proposes a pneumatic catapult foldable drone self-locking device and method. The device is a purely mechanical mechanism with a simple structure and low cost. When the self-locking mechanism is in working mode, the drone arm can be self-locked simply by manually folding it, making the operation convenient.

[0006] The present invention adopts the following technical solution:

[0007] On one hand, the present invention provides a self-locking device for a pneumatically launched foldable unmanned aerial vehicle, characterized in that the device includes a locking baffle, a locking connector, a locking support, a button connector, a button support, and a locking button;

[0008] The locking baffle is used to limit the movement of the drone arm and is connected to one end of the locking connector.

[0009] The locking connector is connected to the locking baffle at one end and slidably connected to the button connector at the other end; the locking connector can rotate around the locking support, thereby driving the locking baffle to move up and down;

[0010] The locking bracket is fixed to the lower part of the drone fuselage and forms a rotating pair with the locking connector.

[0011] The button support is fixed to the lower part of the drone fuselage and is used to support the button connector and the locking button.

[0012] The button connector has a symmetrical structure and is installed on the locking button, moving up and down with the locking button; both ends of the button connector are slidably connected to the locking connector.

[0013] The locking button is mounted on the button support and is used to control the up and down movement of the button connector, thereby driving the locking connector to rotate around the axis and the locking baffle to move up and down.

[0014] In addition to any of the possible implementations described above, another implementation is provided in which the bottom end of the locking baffle is rectangular and has two through holes, and is fixedly connected to the locking connector by bolts;

[0015] The top of the locking baffle is clamp-shaped and conforms to the shape of the drone arm, used to clamp and release the drone arm.

[0016] In addition to any of the possible implementations described above, another implementation is provided in which one end of the locking connector is a boss with two threaded holes, which is fixedly connected to the locking baffle by bolts;

[0017] The other end of the locking connector has a through hole, and it is slidably connected to the button connector by a bolt.

[0018] The locking connector has a through hole in the middle, which is connected to the locking support and forms a rotating pair. The locking connector rotates about the axis where the through hole is located.

[0019] In addition to any of the possible implementations described above, a further implementation is provided in which slots for structural weight reduction are provided on both sides of the through hole in the middle of the locking connector.

[0020] In addition to any of the possible implementations described above, another implementation is provided in which the locking support is a T-shaped structure with two threaded holes at the top for connection with the UAV fuselage; the locking support has an opening groove and a through hole in the middle for connection with the locking connector and to form a rotating pair.

[0021] In addition to any of the possible implementations described above, another implementation is provided in which the button connector has an overall concave structure, with the middle part being an annular shape for coaxial cooperation with the locking button; the left and right ends of the button connector are rectangular structures with slots, which are combined with the locking connector to form a crank-slider mechanism by means of hinged hole bolts.

[0022] In addition to any of the possible implementations described above, another implementation is provided in which two rectangular connecting plates are provided at the upper end of the locking support, each rectangular connecting plate having two through holes for connecting with the body connecting parts;

[0023] The lower end of the button support is a cylindrical structure with a hollow structure in the middle for mounting the locking button; the bottom end of the button support has a limit hole for limiting the vertical movement of the locking button.

[0024] In addition to any of the possible implementations described above, another implementation is provided in which the locking button includes a button body, a locking post, and a spring;

[0025] The button body is cylindrical in shape, with a rectangular boss at the bottom for manual rotation and a cylindrical boss at the top for mounting a spring. The cylindrical boss has a through hole for coaxial engagement with the locking column. The bottom of the through hole in the cylindrical boss has a threaded hole. When the button body and the locking column are engaged to a certain depth, rotating the locking button will fix the button body and the locking column together by the threaded connection.

[0026] The middle part of the body connector is a raised rectangular structure, which serves as the top limit of the spring. The raised middle part has a threaded hole for installing the locking column. The locking column body is threaded and is fixedly connected to the body connector by the thread. The spring is sleeved on the locking column.

[0027] The button connector is mounted on the cylindrical boss of the button body and is coaxially mounted with the locking button.

[0028] On the other hand, the present invention also provides a self-locking method for a pneumatically launched foldable unmanned aerial vehicle, the method using the above-mentioned device, the method comprising:

[0029] S1. The device is installed on the lower part of the drone fuselage via a locking bracket and a button bracket;

[0030] S2. Release the locking button. The locking baffle is in the initial state. The top of the locking baffle is slightly higher than the lower arm of the drone. Manually fold the drone arm. When the arm contacts the outside of the locking baffle, it generates a downward force on the locking baffle. The locking baffle moves downward, causing the locking connector to rotate around the locking support. The end of the locking connector connected to the button connector rotates upward, causing the button connector to move upward. At this time, the spring is in a compressed state.

[0031] S3. Continue folding the drone arm until it passes the locking baffle and reaches the preset locking position; the button connector moves downward under the spring's rebound force, causing the locking connector to rotate in the opposite direction around the locking support, so that the end of the locking connector connected to the locking baffle rotates upward, causing the locking baffle to move upward and return to its initial state. At this time, the drone arm is restricted to the preset locking position by the locking baffle and cannot be unfolded.

[0032] In addition to any of the possible implementations described above, another implementation is provided whereby the following method is used when the drone arm needs to be unlocked:

[0033] To deploy the drone's arms, simply press the locking button. Pressing the button moves it upwards, causing the button connector to move upwards as well. At this point, the locking connecting plate 2 rotates around the locking support, causing the locking baffle to move downwards. When the locking baffle is lower than the arm, the constraint force on the arm disappears, and the arm automatically deploys under the action of the arm torsion spring. The components of the self-locking mechanism then return to their initial state under the action of the spring.

[0034] When the self-locking mechanism is not required to function, it can be disabled using the following methods:

[0035] Rotate the locking button upwards so that the locking button and the locking column are connected together by threads. The spring is compressed, the button connector moves upwards, and drives the locking connector to rotate around the locking support. This causes the end of the locking connector connected to the locking baffle to rotate downwards, which in turn drives the locking baffle to move downwards. The top of the locking baffle is lower than the lower arm of the drone. At this point, the locking baffle no longer limits the drone arm, and the drone arm is in a free state.

[0036] The beneficial effects of this invention are as follows: This invention is a purely mechanical mechanism with a simple structure and low cost. When the self-locking mechanism is in working mode, the drone arm can be self-locked simply by manually folding the arm, making operation convenient. When the drone is launched from the cannon, the drone arm does not need to be self-locked. It is only necessary to rotate the locking button to fix it together with the locking column. At this time, the drone arm can be freely folded and unfolded. Attached Figure Description

[0037] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. Wherein:

[0038] Figure 1 This is a schematic diagram of the structure of a pneumatically launched foldable drone self-locking device according to an embodiment of the present invention.

[0039] Figure 2 This is a schematic diagram of the internal structure of the locking button in an embodiment of the present invention.

[0040] Figure 3 The diagram shown is a structural state diagram of the drone arm when it is folded in the embodiment.

[0041] Figure 4 The diagram shown is a structural state diagram (unlocked state) when the locking button is fixed to the locking column in the embodiment.

[0042] Figure 5 The diagram shown illustrates the structural state of the self-locking mechanism locking the drone arm in the embodiment.

[0043] In the diagram: 1-locking baffle, 2-locking connector, 3-hinge hole bolt one, 4-locking support, 5-button connector, 6-button support, 7-body connector, 8-locking column, 9-hinge hole bolt two, 10-locking button, 11-spring. Detailed Implementation

[0044] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0045] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and those skilled in the art can make similar extensions without departing from the spirit of the invention. Therefore, the invention is not limited to the specific embodiments disclosed below.

[0046] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in different places in this specification does not necessarily refer to the same embodiment, nor is it a single or selective embodiment that is mutually exclusive with other embodiments.

[0047] like Figure 1 As shown, an embodiment of the present invention provides a self-locking device for a pneumatically launched foldable drone, comprising a locking baffle 1, a locking connector 2, a locking support 4, a button connector 5, a button support 6, and a locking button 10.

[0048] The locking baffle 1 is used to limit the arm of the drone and is connected to one end of the locking connector 2.

[0049] The locking connector 2 is connected to the locking baffle 1 at one end and slidably connected to the button connector 5 at the other end; the locking connector 2 can rotate around the locking support 4, thereby driving the locking baffle 1 to move up and down;

[0050] The locking support 4 is fixed to the lower part of the drone fuselage and forms a rotating pair with the locking connector 2.

[0051] The button support 6 is fixed to the lower part of the drone fuselage and is used to support the button connector 5 and the locking button 10.

[0052] The button connector 5 has a symmetrical structure and is installed on the locking button 10, moving up and down with the locking button 10; both ends of the button connector 5 are slidably connected to the locking connector 2 respectively;

[0053] The locking button 10 is mounted on the button support 6 and is used to control the up and down movement of the button connector 5, thereby driving the locking connector 2 to rotate around the axis and the locking baffle 1 to move up and down.

[0054] like Figure 1 , 2 As shown, in one specific embodiment, the bottom end of the locking baffle 1 is rectangular with two through holes, which can be bolted together with the locking connector 2; the top end is shaped like a fixed vise with triangular jaws, the inner side perpendicular to the drone arm for easy clamping of the arm, and the outer side forming a 65° angle with the inner side. When the drone arm is folded, a downward force is generated, causing the locking baffle 1 to move downward, thereby bringing the arm to a predetermined position.

[0055] In one specific embodiment, the initial height of the top of the locking baffle 1 is 2.5mm higher than that of the drone arm, and the drone arm can be effectively clamped by relying on the height difference.

[0056] In one specific embodiment, the locking connector 2 body includes three bosses. The end face of one boss is parallel to the front end of the machine body and serves as the base of the locking baffle 1. It has two threaded holes and is fixed to the locking baffle 1 by bolts. The end face of the middle boss is parallel to the side of the machine body and has a through hole in the center of the boss. It is coaxially engaged with the through hole on the locking support 4 and forms a rotating pair with the locking support 4 by the hinge bolt 3. The end face of the other boss is parallel to the side of the machine body and has a through hole in the center of the boss. It forms a crank-slider mechanism with the button connector by the hinge bolt 9.

[0057] The locking connector 2 has its protrusions fixed together by a cuboid connector. The connector has a slot for reducing structural weight.

[0058] The locking connector 2 can rotate around the locking support 4. In the initial state, the locking connector 2 is parallel to the machine body. When the locking baffle 1 is subjected to the downward force of the machine arm, it moves downward, which at the same time drives the locking connector 2 to rotate around the locking support 4. At this time, the button connector 5 will move upward due to the rotation of the locking connector 2, and the two will slide relative to each other.

[0059] In one specific embodiment, the locking support 4 is generally T-shaped, with two threaded holes at the top for connection to the drone fuselage. The locking support 4 has a raised central section with an opening groove and a through hole for connection to the locking connector 2. The width of the locking connector 2 is slightly smaller than the width of the opening groove, with a clearance fit between them.

[0060] In one specific embodiment, the button assembly includes a button connector 5, a button support 6, a body connector 7, a locking column 8, a hinged hole bolt 9, a locking button 10, and a spring 11.

[0061] The button connector 5 has a symmetrical structure, an overall concave structure, and a circular structure in the middle, which is coaxial with the button support 6, the locking column 8 and the spring 11.

[0062] The button connector 5 has rectangular structures with slots at both ends. The width of the slots is slightly wider than the width of the boss of the locking connector 2. It is combined with the locking connector 2 through the reamed bolt 9 to form a crank-slider mechanism. When the locking connector 2 rotates, it will drive the reamed bolt 9 to move relative to the button connector 5 inside the slot.

[0063] The button support 6 has two rectangular connecting plates at its upper end, each containing two through holes for mating with the body connector 7.

[0064] The lower end of the button support 6 is a cylindrical structure with a hollow structure in the middle for mounting the locking button 10. Its diameter is slightly larger than that of the locking button 10. A limit hole is opened at the lower end to restrict the movement of the locking button 10 in the axial direction.

[0065] The cylindrical button support 6 has a through slot, the width of which is slightly wider than that of the button connector 5. In the initial state, the button connector 5 is located at the bottom of the slot in the button support 6. When the locking connector 2 rotates, it will cause the button connector 5 to move upward inside the slot in the button support 6.

[0066] The fuselage connector 7 has a convex structure with rectangular connecting plates on both sides. Each connecting plate has two through holes and is connected by bolts to the button support 6 and the drone fuselage.

[0067] The middle part of the body connector 7 is a raised rectangular structure, which serves as the top limit of the spring 11. A threaded hole is opened in the middle for installing the locking column 8.

[0068] The locking column 8 has threads on its body and is fixed to the machine body connector 7 by bolts. A spring 11 is installed on the outer periphery of the locking column, and the two are coaxially engaged.

[0069] The button body is cylindrical, with an outer diameter slightly smaller than the inner diameter of the button support 6, for a coaxial clearance fit with the button support 6. The locking button 10 has a rectangular boss at its bottom for easy manual rotation. The locking button 10 also has a cylindrical boss on its top for mounting a spring 11. The cylindrical boss of the locking button 10 has a through hole for a coaxial fit with the locking column 8. The bottom of the through hole has a threaded hole; when the locking button 10 and the locking column 9 are fitted to a certain depth, rotating the button 10 will connect and secure them together via a threaded connection.

[0070] The top of the spring 11 contacts the body connector 7, and the bottom contacts the button connector 5. In the initial state, the spring is in a compressed state, which exerts downward pressure on the button connector 5 to ensure that the button connector 5 and the locking button 10 remain stable.

[0071] This invention provides a self-locking method for a pneumatically launched foldable unmanned aerial vehicle (UAV). The method utilizes the aforementioned device, and when a self-locking function is required, the method includes:

[0072] S1. The device is installed on the lower part of the drone fuselage via a locking bracket 4 and a button bracket 6;

[0073] S2. Release the locking button 10, and the locking baffle 1 is in the initial state. In the initial state, the locking button 10 is located at the bottom of the button support 6 under the action of the spring 11, and the locking connector 2 is parallel to the plane where the arm is located. The top of the locking baffle 1 is slightly higher than the lower arm of the drone. Manually fold the drone arm. When the arm contacts the outside of the locking baffle 1, it generates a downward component force on the locking baffle 1. The locking baffle 1 moves downward, causing the locking connector 2 to rotate around the locking support 4. The end of the locking connector 2 connected to the button connector 5 rotates upward, causing the button connector 5 to move upward. At this time, the spring 11 is in a compressed state.

[0074] S3. Continue folding the drone arm until it passes the locking baffle 1 and reaches the preset locking position. The button connector 5 moves downward under the rebound force of the spring 11, causing the locking connector 2 to rotate in the opposite direction around the locking support 4. This causes the end of the locking connector 2 connected to the locking baffle 1 to rotate upward, causing the locking baffle 1 to move upward. The locking baffle 1 returns to its initial state. At this time, the drone arm is restricted to the preset locking position by the locking baffle 1 and cannot be unfolded, thus locking the arm.

[0075] Once the drone's arms are locked, the entire drone takes on a cylindrical shape, making it easy to carry.

[0076] When the drone's arms need to deploy, simply press the locking button 10. Pressing the button 10 moves it upwards, causing the button connector 5 to move upwards as well. At this time, the locking connector 2 rotates around the locking support 4, causing the locking baffle 1 to move downwards. When the locking baffle 1 is lower than the arm, the constraint force on the arm disappears, and the arm automatically deploys under the action of the arm torsion spring, allowing the drone to return to its flight attitude. After releasing the button, all components of the self-locking mechanism return to their initial state under the action of the spring 11.

[0077] As an example of the failure of the self-locking mechanism when the UAV is launched from the tube in this invention:

[0078] When launching a drone from a cannon, it is necessary to ensure that the arms are folded before launch and automatically unfold after the drone is launched. However, the original self-locking mechanism locks the arms after they are folded, which cannot meet the flight requirements of unfolding the arms during cannon launch. Therefore, it is necessary to ensure that the self-locking mechanism is in a disabled state when the drone is launched from the cannon.

[0079] Press the locking button 10 to move it upwards. When its internal threaded hole contacts the locking post 8, rotate the locking button 10 by hand to secure the two together with bolts.

[0080] When the locking button 10 is fixed to the locking column 8, the spring 11 is compressed, and the height of the locking baffle 1 is lower than the arm, so it cannot play a limiting role, meaning the entire self-locking mechanism is ineffective. At this time, simply fold the arm manually and place it into the cannon firing device. Once the drone is launched into the air, the arm will automatically deploy to complete the predetermined flight mission.

[0081] This invention allows for two working modes of the self-locking mechanism by adjusting the position of the locking button: when the locking button is in the relaxed state, the self-locking mechanism is in working state, and the self-locking function of the machine arm can be achieved by folding the machine arm; when the locking button is in the locked state, the self-locking mechanism is in a disabled state, and if there is no external force restraining the folded machine arm, the machine arm can automatically unfold under the action of the spring.

[0082] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A self-locking device for a pneumatic launchable foldable drone, characterized in that, The device comprises a locking baffle, a locking connector, a locking support, a button connector, a button support and a locking button; The locking baffle is connected with one end of the locking connector and is used for limiting the unmanned aerial vehicle arm; One end of the locking connector is connected with the locking baffle, and the other end is slidingly connected with the button connector; the locking connector can rotate around the locking support, thereby driving the locking baffle to move up and down; The locking support is fixed on the lower part of the unmanned aerial vehicle body and forms a rotating pair with the locking connector; The button support is fixed on the lower part of the unmanned aerial vehicle body and is used for bearing the button connector and the locking button; The button connector is a left-right symmetrical structure, is installed on the locking button and moves up and down with the locking button; the two ends of the button connector are respectively slidingly connected with the locking connector; The locking button is installed on the button support and is used for controlling the up-down movement of the button connector, thereby driving the locking connector to rotate around the locking support and the locking baffle to move up and down.

2. The pneumatic catapult foldable drone self-locking device of claim 1, wherein, The bottom end of the locking baffle is rectangular and has two through holes, which are fixedly connected with the locking connector through bolts; The top end of the locking baffle is pincer-shaped and is adapted to the shape of the unmanned aerial vehicle arm, and is used for clamping and releasing the unmanned aerial vehicle arm.

3. The pneumatic catapult foldable drone self-locking device of claim 2, wherein, One end of the locking connector is a boss with two threaded holes, which is fixedly connected with the locking baffle through bolts; The other end of the locking connector has a through hole, which is slidingly connected with the button connector through bolts; The middle part of the locking connector has a through hole, which is connected with the locking support and forms a rotating pair; the locking connector rotates around the axis of the middle through hole.

4. The pneumatic catapult foldable drone self-locking device of claim 3, wherein, The two sides of the middle through hole of the locking connector are provided with slots for structure weight reduction.

5. The pneumatic catapult foldable drone self-locking device of claim 1, wherein, The locking support is a T-shaped structure as a whole, the top thereof is provided with two threaded holes for connecting with the unmanned aerial vehicle body; the middle part of the locking support is provided with an open slot and a through hole for connecting with the locking connector and forming a rotating pair.

6. The pneumatic catapult foldable drone self-locking device of claim 1, wherein, The button connector is a concave structure as a whole, the middle part thereof is a circular ring for coaxial cooperation with the locking button; the left and right ends of the button connector are rectangular structures provided with slots, which are combined with the locking connector into a crank slider mechanism through hinge hole bolts.

7. The pneumatic catapult foldable drone self-locking device of claim 1, wherein, The upper end of the locking support is provided with two rectangular connecting plates, each of which has two through holes for cooperating with the body connector; The lower end of the button support is a cylindrical structure, the middle part of the cylindrical structure is a hollow structure for installing the locking button; the bottom end of the button support is provided with a limiting through hole for limiting the up-down movement of the locking button.

8. The pneumatic catapult foldable drone self-locking device of claim 7, wherein, The locking button comprises a button main body, a locking column and a spring. The overall structure of the button body is cylindrical, the bottom is provided with a rectangular boss for manual rotation, the upper part is provided with a cylindrical boss for mounting a spring, the cylindrical boss is internally provided with a through hole for coaxial cooperation with the locking column, and the bottom of the through hole of the cylindrical boss is provided with a threaded hole, when the button body is cooperated with the locking column to a certain depth, the locking button is rotated to make the button body and the locking column fixed together through threaded connection; The middle part of the fuselage connecting piece is a convex rectangular structure, which is used as the top end limit of the spring, a threaded hole is opened in the middle convex part, which is used for mounting the locking column; the locking column is provided with a thread, which is fixedly connected on the fuselage connecting piece through the thread; the spring is sleeved on the locking column; The button connecting piece is installed on the cylindrical boss of the button body and coaxially installed with the locking button.

9. A method for self-locking of a pneumatically launched foldable drone, characterized in that, The method uses the device of any one of claims 1-8, the method comprises: S1, the device is installed at the lower part of the unmanned aerial vehicle fuselage through the locking support and the button support; S2, loosen the locking button, the locking baffle is in the initial state, the top position of the locking baffle is slightly higher than the lower machine arm of the unmanned aerial vehicle, manually fold the unmanned aerial vehicle arm, when the arm contacts the outside of the locking baffle, a downward component force is generated on the locking baffle, the locking baffle moves downward, drives the locking connecting piece to rotate around the locking support, the end connected with the button connecting piece of the locking connecting piece rotates upward, so that the button connecting piece moves upward, at this time the spring is in a compressed state; S3, continue to fold the unmanned aerial vehicle arm to the preset locking position beyond the locking baffle; the button connecting piece moves downward under the action of the spring rebound force, drives the locking connecting piece to rotate reversely around the locking support, so that the end connected with the locking baffle of the locking connecting piece rotates upward, drives the locking baffle to move upward, the locking baffle returns to the initial state, at this time the unmanned aerial vehicle arm is limited in the preset locking position by the locking baffle and cannot be unfolded.

10. The method of claim 9, wherein the air- launched foldable drone self-locking method is characterized by, When the unmanned aerial vehicle arm needs to be unlocked, the following method is adopted: If the unmanned aerial vehicle arm needs to be unfolded, you only need to press the locking button with your hand; after pressing the locking button, the locking button moves upward, drives the button connecting piece to move upward, at this time the locking connecting piece rotates around the locking support, drives the locking baffle to move downward; when the position of the locking baffle is lower than the unmanned aerial vehicle arm, the constraint force on the arm disappears, the arm automatically unfolds under the action of the arm torsional spring, the components of the device can return to the initial state under the action of the spring; When the self-locking mechanism does not need to work, the self-locking mechanism is disabled by the following method: Rotate the locking button upward, so that the locking button and the locking column are connected together through the thread, the spring is compressed, the button connecting piece moves upward, drives the locking connecting piece to rotate around the locking support, so that the end connected with the locking baffle of the locking connecting piece rotates downward, drives the locking baffle to move downward, the top position of the locking baffle is lower than the lower machine arm of the unmanned aerial vehicle, at this time the locking baffle no longer limits the unmanned aerial vehicle arm, the unmanned aerial vehicle arm is in a free state.

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