A locking mechanism for composite wing UAV take-off and landing platform

Abstract

The present invention relates to the technical field of unmanned aerial vehicles, and specifically proposes a locking mechanism for a composite wing unmanned aerial vehicle take-off and landing platform, comprising a landing guide seat, an alignment guide part, a positioning support part, and two locking parts. The locking mechanism designed by the present invention for a composite wing unmanned aerial vehicle take-off and landing platform can adjust the landing position of the unmanned aerial vehicle when the unmanned aerial vehicle lands on the take-off and landing platform through the coordination of the alignment guide part, the positioning support part, the landing guide seat, and the locking part, so that the landing gear of the unmanned aerial vehicle can accurately land on the landing guide seat, and the landing guide seat cooperates with the landing gear to limit the landing gear in time to avoid falling before the landing gear is locked, and the locking part can also perform multi-point locking of the horizontal section and the vertical section of the landing gear, thereby increasing the locking support height of the landing gear, and greatly improving the locking effect and locking stability of the unmanned aerial vehicle.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicles, and specifically proposes a locking mechanism for a composite-wing unmanned aerial vehicle take-off and landing platform. Background Art

[0002] A compound wing UAV is an aircraft that combines the advantages of fixed-wing and rotary-wing UAVs. It has the characteristics of long flight time, high efficiency, and vertical take-off and landing capabilities. The use of UAVs at sea or on the seaside has a wide range of applications, such as ocean monitoring, maritime rescue, maritime patrol, etc., which not only improves work efficiency but also enhances safety.

[0003] There are two front and rear landing gears at the bottom of the fuselage of the composite wing UAV. When the composite wing UAV lands on the take-off and landing platform, its fuselage is supported by the landing gear. Currently, some take-off and landing platforms are equipped with locking mechanisms for locking the UAV landing gears, while some are not equipped with locking mechanisms.

[0004] The locking mechanism designed on the existing landing platform only locks the part of the landing gear close to the landing platform, which is prone to the following problems: 1. Due to the low locking position, strong winds often occur in open areas such as the seaside and the sea, and the wind speed may reach level 6 or even higher. When the landing gear at the lower end of the drone is locked on the landing platform through the locking mechanism, the landing gear is easily subjected to external impacts (such as wind, waves, etc.), which can easily generate a large bending moment and cause damage to the drone landing gear. In addition, the low locking point may cause the center of gravity of the drone to be out of the optimal support range, thereby affecting the overall stability.

[0005] 2. In addition, the existing locking mechanism has no limit function after the landing gear of the UAV lands on the take-off and landing platform, resulting in the UAV not being able to be limited in time and being prone to falling and damage.

[0006] 3. The drone is prone to tilting due to the wind during the process of lifting and falling, making it difficult to lock accurately. In addition, the drone is prone to tilting during takeoff, causing the landing gear on it to collide with the locking mechanism and cause damage. Summary of the invention

[0007] In view of the above problems, an embodiment of the present application provides a locking mechanism for a composite-wing UAV take-off and landing platform to solve the technical problems in the related art.

[0008] In order to achieve the above-mentioned purpose, the embodiment of the present application provides the following technical solutions: a locking mechanism for a composite-wing UAV take-off and landing platform, which is used to lock the landing gear of the UAV after the composite-wing UAV lands on the take-off and landing platform. The take-off and landing platform is an existing equipment with a storage cavity for lifting and storing the UAV underneath. The locking mechanism includes a landing guide seat installed on the top of the take-off and landing platform, an alignment guide part, a positioning support part and two locking parts. The alignment guide part is used to pre-position the head of the UAV fuselage when it lands.

[0009] The alignment guide part comprises a limit guide frame installed on the top of the lifting and lowering platform through a vertical plate. The limit guide frame is in a U shape consisting of three guide plates with arc-shaped tops and an opening facing the landing guide seat.

[0010] In one possible implementation, the landing guide seat is a trapezoidal cavity structure with an inclined vertical section that cooperates with the landing gear, and the inclined side wall of the landing guide seat is parallel to the inclined section of the landing gear. The landing guide seat is used to pre-limit the landing gear, and guide components are rotatably installed on both inclined side walls of the landing guide seat. The guide components are used to roll in contact with and guide the side walls of the inclined section when the landing gear descends.

[0011] The positioning and supporting part is arranged on the landing guide seat, and is used for positioning and supporting the UAV fuselage and guiding it during the lifting process.

[0012] The two locking parts are both arranged on the landing guide seat and the take-off and landing platform and are arranged along the length direction of the landing guide seat. The locking part includes a limit stop bar fixedly installed on the two inclined surfaces of the landing guide seat and a slidably installed push frame. The landing gear falls between the limit stop bar and the push frame on the same side. The push frame is in an L-shape with an inclined vertical section. A matching pressure lock assembly is slidably arranged between the push frame and the corresponding limit stop bar. The pressure lock assembly is used to lock the landing gear on the landing guide seat.

[0013] The driving part is arranged on the landing guide seat and the take-off and landing platform, and is used to drive the four push frames to move toward the corresponding limit stop bars and push the landing gear until the pressure locking assembly locks the landing gear, and the driving part locks the positioning support part.

[0014] In a possible implementation, the guide assembly includes a plurality of guide rollers, which are evenly arranged along the inclined surface of the landing guide seat and are rotatably connected to the landing guide seat and the limit stop bar.

[0015] In one possible implementation, the locking assembly includes a plurality of guide grooves provided on the inclined section and the horizontal section of the push frame and close to one side of the limit stop bar, a connecting mounting groove is provided between the plurality of guide grooves, a plurality of guide grooves are provided on the limit stop bar, and a pressing member cooperating with the guide groove is installed between the mounting groove and the plurality of guide grooves via an elastic reset member. When the push frame moves toward the limit stop bar, the pressing member cooperates with the guide groove and moves toward the landing gear, pressing the landing gear against the landing guide seat and the take-off and landing platform.

[0016] In one possible implementation, the pressure member includes a pressure plate that is slidably connected to a plurality of guide grooves, and the pressure plate has an inclined surface at one end close to the limit stop bar and away from the lifting and lowering guide seat. A ball that cooperates with the inclined surface of the pressure plate is rollingly installed on the inner wall of the guide groove, and the ball is in a convex shape in the guide groove.

[0017] In a possible implementation, the pressure plate is rotatably connected to pressure rollers that are uniformly spaced along its length, and the pressure rollers are located on the end surface of the pressure plate close to the landing guide seat.

[0018] In one possible implementation, the elastic reset member includes a connecting plate 1 installed together at the ends of multiple pressure members connected to the inclined section of the push frame, a connecting plate 2 is installed at the end of the pressure plate located at the horizontal section of the push frame, both connecting plate 1 and connecting plate 2 are slidably installed in the installation groove and a reset spring 3 is installed between the installation groove, and the opposite ends of connecting plate 1 and connecting plate 2 cooperate through wedge surfaces so that the two move synchronously.

[0019] In one possible implementation, the positioning support portion includes a lifting rod slidably connected to the top of the landing guide seat, a supporting seat is installed on the top of the lifting rod, and the supporting seat is slidably connected to guide plates on both sides along its width direction. A return spring 1 is installed between the guide plate and the supporting seat, and a return spring 2 is installed between the bottom of the lifting rod and the inner wall of the landing guide seat.

[0020] In one possible implementation, the driving part includes a storage groove opened on the top of the lifting and lowering platform and connected to the landing guide seat, a sliding frame is slidably connected in the storage groove, the sliding frame and four pushing frames are connected to each other through a fixed frame, a limiting sliding groove that slides with the fixed frame is opened on the landing guide seat, a driving source (such as an electric slider, a cylinder, etc.) for driving the sliding frame is installed in the storage groove, and a locking member for locking the lifting rod is installed in the middle of the sliding frame.

[0021] In one possible implementation, the locking member includes an inverted L-shaped insertion rod installed on the top of the sliding frame, the horizontal end of the insertion rod is a wedge-shaped surface, a socket is opened on the lifting rod, a pressure rod matching the wedge-shaped surface of the insertion rod is installed on the socket, and a ball is installed on the pressure rod.

[0022] The above one or more technical solutions in the embodiments of the present invention have at least one of the following beneficial effects: 1. A locking mechanism designed by the present invention for a composite wing UAV take-off and landing platform can adjust the landing position of the UAV when the UAV lands on the take-off and landing platform through the cooperation of an alignment guide part, a positioning support part, a landing guide seat and a locking part, so that the landing gear of the UAV can accurately land on the landing guide seat, and the landing guide seat cooperates with the landing gear to limit the landing gear in time to avoid falling before the landing gear is locked. The locking part can also perform multi-point locking of the horizontal and vertical sections of the landing gear, thereby increasing the locking support height of the landing gear and greatly improving the locking effect and locking stability of the UAV.

[0023] 2. The positioning support part in the present invention can not only adjust the drone when it descends to the take-off and landing platform to avoid the drone from tilting too much and being difficult to place on the landing guide seat, but also vertically guide the drone when it takes off to avoid the problem of the drone shaking due to wind and the collision between the landing gear and the landing guide seat, which affects the take-off of the drone.

[0024] 3. The landing guide seat in the present invention is gradually inserted into the inner side of the landing gear when the UAV lands. The landing guide seat is in a trapezoidal shape with a gradually increasing lower end. The landing guide seat is used to guide the landing, preliminarily position and pre-limit the landing gear through the side wall of the landing guide seat, thereby avoiding the problem of large offset position when the UAV lands on the take-off and landing platform and falling under strong wind force. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0026] Figure 1 It is a schematic diagram of the overall three-dimensional structure of the present invention.

[0027] Figure 2 It is a schematic diagram of the first three-dimensional structure of the present invention.

[0028] Figure 3 It is a schematic diagram of the second three-dimensional structure of the present invention.

[0029] Figure 4 It is a structural schematic diagram of a locking portion of the present invention vertically cut along the horizontal section of the limit stop bar and the push frame.

[0030] Figure 5 It is a structural schematic diagram of the push-pull frame and the elastic reset member of the present invention.

[0031] Figure 6 It is a structural schematic diagram of the supporting seat, guide plate and return spring of the present invention.

[0032] Figure 7 yes Figure 3 Side sectional view of .

[0033] Reference numerals: 1, take-off and landing platform; 2, UAV; 20, landing gear; 3, landing guide seat; 4, alignment guide portion; 40, vertical plate; 41, limit guide frame; 5, guide assembly; 50, guide roller; 6, positioning support portion; 60, lifting rod; 61, support seat; 62, guide plate; 63, reset spring 1; 64, reset spring 2; 7, locking portion; 70, limit stop bar; 71, push frame; 72, pressure lock Components; 720, guide groove; 721, mounting groove; 722, guide groove; 73, elastic return member; 730, connecting plate one; 731, connecting plate two; 732, return spring three; 74, pressure member; 740, pressure plate; 741, pressure roller; 8, driving unit; 80, storage groove; 81, sliding frame; 82, fixed frame; 83, locking member; 830, insertion rod; 831, insertion hole; 832, pressure rod. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] In order to enable those skilled in the art to better understand the scheme of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0036] See also Figure 1 A locking mechanism for a composite wing UAV landing platform is used to lock the landing gear 20 of the composite wing UAV 2 after the UAV 2 lands on the landing platform 1. The landing platform 1 is an existing device with a storage cavity (not shown in the figure) for lifting and storing the UAV 2 below. The locking mechanism includes a landing guide seat 3 installed on the top of the landing platform 1, a positioning guide part 4, a guide assembly 5, a positioning support part 6, a driving part 8 and two locking parts 7. The positioning guide part 4 is used to pre-position the head of the UAV 2 when it lands.

[0037] See also Figure 2 and Figure 3The alignment guide part 4 includes a limiting guide frame 41 installed on the top of the lifting and lowering platform 1 through a vertical plate 40. The limiting guide frame 41 is in a U shape consisting of three guide plates with arc-shaped tops, with an opening facing the landing guide seat 3. A rubber protective pad (not shown in the figure) is installed on the inner wall side of the limiting guide frame 41.

[0038] The position limiting guide frame 41 guides the fuselage head of the UAV 2 to position when landing through the arc sections at the top of the three side walls, so as to facilitate the landing gear 20 to be placed on the landing guide seat 3.

[0039] See also Figure 2 and Figure 3 The landing guide seat 3 is a trapezoidal cavity structure with an inclined vertical section that cooperates with the landing gear 20, and the inclined side wall of the landing guide seat 3 is parallel to the inclined section of the landing gear 20. The landing guide seat 3 is used to pre-limit the landing gear 20. The two inclined side walls of the landing guide seat 3 are rotatably mounted with guide assemblies 5. The guide assemblies 5 are used to roll in contact with and guide the side walls of the inclined section when the landing gear 20 descends.

[0040] See also Figure 2 and Figure 3 The positioning support part 6 is arranged on the landing guide seat 3, and is used to position and support the fuselage of the drone 2 and guide it during the lifting process.

[0041] When the UAV 2 is landing, the fuselage of the UAV 2 is adjusted and positioned and supported by the alignment guide 4 and the positioning support 6 to prevent the UAV 2 from deviating too far and making it difficult for the landing gear 20 to land on the landing guide seat 3.

[0042] When the landing gear 20 lands on the landing guide seat 3, the landing guide seat 3 is gradually inserted into the inner side of the landing gear 20, and the landing guide seat 3 is used to guide the landing and preliminarily position the landing gear 20, so as to avoid a large deviation of the UAV 2 when landing on the landing platform 1, which makes it difficult for the landing platform 1 to land in the storage cavity of the landing platform 1 to fold the UAV 2.

[0043] See also Figure 2 and Figure 3 The two locking parts 7 are both arranged on the landing guide seat 3 and the take-off and landing platform 1 and are arranged along the length direction of the landing guide seat 3. The locking part 7 includes a limit stop bar 70 fixedly installed on both inclined surfaces of the landing guide seat 3 and a slidably installed push frame 71. The landing gear 20 falls between the limit stop bar 70 and the push frame 71 on the same side. The push frame 71 is in an L-shape with a vertical section inclined. A matching press lock assembly 72 is slidably arranged between the push frame 71 and the corresponding limit stop bar 70. The press lock assembly 72 is used to lock the landing gear 20 on the landing guide seat 3.

[0044] The alignment guide part 4 cooperates with the positioning support part 6 to guide the drone 2 in alignment, and can also prevent the landing gear 20 of the drone 2 from falling on the side of the corresponding limit stop bar 70 away from the push frame 71, making it difficult for the push frame 71 to cooperate with the limit stop bar 70 to lock the landing gear 20.

[0045] See also Figure 2 and Figure 3 The driving part 8 is arranged on the landing guide seat 3 and the landing platform 1, and is used to drive the push-pushing frames 71 in the two locking parts 7 to move toward the corresponding limit stop bars 70, and make the push-pushing frames 71 push the landing gear 20 to move toward the limit stop bars 70 in the process, so as to adjust the position of the UAV 2 until the landing gear 20 is tightly pressed against the limit stop bar 70 and the pressure locking assembly 72 locks the landing gear 20. The pressure locking assembly 72 cooperates with the landing guide seat 3 to lock the horizontal section and the vertical section of the landing gear 20, thereby increasing the locking support height with the landing gear 20, and greatly improving the locking effect of the landing gear 20 of the UAV 2 and the stability after locking.

[0046] When the driving unit 8 drives the push frame 71 , the positioning support unit 6 is also pressed down and locked, so that the positioning support unit 6 is separated from the fuselage, thereby preventing the positioning support unit 6 from hindering the landing gear 20 from falling onto the take-off and landing platform 1 .

[0047] See also Figure 2 and Figure 3 The guide assembly 5 includes a plurality of guide rollers 50, which are evenly arranged along the inclined surface of the landing guide seat 3 and are rotatably connected to the landing guide seat 3 and the limit stop bar 70. When the UAV 2 descends, the landing gear 20 moves along the inclined side wall of the landing guide seat 3 and contacts the guide rollers 50. The guide rollers 50 reduce the friction between the landing gear 20 and the side wall of the landing guide seat 3.

[0048] See also Figure 3 and Figure 4 The locking assembly 72 includes a plurality of guide grooves 720 provided on the inclined section and the horizontal section of the push-resistance frame 71 and close to one side of the limit stop bar 70, a connecting mounting groove 721 is provided between the plurality of guide grooves 720, a plurality of guide grooves 722 are provided on the limit stop bar 70, and a pressing member 74 cooperating with the guide groove 722 is installed between the mounting groove 721 and the plurality of guide grooves 720 through an elastic reset member 73. When the push-resistance frame 71 moves toward the limit stop bar 70, the pressing member 74 cooperates with the guide groove 722 to move toward the landing gear 20, pressing the landing gear 20 against the landing guide seat 3 and the take-off and landing platform 1.

[0049] After the landing gear 20 lands on the landing guide seat 3 and the take-off and landing platform 1, the driving unit 8 drives the push frame 71 to move toward the corresponding limit stop bar 70, and the push frame 71 pushes the landing gear 20 to move toward the limit stop bar 70 during this process, thereby adjusting the position of the UAV 2 to prevent the UAV 2 from being accurately located in the middle of the take-off and landing platform 1, which makes it difficult for the UAV 2 to enter the storage cavity later.

[0050] While the driving unit 8 drives the push frame 71 to move until the landing gear 20 is pressed against the limit stop bar 70, the pressing member 74 cooperates with the guide groove 722 to move toward the side wall of the landing gear 20 until the landing gear 20 is pressed and locked on the landing guide seat 3. The pressing member 74 presses and locks the lower horizontal section and the inclined section of the landing gear 20, thereby increasing the fixed height of the landing gear 20 and improving the stability of the UAV 2 locked on the take-off and landing platform 1.

[0051] See also Figure 3 and Figure 4 The pressing member 74 includes a plurality of pressing plates 740 that are slidably connected to the guide grooves 722. The pressing plate 740 has an inclined surface at one end close to the limit stop bar 70 and away from the lifting and lowering guide seat 3. A ball that matches the inclined surface of the pressing plate 740 is rollingly installed on the inner wall of the guide groove 722, and the ball is convex in the guide groove 722.

[0052] See also Figure 3 and Figure 4 The pressure plate 740 is rotatably connected with a pressure roller 741 that is uniformly arranged along its length direction. The pressure roller 741 is located on the end surface of the pressure plate 740 close to the landing guide seat 3. When the pressure plate 740 moves toward the side wall of the landing gear 20 and moves along the width direction of the landing gear 20, the pressure roller 741 rolls in contact with the side wall of the landing gear 20, thereby reducing the friction force of the pressure plate 740 when it moves along the side wall of the landing gear 20.

[0053] See also Figure 4 and Figure 5 The elastic reset member 73 includes a connecting plate 1 730 installed together at the ends of multiple pressure members 74 connected to the inclined section of the push frame 71, and a connecting plate 2 731 is installed at the end of the pressure plate 740 located at the horizontal section of the push frame 71. The connecting plate 1 730 and the connecting plate 2 731 are both slidably installed in the installation groove 721 and a reset spring 3 732 is installed between the installation groove 721. The opposite ends of the connecting plate 1 730 and the connecting plate 2 731 are matched through wedge surfaces so that the two move synchronously.

[0054] When the push frame 71 moves toward the limit stop bar 70, the pressure plate 740 is inserted into the guide groove 722, and the inclined surface at the end of the pressure plate 740 rolls in contact with the ball in the guide groove 722, and the ball in the guide groove 722 gradually squeezes the pressure plate 740 to move toward the side wall of the landing gear 20 during the movement of the pressure plate 740, and the pressure plate 740 drives the corresponding connecting plate 1 730 and the connecting plate 2 731 to move, and the connecting plate 1 730 and the connecting plate 2 731 inclined surfaces cooperate to move synchronously and squeeze the corresponding return spring 3 732, so that multiple pressure plates 740 can move simultaneously to lock the landing gear 20 at multiple points, which greatly improves the locking height and local pressure strength of the landing gear 20.

[0055] See also Figure 6 and Figure 7 The positioning support part 6 includes a lifting rod 60 slidably connected to the top of the landing guide seat 3, a supporting seat 61 is installed on the top of the lifting rod 60, and the supporting seat 61 is slidably connected to guide plates 62 on both sides of the width direction of the supporting seat 61. A return spring 1 63 is installed between the guide plate 62 and the supporting seat 61, and a return spring 2 64 is installed between the bottom of the lifting rod 60 and the inner wall of the landing guide seat 3.

[0056] When the drone 2 is in a tilted state with the landing guide seat 3 during its descent, the bottom of the drone 2 hits against one of the guide plates 62 on one side, and then continues to move downward. Under the elastic force of the return spring 1 63 and its own arc-shaped guiding action, the guide plate 62 causes the fuselage of the drone 2 to move toward the supporting seat 61, thereby adjusting the drone 2 to avoid a large tilt deviation of the drone 2, which makes it difficult to place it on the landing guide seat 3. When the drone 2 continues to move downward, it presses the supporting seat 61 and the lifting rod 60 downward and squeezes the return spring 2 64.

[0057] After the landing gear 20 is inserted into the landing guide seat 3, when the driving unit 8 is working, the driving unit 8 presses the lifting rod 60 downward, so that the supporting seat 61 is separated from the fuselage of the UAV 2, thereby preventing the supporting seat 61 from being in a state of pushing the UAV 2 under the elastic force of the return spring 2 64, making it difficult for the push frame 71 and the pressure plate 740 to lock the landing gear 20 tightly on the landing guide seat 3.

[0058] When the driving part 8 drives the locking part 7 to unlock the landing gear 20, the supporting seat 61 supports the fuselage of the UAV 2 again under the elastic force of the return spring 2 64, and then the UAV 2 takes off vertically. The supporting seat 61 and the lifting rod 60 gradually move upward under the elastic force of the return spring, thereby vertically guiding the take-off of the UAV 2 to avoid the problem that the wind causes the UAV 2 to shake, the landing gear 20 collides with the landing guide seat 3, and affects the take-off of the UAV 2.

[0059] See also Figure 2 and Figure 7 The driving part 8 includes a storage groove 80 opened on the top of the lifting and lowering platform 1 and connected to the landing guide seat 3. A sliding frame 81 is slidably connected in the storage groove 80. The sliding frame 81 and the four push frames 71 are connected through a fixed frame 82. A limiting sliding groove that slides with the fixed frame 82 is opened on the landing guide seat 3. A driving source (such as an electric slider, a cylinder, etc.) for driving the sliding frame 81 is installed in the storage groove 80. A locking member 83 for locking the lifting rod 60 is installed in the middle of the sliding frame 81.

[0060] The driving source drives the sliding frame 81, the fixed frame 82, the push frame 71 and the locking member to move, and the locking member presses down and locks the lifting rod 60. The multiple push frames 71 simultaneously drive the respective connected push plates 740 to move and press and lock the landing gear 20 on the landing guide seat 3.

[0061] See also Figure 7 The locking member 83 includes an inverted L-shaped plug rod 830 installed on the top of the sliding frame 81, the horizontal end of the plug rod 830 is a wedge-shaped surface, a socket 831 is opened on the lifting rod 60, and a pressure rod 832 matching the wedge-shaped surface of the plug rod 830 is installed on the socket 831, and a ball is installed on the pressure rod 832.

[0062] During the movement, the sliding frame 81 drives the insertion rod 830 to move toward the lifting rod 60. After the end of the insertion rod 830 is inserted into the insertion hole 831, the inclined surface of the insertion rod 830 contacts and presses the pressing rod 832 and the lifting rod 60 to move downward, so that the lifting rod 60 drives the supporting seat 61 to move downward and squeezes the return spring 2 64, preventing the bottom of the landing gear 20 from failing to fully contact the landing platform 1 and the landing guide seat 3 under the supporting action of the return spring 2 64.

[0063] See also Figure 1-Figure 7 Working principle: When the UAV 2 lands, the fuselage of the UAV 2 is adjusted and positioned and supported under the cooperation of the alignment guide part 4 and the positioning support part 6, so as to prevent the UAV 2 from deviating a large distance and making it difficult for the landing gear 20 to land on the landing guide seat 3.

[0064] When the landing gear 20 lands on the landing guide seat 3, the landing guide seat 3 is gradually inserted into the inner side of the landing gear 20. The landing guide seat 3 is a trapezoid with a gradually increasing lower end. The landing guide seat 3 is used to guide the landing and preliminarily position the landing gear 20 to avoid a large deviation of the UAV 2 when landing on the take-off and landing platform 1, which makes it difficult for the take-off and landing platform 1 to land in the box and fold the UAV 2.

[0065] Then the driving part 8 drives the push frame 71 in the two locking parts 7 to move toward the corresponding limit stop bar 70, and makes the push frame 71 push the landing gear 20 to move toward the limit stop bar 70 in the process, so as to adjust the position of the UAV 2, until the landing gear 20 is pressed against the limit stop bar 70 and the pressure lock assembly 72 locks the landing gear 20, and the pressure lock assembly 72 cooperates with the landing guide seat 3 to lock the horizontal section and the vertical section of the landing gear 20, thereby increasing the locking support height with the landing gear 20, greatly improving the locking effect of the landing gear 20 of the UAV 2 and the stability after locking.

[0066] In the description of the present invention, it is necessary to understand that the terms "length", "width", "up", "down", "vertical", "horizontal", "top", "bottom", "inside", "outside", "axial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0067] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "connect", "install", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0068] The embodiments of this specific implementation method are all preferred embodiments of the present invention, and are not intended to limit the protection scope of the present invention. Therefore, all equivalent changes made according to the structure, shape, and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A locking mechanism for a composite wing UAV take-off and landing platform, used to lock the landing gear of the composite wing UAV, the take-off and landing platform is used to lift and store the UAV, characterized in that: The locking mechanism includes a landing guide seat installed on the top of the landing platform for pre-limiting the landing gear and a positioning guide part for pre-positioning the UAV during landing. The landing guide seat is a trapezoidal cavity structure with an inclined vertical section that matches the landing gear. Two guide assemblies, respectively arranged on two inclined side walls of the landing guide seat, are used for rolling contact and guiding the inclined section of the landing gear when the landing gear descends; The positioning support part is arranged on the landing guide seat and is used to position and support the UAV and guide it during the lifting process; Two locking parts are arranged on the landing guide seat, and the locking parts include limit stop bars fixedly installed on the two inclined surfaces of the landing guide seat and a push frame slidably installed, and a matching press lock assembly is slidably arranged between the push frame and the corresponding limit stop bars, and the press lock assembly is used to lock the horizontal section and the inclined section of the landing gear on the landing guide seat; The driving part is arranged on the landing guide seat and the take-off and landing platform; the driving part is used to drive the locking part to push the landing gear to align and lock the landing gear.

2. The locking mechanism for a composite wing UAV take-off and landing platform according to claim 1, characterized in that: The compression lock assembly includes a plurality of guide grooves provided on the inclined section and the horizontal section of the push frame and close to one side of the limit stop bar, a plurality of connecting mounting grooves are provided between the plurality of guide grooves, and a plurality of guide grooves are provided on the limit stop bar; A pressing piece matched with the guide groove is installed between the installation groove and the multiple guide grooves through an elastic reset piece. When the push frame moves toward the limit stop bar, the pressing piece matches with the guide groove and moves toward the landing gear, pressing the landing gear against the landing guide seat and the take-off and landing platform.

3. The locking mechanism for a composite wing UAV take-off and landing platform according to claim 2, characterized in that: The positioning support part includes a lifting rod slidably connected to the top of the landing guide seat, a supporting seat is installed on the top of the lifting rod, and guide plates are slidably connected to the supporting seat on both sides along its width direction. A return spring 1 is installed between the guide plate and the supporting seat, and a return spring 2 is installed between the bottom of the lifting rod and the inner wall of the landing guide seat.

4. The locking mechanism for a composite wing UAV take-off and landing platform according to claim 2, characterized in that: The pressing member includes a pressing plate slidably connected to a plurality of guide grooves, the pressing plate has an inclined surface at one end close to the limit stop bar and away from the lifting and lowering guide seat, and a ball that matches the inclined surface of the pressing plate is rollingly installed on the inner wall of the guide groove, and the ball is convex in the guide groove.

5. The locking mechanism for a composite wing UAV take-off and landing platform according to claim 3, characterized in that: The driving part also locks the positioning support part. The driving part includes a storage groove opened on the top of the lifting and lowering platform and connected to the landing guide seat. A sliding frame is slidably connected in the storage groove. The sliding frame and four push frames are connected to each other through a fixed frame. A limiting sliding groove that slides with the fixed frame is opened on the landing guide seat. A driving source for driving the sliding frame is installed in the storage groove. A locking member for locking the lifting rod is installed in the middle of the sliding frame.

6. The locking mechanism for a composite wing UAV take-off and landing platform according to claim 2, characterized in that: The elastic reset member includes a connecting plate 1 which is installed together at the ends of multiple pressure members connected to the inclined section of the push frame, and a connecting plate 2 is installed at the end of the pressure plate located at the horizontal section of the push frame. Both the connecting plate 1 and the connecting plate 2 are slidably installed in the installation groove and a reset spring 3 is installed between the installation groove. The opposite ends of the connecting plate 1 and the connecting plate 2 cooperate with each other through wedge surfaces so that the two move synchronously.

7. The locking mechanism for a composite wing UAV take-off and landing platform according to claim 1, characterized in that: The guide assembly comprises a plurality of guide rollers, which are evenly arranged along the inclined surface of the landing guide seat and are rotatably connected to the landing guide seat and the limit stop bar.

8. The locking mechanism for a composite wing UAV take-off and landing platform according to claim 1, characterized in that: The alignment guide part comprises a limit guide frame installed on the top of the lifting and lowering platform through a vertical plate. The limit guide frame is in a U shape consisting of three guide plates with arc-shaped tops and an opening facing the landing guide seat.

9. The locking mechanism for a composite wing UAV take-off and landing platform according to claim 4, characterized in that: The pressure plate is rotatably connected with pressure rollers that are uniform along its length direction, and the pressure rollers are located on the end surface of the pressure plate close to the landing guide seat.

10. The locking mechanism for a composite wing UAV take-off and landing platform according to claim 5, characterized in that: The locking member comprises an inverted L-shaped plug rod installed on the top of the sliding frame, the horizontal end of the plug rod is a wedge-shaped surface, a plug hole is opened on the lifting rod, and a pressure rod matching the wedge-shaped surface of the plug rod is installed on the plug hole.

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