Multi-surface tail locking release mechanism, control method and barrel folding wing unmanned aerial vehicle

Abstract

The application provides a multi-surface tail wing locking release mechanism, a control method and a barrel folding wing unmanned aerial vehicle. The mechanism comprises a base, a gas generator, a locking release assembly and a limiting assembly. The gas generator is installed to the base. In the locking release assembly, one end of a driving shaft is contained in the base and provided with a cavity, the gas can pass into the cavity to push the driving shaft to move away from the surface, a bracket moves with the driving shaft, a pin is installed on the bracket through the base and can be inserted into the surface, and the length of the pin depends on the length of each surface and the release timing. In the limiting assembly, a support is fixed to the base through a support rod, and a stopper limits the movement of the driving shaft when it moves to contact the support. According to the application, the tail wing surface is unfolded regardless of the smoothness of the barrel wall, and the tail wing can be unfolded in delay; the locking and release of multiple surfaces are controlled by the same mechanism, and the release reliability is high; different lengths of pins can be selected for the synchronous or asynchronous release of multiple surfaces according to the length of the tail wing surface and the release timing requirements.

Description

Technical Field

[0001] This invention belongs to the field of structural design technology for tube-launched folding-wing unmanned aerial vehicles (UAVs), specifically relating to a multi-control surface tail fin locking and release mechanism, a multi-control surface tail fin release control method using the mechanism, and a tube-launched folding-wing UAV including the mechanism. Background Technology

[0002] Cannon-launched folding-wing UAVs, or simply cannon-launched folding-wing UAVs, have attracted attention due to their advantages over fixed-wing UAVs, such as smaller size, easier portability, and greater tactical flexibility. To ensure the necessary stability and maneuverability, many cannon-launched folding-wing UAVs are equipped with tail fin structures, among which multi-control surface tail fin layouts are widely used to improve the control performance of cannon-launched folding-wing UAVs and reduce the lateral dimensions of the tail fins.

[0003] For ease of control, most folding-wing UAVs currently use an automatic release mechanism for their wings and tail fins by releasing the constraints of the launch tube wall when the UAV leaves the launch tube. In other words, when the folding-wing UAV is in a folded state inside the launch tube, the multiple control surfaces of its multi-control tail fin are in a retracted position due to the constraints of the launch tube wall. After the UAV leaves the launch tube, the constraints of the multi-control surfaces of the tail fin are released and it unfolds freely.

[0004] This release method has the following problems:

[0005] 1. Since the wings of the tube-launched folding-wing UAV also unfold from the folded state, and the wings are often long in order to have better aerodynamic performance, they will cover the tail area when folded. Therefore, the free release method may cause interference between the wings and tail when unfolding, which may lead to the failure of UAV launch.

[0006] 2. Due to the different control strategies required during the transition phase after launch, the tail fins need to be able to deploy with a delay, but the current free-release method cannot meet this requirement;

[0007] 3. In the current method of tube wall constraint, the tail fin and the tube wall are in sliding contact during the launch process. In order to ensure reliable launch and avoid interference of the tail fin by the tube wall during launch, the smoothness of the launch tube wall is required to be high. The tube wall should not have too many protruding obstacles in its structural design. Moreover, after launch, large gunpowder residue particles will also affect the release of the tail fin, thereby affecting the service life of the launch tube.

[0008] In addition to the aforementioned tube wall constraint + free release method, current multi-control surface tail fins also employ locking pin constraint + rope release and locking pin constraint + actuator release methods. However, these methods all involve setting up a separate constraint and release structure for each tail fin control surface, resulting in complex structures. Moreover, due to the low release control precision of the rope and actuator, for multi-control surface tail fin types such as X-tails, when using the above-mentioned independent constraint and release methods for each control surface, there are problems such as low overall reliability, poor controllability of control surface release, and impact on the flight control effect during the launch phase variant process.

[0009] Furthermore, under certain performance requirements, aircraft designs may encounter situations where the control surfaces in a multi-control tail fin have different lengths. For example, the lower V-tail of an X-tail fin may be longer than the upper V-tail. Alternatively, the release and unlocking timings of the various control surfaces in a multi-control tail fin may need to be different. Currently, these requirements can only be achieved by setting separate constraint and release structures for each tail fin control surface.

[0010] Therefore, it is necessary to design a constraint and release structure for the multi-control surface tail of a tube-launched folding-wing UAV, which can realize the controllable locking and release of the multi-control surface tail according to control requirements, such as the synchronous or asynchronous controllable release of tail control surfaces of the same or different lengths. Summary of the Invention

[0011] The purpose of this invention is to solve the problems existing in the prior art for multi-control surface tail surfaces of tube-launched folding-wing UAVs. These problems include interference between the wing and control surfaces, inability to delay the deployment of control surfaces, and high requirements for the smoothness of the tube wall when using tube wall constraint + rope release or locking pin constraint + actuator release, resulting in low reliability and poor controllability of control surface release. Furthermore, the need for separate constraint and release structures is required when synchronous or asynchronous controllable release of multiple control surfaces of the tail wing is needed according to tail wing control requirements. This invention provides a multi-control surface tail wing locking and release mechanism, a multi-control surface tail wing release control method using this mechanism, and a tube-launched folding-wing UAV incorporating this mechanism. Using a single mechanism, multiple control surfaces of the UAV tail wing can be simultaneously locked. Multiple tail wing control surfaces can be released and delayed when needed through timing control, thus avoiding interference with the wing. The release of multiple tail wing control surfaces is controlled by a single mechanism, resulting in high reliability and strong controllability. Synchronous or asynchronous controllable release can be achieved for tail wing control surfaces of the same or different lengths.

[0012] To achieve the above objectives, the technical solution provided by this invention is:

[0013] A multi-control surface tail fin locking and releasing mechanism is used to lock and release multiple tail fin control surfaces of a tube-launched folding-wing UAV. Its special feature is that it includes a base, a gas generator, a locking and releasing assembly, and a limiting assembly.

[0014] The base is used to support the gas generator, locking and releasing components and limiting components, and is fixed to the tail section of the drone fuselage;

[0015] The gas generator is mounted to the base and contains at least two propellants to provide the force to release the tail fin control surfaces;

[0016] The locking and releasing assembly includes a drive shaft, a bracket, and multiple pins that correspond one-to-one with the various tail fin control surfaces.

[0017] The drive shaft is horizontally positioned, with its first end housed in a base and having a cavity. Gas from the gas generator can pass into the cavity and drive the drive shaft to move in a direction away from the tail fin control surface.

[0018] The bracket is fitted onto the drive shaft and can move together with the drive shaft.

[0019] The pins are horizontally mounted on the bracket through the base and can be inserted into the tail fin control surfaces to lock multiple tail fin control surfaces simultaneously. The length of the pin depends on the length of each control surface and the release sequence. The pins can be simultaneously driven by the bracket to move away from the tail fin control surfaces to achieve synchronous or asynchronous controllable release of the control surfaces.

[0020] The limiting assembly is used to limit the locking and releasing assembly. It includes a support member, a stop member, and two support rods. The support member is fixed to the base by the support rods. The second end of the drive shaft passes through the support member and is movable relative to the support member.

[0021] A stop is provided on the drive shaft to limit the movement of the drive shaft when it moves with the drive shaft to contact the support.

[0022] Furthermore, the stop is a sleeve portion that protrudes radially outward from the drive shaft, and the bracket is sleeved on the sleeve portion.

[0023] Furthermore, the base includes two cylindrical sections for receiving the support rod.

[0024] Furthermore, the support rod is hollow cylindrical in shape.

[0025] Furthermore, the base is a rectangular box shape with its back to the control surface open. The gas generator is vertically mounted on the upper wall of the base, and the base is connected to the UAV at its two side walls.

[0026] Furthermore, the base includes two protrusions that project vertically inward from its upper and lower walls, respectively, and the protrusions are used to receive pins.

[0027] Furthermore, weight-reducing holes are provided on the base.

[0028] A multi-control surface tail fin release control method, characterized in that it uses the aforementioned multi-control surface tail fin locking and release mechanism to control the release sequence of multiple tail fin control surfaces, including:

[0029] When multiple tail fin control surfaces are of equal length:

[0030] When the tail fin control surfaces need to be released synchronously, the lengths of multiple pins should be selected to be equal.

[0031] When the tail fin control surfaces need to be released asynchronously, the lengths of multiple pins are selected such that the length of the pin corresponding to the control surface that needs to be released first is shorter than the length of the pin corresponding to the control surface that needs to be released later.

[0032] When multiple tail fin control surfaces are of unequal length:

[0033] When the tail fin control surfaces need to be released synchronously, the lengths of multiple pins are selected such that the length of the pin corresponding to the shorter control surface is longer than the length of the pin corresponding to the longer control surface, so that the length of the part of the pin inserted into the control surface is equal.

[0034] When asynchronous release of the tail fin control surfaces is required, the lengths of the multiple pins are selected such that the length of the pin corresponding to the control surface to be released first is shorter than the length of the pin corresponding to the control surface to be released later.

[0035] A tube-launched folding-wing UAV is characterized by including a fuselage, wings, a multi-control tail fin, and a locking and releasing mechanism for the aforementioned multi-control tail fin connected to the tail section of the fuselage.

[0036] The advantages of this invention are:

[0037] 1. The multi-control surface tail fin locking and releasing mechanism and release control method of the present invention, wherein the mechanism includes a gas generator mounted on a base, and a bracket fitted on a horizontal drive shaft connected to pins corresponding to the tail fin control surfaces. The pins pass through the base to lock the tail fin control surfaces simultaneously. When the tail fin control surfaces need to be deployed, the gas generator is activated to push the drive shaft and the bracket. The bracket drives multiple pins to move away from the tail fin control surfaces simultaneously, thereby releasing the control surfaces. Therefore, in the present invention, the deployment of the tail fin control surfaces is independent of the surface finish of the cylinder wall, and the tail fin can be deployed with a delay, avoiding interference between the tail fin and the wing. The locking and releasing of multiple tail fin control surfaces are controlled by the same mechanism, resulting in high release reliability and strong controllability. In addition, different lengths of pins can be selected to achieve synchronous or asynchronous release of multiple tail fin control surfaces according to different lengths of tail fin control surfaces and control surface release sequence requirements, realizing tail fin control surface release sequence control. The pins, which originally only played a locking role, are given a control function. By designing the length of the pins, the controllable release sequence of the tail fin control surfaces can be precisely achieved.

[0038] 2. Compared to existing UAVs, the tube-launched folding-wing UAV of this invention features a multi-control surface tail fin locking and release mechanism. This allows for simultaneous locking and synchronous or asynchronous controllable release of multiple tail fin control surfaces, preventing interference between the control surfaces and the wings during deployment and improving the launch reliability of the UAV. The timing control of the tail fin control surface release makes the UAV adaptable to various tail fin deployment requirements and different launch conditions. Furthermore, the tube-launched folding-wing UAV of this invention does not require changes to the structure of existing UAVs during use; only openings in the tail fin control surfaces and the addition of the multi-control surface tail fin locking and release mechanism of this invention are needed. This is easy to implement, has low improvement costs, and is highly applicable. Attached Figure Description

[0039] The features and advantages of the invention will become more readily apparent from the following description with reference to the accompanying drawings, which are not drawn to scale and some features are enlarged or reduced to show details of specific parts.

[0040] Figure 1 This is a perspective view of the multi-control surface tail fin locking and releasing mechanism of the present invention in the state of releasing the tail fin;

[0041] Figure 2 This is a perspective view of the multi-control surface tail fin locking and release mechanism of the present invention in the state of locking the tail fin;

[0042] Figure 3 This is an assembled perspective view of the multi-control surface tail fin locking and release mechanism of the present invention;

[0043] Figure 4 This is a perspective view of the base in the multi-control surface tail fin locking and releasing mechanism of the present invention;

[0044] Figure 5 This is a perspective view of the drive shaft in the locking and releasing assembly of the present invention;

[0045] Figure 6 This is a perspective view of the assembly of the support member and the support rod in the limiting component of the present invention.

[0046] In the picture:

[0047] 1-Base, 11-Upper wall, 12-Side wall, 121-Screw hole, 13-Lower wall, 14-Protrusion, 15-Weight reduction hole, 16-Cylinder section;

[0048] 2-Gas generator;

[0049] 3-Locking and releasing assembly, 31-Drive shaft, 311-First end, 312-Second end, 313-Radial hole, 314-Cavity, 316-Shoulder, 32-Bracket, 33-Pin;

[0050] 4-Limiting component, 41-Support component, 411-Hole, 42-Stop component, 43-Support rod;

[0051] 101 - Tail section of fuselage, 102 - Tail control surface, 103 - Pin hole. Detailed Implementation

[0052] The present invention will now be described in detail with reference to the accompanying drawings and exemplary embodiments thereof. It should be noted that the following detailed description of the present invention is for illustrative purposes only and is not intended to limit the scope of the invention.

[0053] This invention provides a multi-control surface tail fin locking and releasing mechanism, a multi-control surface tail fin releasing control method using the mechanism, and a tube-launched folding-wing UAV including the mechanism. The mechanism is used to install on the tube-launched folding-wing UAV to lock and release multiple tail fin control surfaces of the tube-launched folding-wing UAV. The tail fin can be an X-shaped tail fin with four tail fin control surfaces, or a V-shaped tail fin with two tail fin control surfaces, etc.

[0054] The multi-control surface tail fin locking and release mechanism provided by the present invention will now be described using the X-shaped tail fin as an example.

[0055] Reference Figures 1 to 3 The multi-control surface tail fin locking and releasing mechanism, as an exemplary embodiment of the present invention, includes a base 1, a gas generator 2, a locking and releasing assembly 3, and a limiting assembly 4. The base 1 supports the gas generator 2, the locking and releasing assembly 3, and the limiting assembly 4. The gas generator 2 provides the force to release the multiple tail fin control surfaces 102. The locking and releasing assembly 3 interacts with the tail fin control surfaces 102 to lock and release them. The limiting assembly 4 limits the locking and releasing assembly 3 when it releases the tail fin control surfaces 102. When the locking and releasing assembly 3 cooperates with the tail fin control surfaces 102 to lock the multiple tail fin control surfaces 102, the tail section 101 of the UAV is... Figure 2 As shown, when the gas generator 2 is activated, the locking and releasing assembly 3 actuates, releasing multiple tail fin control surfaces 102 according to a timing requirement. Under the action of their control mechanisms (not shown in the figure), the tail fin control surfaces 102 extend outwards, pass through the long slots on the fuselage tail section 101, and then reach the extended position, with the fuselage tail section 101 in a position... Figure 1 The state shown.

[0056] The base 1 is fixed to the tail section 101 of the fuselage and can be connected to the tail section 101 above the tail section shaft of the UAV. In particular, it can be connected to both sides of the tail section 101 in the width direction by screw connection. The gas generator 2 is installed on the base 1. At least two propellants can be arranged in the gas generator 2, which has extremely high ignition reliability.

[0057] Combination Figure 3 and Figure 4 In an exemplary embodiment of the present invention, the base 1 is a rectangular box shape open away from the control surface 102 in the forward and backward direction of the UAV. The bottom of the box is vertically arranged and includes an upper wall 11, two side walls 12, and a lower wall 13. The gas generator 2 is vertically mounted on the upper wall 11 of the base 1. The base 1 is connected to the UAV at its two side walls 12. Screws can be screwed to the tail section 101 of the fuselage through two screw holes 121 on each side wall 12. The lower wall 13 may have holes to avoid the tail section shaft. It should be noted that the terms "upper," "lower," and "vertical" and their related expressions mentioned herein refer to the height direction of the UAV, while "horizontal" and its related expressions refer to the forward and backward direction of the UAV.

[0058] The base 1 may include two protrusions 14 projecting vertically inward from its upper wall 11 and lower wall 13, respectively. The protrusions 14 are connected to the bottom of the base 1 and are used to house pins 33, which will be described below. Furthermore, the base 1 may include two cylindrical portions 16 for receiving a support rod 43, which will be described below. These cylindrical portions 16 may also be integral with the bottom of the base 1 and are located vertically between the protrusions 14. The protrusions 14 and cylindrical portions 16 provided on the base 1 are particularly symmetrical about the central axis in the width direction of the UAV to improve the flight performance of the UAV.

[0059] Preferably, the base 1 is provided with weight reduction holes 15 to reduce the weight of the UAV and improve flight performance. The number of weight reduction holes 15 is not limited, and two are shown in the figure. The weight reduction holes 15 are preferably symmetrical about the central axis of the UAV in the width direction.

[0060] like Figure 3 As shown, the locking and releasing assembly 3 includes a drive shaft 31, a bracket 32, and multiple pins 33 (only one is shown in the figure) that correspond one-to-one with multiple tail fin control surfaces 102.

[0061] Combination Figure 3 and Figure 5The drive shaft 31 is horizontally positioned on the side of the base 1 opposite to the side where the tail fin is located, and can be arranged perpendicular to the vertical bottom of the base 1. It has a first end 311 and a second end 312. The diameter of the first end 311 is larger than the diameter of the second end 312. The second end 312 can be solid as shown in the figure, or it can be hollow. The first end 311 is housed in the base 1 and has a cavity 314. That is, the end face of the first end 311 closer to the second end 312 is closed. The gas from the gas generator 2 can pass into the cavity 314, specifically through the radial hole 313 on the first end 311. The gas can drive the drive shaft 31 to move in a direction away from the tail fin control surface 102. It should be understood that when the drive shaft 31 is installed in place, the cavity 314 is closed by the base 1; that is, the outer end face of the first end 311 is in contact with the base 1 to prevent gas leakage from that end face. In addition, the outer end face of the first end 311 may be chamfered to facilitate its assembly with the base 1.

[0062] Continue to refer to Figure 3 The bracket 32 ​​is fitted onto the drive shaft 31 and can move together with it. The shape of the bracket 32 ​​can be designed according to the tail fin type. For example, for the X-tail fin shown in the figure, the bracket 41 can be roughly X-shaped, with its four tips corresponding to the four control surfaces of the X-tail fin. In a specific embodiment, the bracket 32 ​​can be fitted onto the shoulder 316 of the drive shaft 31 to reduce the machined surface area of ​​the drive shaft 31. When the mechanism of the present invention is installed on the UAV, the bracket 32 ​​is in contact with the base 1.

[0063] Pins 33 pass horizontally through the base 1, particularly through the protrusion 14 on the base 1, and are mounted on the bracket 32. They can be inserted into the pin holes 103 of the tail fin control surfaces 102 to simultaneously lock multiple tail fin control surfaces 102. The length of the pins 33 depends on the length of each control surface and the release sequence. The pins 33 can be simultaneously driven by the bracket 32 ​​to move in a direction away from the tail fin control surfaces 102, so as to achieve synchronous or asynchronous controllable release of the control surfaces 102. The control mechanism for deploying the control surfaces 102 after release can be implemented using mature technology and will not be described in this invention.

[0064] Combined with reference Figure 3 and Figure 6 The limiting component 4 and the drive shaft 31 are located on the same side of the base 1, and include a support 41, a stop 42 and two support rods 43.

[0065] The support member 41 is fixed to the base 1 by a support rod 43. The second end 312 of the drive shaft 31 passes through the hole 411 on the support member 41 and is movable relative to the support member 41. The support member 33 may be generally plate-shaped and arranged parallel to the bottom of the base box.

[0066] In an exemplary embodiment of the present invention, both support rods 43 are parallel to and symmetrically arranged about the drive shaft 31. One end of the support rod 43 is connected to the support member 41, and the other end is fixed to the base 1. In particular, it can be threaded to the cylindrical portion 16 of the base 1, but the connection method is not limited. In addition, the support rod 43 can be hollow cylindrical in shape to reduce the weight of the mechanism and the drone.

[0067] A stop 42 is disposed on the drive shaft 31 to limit the movement of the drive shaft 31 when it moves to contact the support member 41. The stop 42 can be a separate component, but more particularly, it can be an integral part of the drive shaft 31. Specifically, as... Figure 5 As shown, the stop 42 is a sleeve portion protruding radially outward from the drive shaft 31. The bracket 32 ​​can be fitted onto this sleeve portion. This embodiment differs from the embodiment mentioned above where the bracket 32 ​​is mounted on the shoulder 316 of the drive shaft 31. Furthermore, in another embodiment, the bracket 32 ​​can be fitted onto the shoulder 316, with the sleeve portion of the stop 42 engaging with the shoulder 316. This method allows only the shoulder 316 where the bracket 32 ​​is mounted to be machined. It should be understood that, regardless of the structure used, the position and / or length of the stop 42 should be designed to ensure that the bracket 32 ​​disengages the drive pin 33 from the tail fin control surface, enabling the release of the tail fin control surface.

[0068] The multi-control surface tail fin release control method using the above-mentioned multi-control surface tail fin locking and release mechanism provided by the present invention will be described next.

[0069] Reference Figures 1 to 3 As an exemplary embodiment of the present invention, the multi-control surface tail fin release control method uses the above-described mechanism to control the release timing of multiple tail fin control surfaces 102, including:

[0070] When multiple tail fin control surfaces 102 are of equal length:

[0071] When the tail fin control surface 102 needs to be released synchronously, the lengths of the multiple pins 33 are selected to be equal.

[0072] When the tail fin control surface 102 needs to be released asynchronously, the lengths of the multiple pins 33 are selected such that the length of the pin 33 corresponding to the control surface that needs to be released first is shorter than the length of the pin 33 corresponding to the control surface that needs to be released later.

[0073] The method of the present invention further includes:

[0074] When the lengths of multiple tail fin control surfaces 102 are not equal:

[0075] When the tail fin control surface 102 needs to be released synchronously, the lengths of the multiple pins 33 are selected such that the length of the pin 33 corresponding to the shorter control surface is longer than the length of the pin 33 corresponding to the longer control surface, so that the lengths of the pins 33 inserted into the control surface are equal.

[0076] When the tail fin control surface 102 needs to be released asynchronously, the lengths of the multiple pins 33 are selected such that the length of the pin 33 corresponding to the control surface that needs to be released first is shorter than the length of the pin 33 corresponding to the control surface that needs to be released later.

[0077] As described above, according to the multi-control surface tail fin locking and releasing mechanism and releasing control method of the present invention, the tail fin control surface deployment is independent of the tube wall smoothness, and the tail fin can be delayed in deployment, avoiding interference between the tail fin and the wing; the locking and releasing of multiple tail fin control surfaces are controlled by the same mechanism, resulting in high release reliability and strong controllability; in addition, different lengths of pins can be selected to release the multiple tail fin control surfaces synchronously or asynchronously according to the different lengths of tail fin control surfaces and the control surface release sequence requirements, realizing the release sequence control of the tail fin control surfaces, giving control function to the pins that originally only played a locking role, and by designing the length of the pins, the controllable release sequence of the tail fin control surfaces can be precisely achieved.

[0078] The following describes the tube-launched folding-wing UAV provided by the present invention.

[0079] As an exemplary embodiment of the present invention, the tube-launched folding-wing UAV includes a fuselage, wings, a multi-control tail fin, and a locking and releasing mechanism for the aforementioned multi-control tail fin connected to the tail section of the fuselage. The connection structure between the various parts of the UAV can be implemented using known technologies and the above description of the locking and releasing mechanism for the multi-control tail fin, and will not be repeated here.

[0080] Compared to existing UAVs, the tubular-launched folding-wing UAV of this invention features a multi-control tail fin locking and release mechanism. This allows for simultaneous locking and synchronous or asynchronous controllable release of multiple tail fin control surfaces, preventing interference between the control surfaces and the wings during deployment and improving launch reliability. The timing control of the tail fin control surface release makes the UAV adaptable to various tail fin deployment requirements and different launch conditions. Furthermore, the tubular-launched folding-wing UAV of this invention requires no changes to the existing UAV structure during use; only opening holes in the tail fin control surfaces, creating pin holes, and adding the multi-control tail fin locking and release mechanism of this invention are needed. This is easy to implement, has low modification costs, and is highly applicable.

[0081] The features mentioned and / or shown in the foregoing description of exemplary embodiments of the present invention may be combined in the same or similar manner with one or more other embodiments, combined with features in other embodiments, or substituted for corresponding features in other embodiments. Such combinations or substitutions should also be considered as including within the scope of protection of the present invention.

Claims

1. A multi-surface tail lock release mechanism for locking and releasing a plurality of tail surfaces of a cylindrical launch folded wing UAV, characterized in that: Includes a base, a gas generator, a locking and releasing assembly, and a limit assembly; The base is used to support the gas generator, the locking and releasing assembly and the limiting assembly, and is fixedly connected to the tail section of the UAV fuselage; The gas generator is mounted to the base and contains at least two propellants for providing force to release the tail fin control surfaces; The locking and releasing assembly includes a drive shaft, a bracket, and multiple pins that correspond one-to-one with the multiple tail fin control surfaces. The drive shaft is horizontally positioned, with its first end housed in the base and having a cavity. The gas from the gas generator can flow into the cavity and propel the drive shaft in a direction away from the tail fin control surface. The bracket is sleeved on the drive shaft and can move together with the drive shaft. The pins are horizontally mounted on the bracket through the base and can be inserted into the tail fin control surfaces to lock multiple tail fin control surfaces simultaneously. The length of the pins depends on the length of each control surface and the release sequence. The pins can be simultaneously driven by the bracket to move away from the tail fin control surfaces to achieve synchronous or asynchronous controllable release of the control surfaces. The limiting component is used to limit the locking and releasing component, and includes a support member, a stop member, and two support rods. The support member is fixed to the base by the support rod, and the second end of the drive shaft passes through the support member and is movable relative to the support member. The stop member is disposed on the drive shaft and is used to restrict the movement of the drive shaft when it moves with the drive shaft to contact the support member.

2. The multi-surface tail lock release mechanism of claim 1, wherein: The stop is a sleeve portion that protrudes radially outward from the drive shaft, and the bracket is sleeved on the sleeve portion.

3. The multi-control surface tail fin locking and release mechanism according to claim 1 or 2, characterized in that: The base includes two cylindrical sections for receiving the support rod.

4. The multi-control surface tail fin locking and release mechanism according to claim 1 or 2, characterized in that: The support rod is in the shape of a hollow cylinder.

5. The multi-control surface tail fin locking and release mechanism according to claim 1 or 2, characterized in that: The base is a rectangular box shape with its back to the control surface open. The gas generator is vertically mounted on the upper wall of the base, and the base is connected to the UAV at its two side walls.

6. The multi-control surface tail fin locking and release mechanism according to claim 5, characterized in that: The base includes two protrusions that project vertically inward from its upper and lower walls, respectively, and the protrusions are used to receive the pin.

7. The multi-control surface tail fin locking and release mechanism according to claim 1 or 2, characterized in that: The base has weight-reducing holes.

8. A multi-control surface tail fin release control method, characterized in that, It uses the multi-control surface tail fin locking and release mechanism according to any one of claims 1 to 7 to control the release timing of multiple tail fin control surfaces, including: When multiple tail fin control surfaces are of equal length: When the tail fin control surfaces need to be released synchronously, the lengths of multiple pins should be selected to be equal. When the tail fin control surfaces need to be released asynchronously, the lengths of multiple pins are selected such that the length of the pin corresponding to the control surface that needs to be released first is shorter than the length of the pin corresponding to the control surface that needs to be released later. When multiple tail fin control surfaces are of unequal length: When the tail fin control surfaces need to be released synchronously, the lengths of multiple pins are selected such that the length of the pin corresponding to the shorter control surface is longer than the length of the pin corresponding to the longer control surface, so that the length of the part of the pin inserted into the control surface is equal. When asynchronous release of the tail fin control surfaces is required, the lengths of the multiple pins are selected such that the length of the pin corresponding to the control surface to be released first is shorter than the length of the pin corresponding to the control surface to be released later.

9. A tube-launched folding-wing unmanned aerial vehicle, characterized in that: It includes a fuselage, wings, a multi-faceted tail fin, and a multi-faceted tail fin locking and releasing mechanism according to any one of claims 1 to 7 connected to the tail section of the fuselage.

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