Variable-diameter launching structure of barrel-launched unmanned aerial vehicle

Abstract

The invention belongs to the technical field of unmanned aerial vehicle launching devices, and particularly relates to a variable-diameter launching structure of a barrel-launched unmanned aerial vehicle. Comprising a cylindrical machine body, an infolding rotor wing assembly, an adjustable positioning assembly and a replaceable launching base. The cylindrical aircraft body is of a light shell structure, and a plurality of rotor wing positioning grooves are formed in the outer wall of the cylindrical aircraft body in an annular array; the infolding rotor assemblies are mounted in the rotor positioning grooves; the adjustable positioning assembly comprises a mounting base, an L-shaped pressing rod, a U-shaped sliding block and an adjusting bolt. The device further comprises a plurality of replaceable launching bases with different inner diameters, and the replaceable launching bases are connected to the outer portion of the installation base in a sleeving mode. The variable-diameter launching structure of the barrel-launched unmanned aerial vehicle is mainly used for achieving single-barrel launching of unmanned aerial vehicles of various types and sizes, the requirement for launching barrels is reduced, the carrying amount of large equipment is reduced, the operation concealment is improved, and the launching material cost is reduced.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicle (UAV) launching devices, and in particular relates to a variable-diameter launching structure for a tube-launched UAV. Background Art

[0002] The drone barrel launch technology is based on launching in a launch tube, which is easy to hide and carry, has drone protection functions, has low launch costs and is easy to operate. It is a very commonly used drone launch solution. During use, the drone needs to match the launch tube with a suitable inner diameter according to its own outer dimensions. When barrel launch is used as the main launch mode, it is necessary to enable multiple drones to share the same launch tube as much as possible to minimize the number of launch tubes required. However, in different mission types, due to different performance requirements such as concealment and load capacity, drones inevitably have different outer dimensions, and drones with large differences in outer dimensions generally cannot be launched using the same launch tube. This results in a small number of drones needing to carry additional launch tubes during some missions, affecting mission efficiency and implementation costs. Summary of the invention

[0003] The purpose of the present invention is to provide a variable-diameter launching structure for launching drones of different sizes using the same launching tube, thereby reducing the demand for launching tubes for drones of different sizes and types.

[0004] To achieve the above purpose, the present invention adopts the following technical solution.

[0005] A variable-diameter launch structure for a tube-launched UAV, comprising a tube-type body 1, an inward-folding rotor assembly 2, an adjustable positioning assembly 3, and a replaceable launch seat 4;

[0006] The cylindrical body 1 is a light shell structure, and a plurality of rotor positioning grooves 1a are arranged in a circular array on the outer wall of the cylindrical body 1; the inward folding rotor assembly 2 is installed in the rotor positioning groove 1a, and the front end of the inward folding rotor assembly 2 is connected to the inner wall of the rotor positioning groove 1a;

[0007] The adjustable positioning assembly 3 includes a mounting seat 30, an L-shaped pressure rod 31, a U-shaped slider 32, and an adjusting bolt 34;

[0008] The mounting seat 30 is arranged at the rear side of the cylindrical body 1, and a mounting cavity 3a is dug out at the front side of the mounting seat 30. A mounting portion 3b facing the rotor positioning groove 1a is arranged on the inner wall of the mounting cavity 3a, and a positioning column 3c is arranged between adjacent mounting portions 3b. A spring mounting cavity is arranged at the bottom of the mounting cavity 3a.

[0009] The mounting portion 3b is provided with a mounting groove 3e penetrating the front side and the inner side of the mounting portion 3b, the inner walls on both sides of the mounting groove 3e are provided with guide grooves 3t, and the outer inner wall of the mounting groove 3e is provided with an adjusting screw hole 3f;

[0010] A connecting platform 1b is provided at the rear side of the cylinder body 1 and is inserted between the ends of the positioning posts 3c. The positioning posts 3c extend toward the center of the mounting seat 30, and the ends thereof abut against the connecting platform 1b.

[0011] The U-shaped slider 32 is slidably arranged in the guide slot 3t and can slide in the inward and outward directions; the two symmetrical arms of the U-shaped slider 32 are provided with a shaft hole 3g, and the arm body perpendicular to the two arms is provided with a connecting hole 3h; the connecting hole 3h is coaxial with the adjusting screw hole 3f, and the adjusting bolt 34 is screwed into the adjusting screw hole 3f from the outside and then inserted into the connecting hole 3h and rotatably connected to the U-shaped slider 32; the shaft hole 3g is perpendicular to the central axis of the cylinder body 1;

[0012] The short arm portion of the L-shaped pressure rod 31 is inserted into the rear side of the connecting platform 1b, and connecting shafts that can be inserted into the rotating shaft holes 3g are provided on both sides of the bent portion of the L-shaped pressure rod 31;

[0013] A compression spring 6 is arranged in the spring installation cavity, and a spring cover plate 35 is arranged on the front side of the compression spring. The spring cover plate 35 can abut against the rear side of the short arm of the L-shaped pressure rod 31;

[0014] It comprises a plurality of replaceable launching seats 4 with different inner diameters, and the replaceable launching seats 4 are sleeved on the outside of the mounting seat 30 .

[0015] A further improvement or preferred embodiment of the aforementioned variable-diameter launching structure of a barrel-launched UAV, a spring mounting hole is provided at the bottom of the mounting cavity 3a, the front edge of the spring mounting hole extends inward to form a limit platform 3k, the rear inner wall of the spring mounting hole is provided with an internal thread, a spring positioning box 5b is installed on the rear side of the spring mounting hole, the spring positioning box 5b is a cylindrical structure, and its outer wall is provided with an external thread matching the internal thread; the spring cover plate 35 is a cap-shaped structure, and the cap body part passes through the middle opening of the limit platform 3k, and the brim part rests against the rear inner wall of the limit platform 3k; the inner cavity of the spring positioning box 5b, the inner wall of the spring mounting hole and the rear inner wall of the spring cover plate 35 form a spring mounting cavity.

[0016] A further improvement or preferred embodiment of the aforementioned variable-diameter launching structure of the barrel-launched UAV is that a roller 5a is provided at the front end of the L-shaped pressure rod 31, a connecting platform 3j is provided on the inner side of the middle part of the L-shaped pressure rod 31, a V-shaped elastic member 33 is installed on the connecting platform 3j, the middle part of the V-shaped elastic member 33 is fixed on the connecting platform 3j, and two arms extend to one side of the barrel body 1 and abut against the outer wall of the barrel body 1.

[0017] A further improvement or preferred embodiment of the aforementioned variable-diameter launching structure of the tube-launched UAV is that the inner side of the rod body of the L-shaped pressure rod 31 is provided with a protrusion 3m extending toward the rotor positioning groove 1a, and the protrusion 3m abuts against the inward-folding rotor assembly 2 in the rotor positioning groove 1a.

[0018] A further improvement or preferred embodiment of the aforementioned variable-diameter launching structure of a barrel-launched UAV, the replaceable launching seat 4 comprises a barrel body 4a, an annular connecting portion 4b extending inward from an opening on the front side of the barrel body and resting against an outer wall of the mounting seat 30, the inner wall of the annular connecting portion 4b and the outer wall of the mounting seat 30 being connected by threads.

[0019] A further improvement or preferred embodiment of the aforementioned variable-diameter launching structure of a barrel-launched UAV, wherein the barrel-type fuselage 1 is a closed barrel-type structure, and the rotor positioning groove 1a is formed by a local inward concave deformation of the outer wall of the barrel-type fuselage 1; the rotor positioning groove 1a extends in a straight line along the front-to-back direction.

[0020] A further improvement or preferred embodiment of the aforementioned variable-diameter launching structure of a tube-launched UAV, wherein the inner side of the rear end of the rotor positioning slot 1a is recessed inward to form a accommodating chamber 1n; the inward-folding rotor assembly 2 comprises: a rotor arm 2a that can be folded and stored in the rotor positioning slot 1a, a waterproof motor 2b arranged on the inner side of the end of the rotor arm 2a, and a rotor 2c assembled on the motor shaft of the waterproof motor 2b.

[0021] Its beneficial effects are:

[0022] The variable-diameter launch structure for tube-launched UAVs of the present application is mainly used to enable single-tube launch of various types and sizes of UAVs, thereby reducing the demand for launch tubes, reducing the amount of large equipment carried, improving the concealment of operations, and reducing the material cost of launch. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is a schematic diagram of the variable-diameter launch structure of a tube-launched UAV;

[0024] Figure 2 This is a partial schematic diagram of the variable-diameter launch structure of a tube-launched UAV;

[0025] Figure 3 This is a partial enlarged view of the variable-diameter launch structure of the tube-launched UAV.

[0026] Figure 4 is a schematic diagram of the structure of the mounting base 30;

[0027] The reference numerals include:

[0028] Cylindrical body 1, rotor positioning groove 1a, connecting platform 1b, accommodating chamber 1n, inward folding rotor assembly 2, rotor arm 2a, waterproof motor 2b, rotor 2c, adjustable positioning assembly 3, mounting cavity 3a, mounting part 3b, positioning column 3c, mounting groove 3e, adjusting screw hole 3f, rotating shaft hole 3g, connecting hole 3h, connecting platform 3j, limiting platform 3k, guide protrusion 3m, slide groove 3t, mounting seat 30, L-shaped pressure rod 31, U-shaped slider 32, V-shaped elastic member 33, adjusting bolt 34, spring cover plate 35, replaceable launching seat 4, cylinder body 4a, annular connecting part 4b, roller 5a, spring positioning box 5b. DETAILED DESCRIPTION

[0029] The present invention is described in detail below in conjunction with specific embodiments.

[0030] The variable-diameter launch structure of the tube-launched UAV in the present application is mainly used to meet the launch requirements of different types of tube-launched UAVs, enabling them to be launched through as few launch tubes as possible, while expanding their launch methods, and can be applied to various types of UAV launch operations based on tube-launching in water and land environments.

[0031] like Figure 1 As shown, a variable-diameter launch structure of a barrel-launched UAV of the present application mainly comprises a barrel-type body 1, an inward-folding rotor assembly 2, an adjustable positioning assembly 3, and a replaceable launch seat 4;

[0032] The cylindrical body 1 is a light shell structure, and a plurality of rotor positioning grooves 1a are arranged in a circular array on the outer wall of the cylindrical body 1; the inward folding rotor assembly 2 is installed in the rotor positioning groove 1a, and the front end of the inward folding rotor assembly 2 is connected to the inner wall of the rotor positioning groove 1a;

[0033] The adjustable positioning assembly 3 includes a mounting seat 30, an L-shaped pressure rod 31, a U-shaped slider 32, and an adjusting bolt 34;

[0034] The mounting seat 30 is arranged at the rear side of the cylindrical body 1, and a mounting cavity 3a is dug out at the front side of the mounting seat 30. A mounting portion 3b facing the rotor positioning groove 1a is arranged on the inner wall of the mounting cavity 3a, and a positioning column 3c is arranged between adjacent mounting portions 3b. A spring mounting cavity is arranged at the bottom of the mounting cavity 3a.

[0035] The mounting portion 3b is provided with a mounting groove 3e penetrating the front side and the inner side of the mounting portion 3b, the inner walls on both sides of the mounting groove 3e are provided with guide grooves 3t, and the outer inner wall of the mounting groove 3e is provided with an adjusting screw hole 3f;

[0036] The adjustable positioning assembly 3 constitutes the positioning support structure of the UAV, transmitting the rear launch thrust to the UAV body so that it can be launched smoothly, wherein a compression spring is arranged in the mounting seat so that the pressure rod can support the inner wall of the launch channel;

[0037] A connecting platform 1b is provided at the rear side of the cylinder body 1 and is inserted between the ends of the positioning posts 3c. The positioning posts 3c extend toward the center of the mounting seat 30, and the ends thereof abut against the connecting platform 1b.

[0038] The U-shaped slider 32 is slidably arranged in the guide slot 3t and can slide in the inward and outward directions; the two symmetrical arms of the U-shaped slider 32 are provided with a shaft hole 3g, and the arm body perpendicular to the two arms is provided with a connecting hole 3h; the connecting hole 3h is coaxial with the adjusting screw hole 3f, and the adjusting bolt 34 is screwed into the adjusting screw hole 3f from the outside and then inserted into the connecting hole 3h and rotatably connected to the U-shaped slider 32; the shaft hole 3g is perpendicular to the central axis of the cylinder body 1;

[0039] The short arm portion of the L-shaped pressure rod 31 is inserted into the rear side of the connecting platform 1b, and connecting shafts that can be inserted into the rotating shaft holes 3g are provided on both sides of the bent portion of the L-shaped pressure rod 31;

[0040] A compression spring 6 is arranged in the spring installation cavity, and a spring cover plate 35 is arranged on the front side of the compression spring. The spring cover plate 35 can abut against the rear side of the short arm of the L-shaped pressure rod 31;

[0041] It includes a plurality of replaceable launch bases 4 with different inner diameters, and the replaceable launch bases 4 are sleeved on the outside of the mounting base 30;

[0042] The replaceable launching seat 4 includes a barrel body 4a, an annular connecting portion 4b extending inward from the opening at the front side of the barrel body and resting against the outer wall of the mounting seat 30, and the inner wall of the annular connecting portion 4b and the outer wall of the mounting seat 30 are connected by threads.

[0043] Among them, the interchangeable launching seat 4 is mainly used to assemble launching gunpowder or launching device to provide driving force for the UAV launch. It is easy to know that the outer diameter of the interchangeable launching seat 4 matches the inner diameter of the launching channel to ensure effective propulsion. The UAV positioning support structure composed of the front adjustable positioning component 3 ensures that the UAV can be connected to the interchangeable launching seat 4 and prevents it from shaking. The built-in compression spring ensures that the pressure rod can be close to the launching channel to ensure stable support and store elastic potential energy to ensure that the launching device can quickly open the pressure rod after being launched from the channel to release the UAV. At the same time, the tail of the pressure rod will push the UAV to further accelerate under the push of the spring at the moment the pressure rod is opened, increase the shooting speed, and at the same time make the moving part of the launching device separate from the UAV.

[0044] A spring mounting hole is provided at the bottom of the mounting cavity 3a, and the front edge of the spring mounting hole extends inward to form a limit platform 3k. The rear inner wall of the spring mounting hole is provided with an internal thread. A spring positioning box 5b is installed at the rear side of the spring mounting hole. The spring positioning box 5b is a cylindrical structure, and its outer wall is provided with an external thread matching the internal thread; the spring cover plate 35 is a cap-shaped structure, and the cap body part passes through the middle opening of the limit platform 3k, and the brim part abuts against the rear inner wall of the limit platform 3k; the inner cavity of the spring positioning box 5b, the inner wall of the spring mounting hole and the rear inner wall of the spring cover plate 35 form a spring mounting cavity.

[0045] A roller 5a is provided at the front end of the L-shaped pressure rod 31, a connecting platform 3j is provided on the inner side of the middle part of the L-shaped pressure rod 31, a V-shaped elastic member 33 is installed on the connecting platform 3j, the middle part of the V-shaped elastic member 33 is fixed on the connecting platform 3j, and the two arms extend to one side of the cylindrical body 1 and abut against the outer wall of the cylindrical body 1.

[0046] The inner side of the rod body of the L-shaped pressure rod 31 is provided with a protrusion 3m extending toward the rotor positioning groove 1a, wherein the protrusion 3m abuts against the inward-folding rotor assembly 2 in the rotor positioning groove 1a.

[0047] The cylindrical body 1 is a closed cylindrical structure, wherein the rotor positioning groove 1a is formed by the outer wall of the cylindrical body 1 partially concave and deformed inward; the rotor positioning groove 1a extends linearly along the front-rear direction.

[0048] The inner side of the rear end of the rotor positioning groove 1a is recessed inward to form a accommodating chamber 1n; the inward-folding rotor assembly 2 includes: a rotor arm 2a that can be folded and stored in the rotor positioning groove 1a, a waterproof motor 2b arranged on the inner side of the end of the rotor arm 2a, and a rotor 2c assembled on the motor shaft of the waterproof motor 2b.

[0049] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention, rather than to limit the scope of protection of the present invention. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solution of the present invention can be modified or replaced by equivalents without departing from the essence and scope of the technical solution of the present invention.

Claims

1. A variable-diameter launch structure for a tube-launched UAV, characterized in that: It comprises a cylindrical body (1), an inward-folding rotor assembly (2), an adjustable positioning assembly (3), and a replaceable launching seat (4); The cylindrical body (1) is a light shell structure, and a plurality of rotor positioning grooves (1a) are arranged in a circular array on the outer wall of the cylindrical body (1); the inward-folding rotor assembly (2) is installed in the rotor positioning groove (1a), and the front end of the inward-folding rotor assembly (2) is connected to the inner wall of the rotor positioning groove (1a); The adjustable positioning assembly (3) comprises a mounting seat (30), an L-shaped pressure rod (31), a U-shaped sliding block (32), and an adjusting bolt (34); The mounting seat (30) is arranged at the rear side of the cylindrical body (1), and a mounting cavity (3a) is dug out at the front side of the mounting seat (30); a mounting portion (3b) directly facing the rotor positioning groove (1a) is arranged on the inner wall of the mounting cavity (3a); positioning columns (3c) are arranged between adjacent mounting portions (3b); and a spring mounting cavity is arranged at the bottom of the mounting cavity (3a); The mounting portion (3b) is provided with a mounting groove (3e) penetrating the front side and the inner side of the mounting portion (3b); guide sliding grooves (3t) are provided on the inner walls on both sides of the mounting groove (3e); and an adjusting screw hole (3f) is provided on the outer inner wall of the mounting groove (3e); A connecting platform (1b) is provided on the rear side of the cylindrical body (1) and is inserted between the ends of the positioning columns (3c). The positioning columns (3c) extend toward the center of the mounting seat (30) and the ends thereof abut against the connecting platform (1b). The U-shaped slider (32) is slidably arranged in the guide slot (3t) and can slide in the inward and outward directions; two symmetrical arms of the U-shaped slider (32) are provided with a rotating shaft hole (3g), and an arm body perpendicular to the two arms is provided with a connecting hole (3h); the connecting hole (3h) is coaxial with the adjusting screw hole (3f), and the adjusting bolt (34) is screwed into the adjusting screw hole (3f) from the outside and then inserted into the connecting hole (3h) and rotatably connected to the U-shaped slider (32); the rotating shaft hole (3g) is perpendicular to the central axis of the cylinder body (1); The short arm portion of the L-shaped pressure rod (31) is inserted into the rear side of the connecting platform (1b), and connecting shafts that can be inserted into the rotating shaft holes (3g) are provided on both sides of the bent portion of the L-shaped pressure rod (31); A compression spring (6) is arranged in the spring installation cavity, and a spring cover plate (35) is arranged on the front side of the compression spring. The spring cover plate (35) can abut against the rear side of the short arm of the L-shaped pressure rod (31); It comprises a plurality of replaceable launching seats (4) with different inner diameters, and the replaceable launching seats (4) are sleeved on the outside of the mounting seat (30).

2. The variable-diameter launch structure for a tube-launched UAV according to claim 1 is characterized in that: A spring installation hole is provided at the bottom of the installation cavity (3a), the front edge of the spring installation hole extends inward to form a limit platform (3k), the rear inner wall of the spring installation hole is provided with an internal thread, a spring positioning box (5b) is installed at the rear side of the spring installation hole, the spring positioning box (5b) is a cylindrical structure, and its outer wall is provided with an external thread matching the internal thread; the spring cover plate (35) is a cap-shaped structure, and the cap body part passes through the middle opening of the limit platform (3k), and the brim part abuts against the rear inner wall of the limit platform (3k); the inner cavity of the spring positioning box (5b), the inner wall of the spring installation hole and the rear inner wall of the spring cover plate (35) surround the spring installation cavity.

3. The variable-diameter launch structure for a tube-launched UAV according to claim 1 is characterized in that: The front end of the L-shaped pressure rod (31) is provided with a roller (5a), the inner side of the middle part of the L-shaped pressure rod (31) is provided with a connecting platform (3j), a V-shaped elastic member (33) is installed on the connecting platform (3j), the middle part of the V-shaped elastic member (33) is fixed on the connecting platform (3j), and two arms extend toward one side of the cylindrical body (1) and abut against the outer wall of the cylindrical body (1).

4. The variable-diameter launch structure for a tube-launched UAV according to claim 3 is characterized in that: A protrusion (3m) extending toward the rotor positioning groove (1a) is provided on the inner side of the rod body of the L-shaped pressure rod (31), and the protrusion (3m) abuts against the inward-folding rotor assembly (2) in the rotor positioning groove (1a).

5. The variable-diameter launch structure for a tube-launched UAV according to claim 1 is characterized in that: The replaceable launching seat (4) comprises a barrel (4a), an annular connecting portion (4b) extending inward from the front opening of the barrel and abutting against the outer wall of the mounting seat (30), wherein the inner wall of the annular connecting portion (4b) and the outer wall of the mounting seat (30) are connected by threads.

6. The variable-diameter launch structure for a tube-launched UAV according to claim 1 is characterized in that: The cylindrical body (1) is a closed cylindrical structure, and the rotor positioning groove (1a) is formed by partially inwardly concave deformation of the outer wall of the cylindrical body (1); the rotor positioning groove (1a) extends linearly in the front-rear direction.

7. The variable-diameter launch structure for a tube-launched UAV according to claim 6 is characterized in that: The rear end inner side of the rotor positioning groove (1a) is recessed inward to form a receiving chamber (1n); the inward folding rotor assembly (2) comprises: a rotor arm (2a) that can be folded and received in the rotor positioning groove (1a), a waterproof motor (2b) disposed on the inner side of the end of the rotor arm (2a), and a rotor (2c) mounted on the motor shaft of the waterproof motor (2b).

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