Unmanned aerial vehicle launch tube structure

Abstract

An unmanned aerial vehicle launch tube structure is provided. [Solution] The unmanned aerial vehicle launch tube structure comprises a tube body 10, an ejection piston unit 30, a positioning base 40, a quick release unit, a loading section cover 70, a chemical gas generation module 80, and a reinforcing support ring 90. The chemical gas generation module 80 and the loading section cover 70 are continuously loadable, and the chemical gas generation module 80 is electronically activated to generate gas propulsion, launching the unmanned aerial vehicle from the tube body. Rapid replenishment of the replaceable chemical gas generation module 80 enables highly efficient continuous deployment, significantly improving operational efficiency and tactical readiness, and achieving practical advances in terms of enabling rapid replenishment of the propulsion source in use.

Description

[Technical Field]

[0001] This invention relates to the structure of an unmanned aerial vehicle launcher, in particular to an unmanned aerial vehicle launcher with a modularized chemical mixture loading mechanism, a hermetically sealed propulsion structure, and an adjustable elevation support mechanism, which is applicable to military deployment, disaster relief, border surveillance, or special missions, and belongs to the technical field of unmanned aerial vehicle launcher structures, which can effectively improve the launch efficiency of unmanned aerial vehicles and their rapid deployment capabilities on site. [Background technology]

[0002] In recent years, unmanned aerial vehicle technology has been widely applied in fields such as military, disaster relief, reconnaissance, and agriculture. To meet the demand for immediate deployment in diverse environments, the launch and deployment methods of unmanned aerial vehicles have also been attracting increasing attention. Conventional unmanned aerial vehicle launchers mainly use a system that utilizes high-pressure gas generated by an air compressor as propulsion. For example, Patent Document 1, "Deployable Wing Maneuverable Unmanned Aerial Vehicle for Launch, Storage and Transport," has a tubular structure for both launch and storage and transport, a support leg frame unit including a left support leg frame and a right support leg frame inside, and a launch auxiliary assembly that incorporates a launch controller, a thrust generation module and a kinetic energy auxiliary propulsion mechanism. The thrust generating module may be provided with at least one high-pressure gas release auxiliary propulsion unit or a rapid gas generation expansion boost mechanism. However, conventional firing systems have several drawbacks, particularly limited efficiency in continuous firing. Air compressors require pressure buildup to generate high-pressure gas, and users must wait for the pressure buildup to be completed before firing the next shot, which significantly impairs readiness and tactical flexibility.

[0003] Furthermore, conventional launch tubes are mostly made of metal or carbon fiber materials, which tend to block radio waves and disrupt communication between the unmanned aerial vehicle and the control center. This poses a problem in that unmanned aircraft are prone to loss of control or crashes due to poor signal quality when launched.

[0004] Furthermore, the conventional structure lacks a quick release or safe locking mechanism when operating or loading the explosive module, which makes maintenance and use inconvenient. Furthermore, it lacks structural reinforcement, elevation adjustment, and modular assembly design, limiting its range of application and the diversity of its use scenarios. Therefore, there is a strong need for a fast-loading, easy-to-deploy, and structurally stable unmanned aerial vehicle launcher structure that can improve the deployment capabilities and overall operability of unmanned aerial vehicles. [Prior art documents] [Patent documents]

[0005] [Patent Document 1] Republic of China Publication No. M668050 Specification Summary of the Invention [Problem to be solved by the invention]

[0006] The prior art has drawbacks in terms of quick loading, easy deployment, and stable construction. [Means for solving the problem]

[0007] This invention relates to an unmanned aerial vehicle launcher equipped with a modularized chemical gas generation module, airtight sealing, and an adjustable elevation support mechanism. It also relates to an unmanned aerial vehicle launcher structure that can be quickly assembled and disassembled, provides stable pneumatic propulsion and structural stability during the launch process, and effectively improves the deployment efficiency of unmanned aerial vehicles and the flexibility of their operation on the battlefield.

[0008] The unmanned aerial vehicle launch tube structure of the present invention comprises a hollow tube body, an ejection piston unit, a positioning base, a quick release unit, a loading compartment cover, and a chemical gas generating module; The hollow tube defines a firing space therein, the tube having a firing end and a connecting end; The injection piston unit is movably installed in the firing space, the injection piston unit has a piston, a support seat is installed at the top end of the piston, a receiving chamber is formed inside the support seat, and a seal ring is installed around the bottom end of the piston; The positioning base has a base surface, a mounting hole in the center of the base surface, and a peripheral wall at the top of the base surface, the base surface and the peripheral wall jointly defining an explosion-proof space, the peripheral wall being fitted into the inside of the connecting end of the pipe for assembly, a side flange extending outward from the outer edge of the base surface, the top edge of the side flange forming a bottom ring peripheral surface that abuts against the bottom edge of the connecting end, and the top edge of the peripheral wall forming an upper annular edge, by which the sealing ring is abutted and positioned correspondingly; The quick release unit is installed at a predetermined position on the bottom of the base of the positioning base, and has a pivot seat installed on the bottom of the base; The loading section cover has a rotating end at one end, pivotally connected to the pivot seat, and a swing end at the other end, which has an engaging groove formed at the swing end, which is movably engaged with the quick release unit. The loading section cover has a receiving surface at its top, which has a loading hole corresponding to the position of the mounting hole. The chemical gas generation module is housed in the loading hole, and an electronic ignition unit is installed on the top of the chemical gas generation module and a launch control unit is installed on the bottom. The electronic ignition unit protrudes upward and is inserted into the loading hole and housed in the explosion-proof space.

[0009] This invention utilizes the continuous loading capability of the chemical gas generation module and the loading section cover, so that when the chemical gas generation module ignites and explodes, gas thrust is generated, pushing up the piston and launching the unmanned aerial vehicle from the launch point. By quickly replenishing the replaceable chemical gas generation module, highly efficient continuous deployment can be achieved. The overall device of the present invention greatly improves upon the drawback of the conventional structure that the power source relies on the standby pressure storage of an air compressor, significantly improving operational efficiency and tactical readiness, and achieving practical advances in terms of enabling quick replenishment of the propulsion source in use. [Brief explanation of the drawings]

[0010] [Figure 1] FIG. [Figure 2] FIG. 2 is an exploded view of the present invention. [Figure 3] FIG. 2 is an exploded view of the present invention; [Figure 4] 2 is an exploded perspective view of the positioning base, quick release unit, loading compartment cover, and rear support seat of the present invention; FIG. [Figure 5] 1 is a top view of a chemical gas generating module according to the present invention; [Figure 6] FIG. 2 is a cross-sectional view showing the device in a supporting state. [Figure 7] 4 is a cross-sectional view of the quick release unit of the present invention rotated and fitted into the engagement groove. FIG. [Figure 8] 4 is a cross-sectional view of the device with the loading compartment cover rotated outward; FIG. [Figure 9] 2 is a cross-sectional view of the chemical gas generation module of the present invention after reloading; FIG. DETAILED DESCRIPTION OF THE INVENTION

[0011] 1 to 9 show a preferred embodiment of the unmanned aerial vehicle launch tube structure according to the present invention. These embodiments are for illustrative purposes only and do not limit the scope of the present invention. The present invention comprises a tube 10, an injection piston unit 30, a positioning base 40, a quick release unit 50, a loading compartment cover 70, a chemical gas generating module 80 and a reinforcing support ring 90. This allows for quick assembly, hermetic sealing, high strength fixing and safe firing functions.

[0012] The tube 10 is hollow and cylindrical, defining a firing space 14 therein. The tube 10 has a connecting end 11 at one end and a launching end 13 at the other end. The connecting end 11 has a plurality of through holes 12 formed on its outer periphery for subsequent screw fastening.

[0013] The firing piston unit 30 is slidably disposed within the firing chamber 14 of the tube 10 and includes a piston 33 . The piston 33 can slide along the axial direction in the launch space 14 of the tube body 10, and a support seat 31 is installed at the top end of the piston 33. A storage chamber 32 is formed inside the support seat 31 to store the unmanned aerial vehicle X. A seal ring 34 is installed around the lower edge of the piston 33, and the piston 33 is installed in the firing space 14 so as to be able to slide along the axial direction of the tube body 10, and performs the firing operation.

[0014] The positioning base 40 is mounted inside the connecting end 11 of the tube 10 , and has a base surface 45 and a peripheral wall 43 . The peripheral wall 43 extends upward around the base surface 45 and defines an explosion-proof space 47 recessed inward. A combination hole 46 is provided in the center of the base surface 45 . An upper annular edge 44 corresponding to the seal ring 34 is installed at the top end of the peripheral wall 43, and when the piston 33 is pushed in and positioned, the seal ring 34 forms an airtight sealing structure, maintaining the air pressure within the explosion-proof space 47 and providing effective kinetic energy to the unmanned aerial vehicle X. A side edge flange 41 extends outward from the outer periphery of the positioning base 40 , and its outer diameter is larger than the opening of the coupling end 11 . The top edge of the side edge flange 41 is formed with a bottom ring circumferential surface 42, which abuts against the bottom edge of the connecting end 11, limiting the insertion depth of the tube body 10 and improving the stability of the structure. On the outer periphery of the peripheral wall 43, threaded holes 48 corresponding to the plurality of through holes 12 respectively are provided.

[0015] In order to realize quick loading and unloading of the chemical gas generating module 80, the present invention provides a quick release unit 50 below the base surface 45 of the positioning base 40. The quick release unit 50 has two symmetrically arranged pivot seats 51, a pivot member 52, a pressure contact member 54, a rotating handle 56 having an eccentric shaft 55, and at least one correspondingly arranged pivot seat 60 having a pivot hole 61. The two pivot seats 51 pivotally connect the pivot member 52, and a rotary shaft pillar 53 is installed in the center of the pivot member 52 in the radial direction, and a pressure contact member 54 is attached to the rotary shaft pillar 53. The end of the rotating shaft post 53 is pivotally attached to an eccentric shaft 55 of a rotating handle 56 .

[0016] The loading section cover 70 is pivotally connected to the pivot seat 60 by a rotating end 71, which has a rotating pivot hole 72, and the rotating pivot hole 72 and the pivot hole 61 are pivotally connected together by a pivot member 62. When the pivot member 62 is fixed by a nut member 63, the loading section cover 70 can rotate and swing back and forth, thereby realizing the opening and closing function. The other end of the loading section cover 70 is a swing end 75 , and an engagement groove 76 is provided below the swing end 75 to engage with the rotary shaft column 53 . When the engagement groove 76 engages with the rotating shaft column 53, the rotating handle 56 rotates clockwise or counterclockwise, and the eccentric shaft 55 presses the pressure-contact member 54, thereby press-contacting and fixing both sides of the engagement groove 76, thereby realizing quick engagement and detachment. A receiving surface 78 is provided above the loading section cover 70, and the receiving surface 78 has a loading hole 74 corresponding to the combination hole 46 of the positioning base 40, and a plurality of combination holes 77, into which a chemical gas generation module 80 can be inserted.

[0017] Chemical gas generation module 80 includes an electronic igniter 81 and a launch control unit 85 with a laterally extending connecting edge 82 disposed therebetween. A plurality of through holes 83 are provided around the connecting edge 82, each corresponding to a corresponding one of the combination holes 77 of the loading section cover 70. A plurality of connecting members 84 are threaded through the respective through holes 83 and the combination holes 77 to be fixed. A gasket 79 is sandwiched between the loading section cover 70 and the chemical gas generating module 80 to enhance adhesion and vibration resistance. The electronic ignition unit 81 is inserted into the combination hole 46 of the positioning base 40 and fitted into the explosion-proof space 47, thereby enabling the concentration of high-pressure gas energy. A launch command receiving circuit 86 is installed inside the launch control unit 85, and can be connected to an external trigger switch (not shown) by wire or wirelessly, controlling the ignition or thrust timing and ensuring launch safety.

[0018] In order to improve the explosion resistance of the entire structure, a reinforcing support ring 90 is fitted around the outer periphery of the connecting end 11 of the pipe body 10 in correspondence with the position of the explosion-proof space 47 . A plurality of connecting holes 93 are provided around the periphery of the reinforcing support ring 90, which correspond to the through holes 12 of the pipe body 10 and the screw holes 48 of the positioning base 40, respectively. A plurality of screw members 94 are used to pass through the connecting holes 93 and the through holes 12 in turn, and then fixed to the screw holes 48, thereby increasing the reinforcing fixing force and improving the integrity of the explosion-resistant structure.

[0019] A support frame 20 is mounted around the outer periphery of the launch end 13 of the tube 10 to provide a stable support mechanism against the ground. The support frame 20 is provided with a fixing ring 21 and two front landing gear frames 26 that extend outward from the fixing ring 21 in a figure-eight shape. Engagement portions 22 each having an engagement hole 23 are provided on both ends of the fixing ring 21, and a screw fastening member 24 and a screw fastening member 25 are combined with the two engagement holes 23. A pivot seat 64 is provided at the bottom of the positioning base 40, and a pivot hole 65 is provided above the pivot seat 64. The pivot seat 64 is connected to a rear support seat S, and the rear support seat S is provided with two pivot lugs S1 corresponding to the pivot seat 64. Each pivot lug S1 has a pivot hole S2 passing therethrough. A pivot member 66 and a nut member 67 are inserted into the pivot hole 65 and each pivot hole S2 and pivotally fixed, thereby allowing the rear support seat S to be pivotally rotated at the rear of the tube body 10, thereby realizing the function of adjusting the launch elevation angle.

[0020] The tube body 10 is made of glass fiber, which not only reduces weight but also increases the reception strength of electronic signals, thereby further improving the sensitivity and stability of the launch control of unmanned aerial vehicles.

[0021] In this invention, the chemical gas generating module 80 and the loading section cover 70 are continuously loaded, and when the chemical gas generating module 80 ignites and explodes, gas thrust is generated, pushing up the piston 33 and launching the unmanned aerial vehicle X from the launch end 13. Rapid replenishment of replaceable chemical gas generation modules 80 allows for efficient continuous deployment. The overall system of the present invention greatly improves upon the drawback of the conventional structure that the power source relies on the standby pressure storage of the air compressor, and can significantly improve operational efficiency and tactical readiness. [Explanation of symbols]

[0022] 10 tube body, 11 joint end, 12 through holes; 13 launch end, 14 launch space, 20 support frame, 21 fixing ring, 22 engagement portion, 23 engagement hole, 24 screw fastening member, 25 Screw fixing member, 26 nose landing gear frame, 30 injection piston unit, 31 Support seat, 32 containment cells, 33 pistons, 34 seal ring, 40 positioning base, 41 side edge flange, 42 Bottom ring surface, 43 Peripheral wall, 44 Superior annular margin, 45 base, 46 hole, 47 Explosion-proof spaces, 48 screw holes, 50 quick release unit, 51 Pivot seat, 52 pivot member, 53 Rotating shaft column, 54 Pressure welding member, 55 Eccentric shaft, 56 rotating handle, 60 Cardinals, 61 pivot hole, 62 pivot member, 63 Nut member, 64 Pivot seat, 65 Pivot hole, 66 pivot member, 67 Nut member, 70 Loading compartment cover, 71 Rotating end, 72 rotating pivot, 74 loading hole, 75 swing end, 76 engagement groove, 77 combination holes, 78 receiving surface, 79 gaskets, 80 Chemical Gas Generation Module, 81 Electronic ignition section, 82 connective edges, 83 through holes, 84 connecting members, 85 Launch Control Unit, 86 Launch command receiving circuit, 90 Reinforcement support ring, 93 binding hole, 94 screw members, S rear support seat, S1 pivot ear, S2 cardinal foramen, X unmanned aerial vehicle.

Claims

1. An unmanned aerial vehicle launch tube structure, comprising: a hollow tube body, an ejection piston unit, a positioning base, a quick release unit, a loading section cover, and a chemical gas generation module; The hollow tube defines a firing space therein, and the tube has a firing end and a connecting end. The injection piston unit is movably installed in the firing space, the injection piston unit has a piston, a support seat is installed at the top end of the piston, a receiving chamber is formed inside the support seat, and a seal ring is installed around the bottom end of the piston; The positioning base has a base surface, a mounting hole in the center of the base surface, and a peripheral wall at the top of the base surface, the base surface and the peripheral wall jointly defining an explosion-proof space, the peripheral wall being fitted into the connecting end of the pipe for assembly, and a side flange extending outward from the outer edge of the base surface, the top edge of the side flange forming a bottom ring peripheral surface that abuts against the bottom edge of the connecting end; The quick release unit is installed at a predetermined position on the bottom of the positioning base, and the quick release unit has at least one pivot seat installed correspondingly; the loading section cover has a rotating end at one end, the rotating end is pivotally connected to the pivot seat, and a swing end at the other end, the swing end is provided with an engagement groove, the engagement groove is movably engaged with the quick release unit, a receiving surface is provided on the top of the loading section cover, and the receiving surface is provided with a loading hole corresponding to the position of the set hole; The chemical gas generating module is accommodated in the loading hole, and an electronic ignition unit is installed at the top of the chemical gas generating module, and a launch control unit is installed at the bottom. The electronic ignition unit protrudes upward and is inserted into the loading hole and accommodated in the explosion-proof space. Characterized by Unmanned aerial vehicle launch tube structure.

2. The unmanned aerial vehicle launch tube structure further includes a support frame; The support frame is provided with a fixing ring and two nose landing gear frames extending outward in a figure-eight shape from the fixing ring, The fixing ring is engaged with the outer edge of the tube at a position close to the firing end, and both ends of the fixing ring are provided with engaging portions having engaging holes, and a screw fastening member and a screw fastening member are combined in the two engaging holes, which are passed through oppositely and screwed together. Characterized by The unmanned aerial vehicle launch tube structure of claim 1 .

3. A pivot seat is further provided at the bottom of the positioning base; The pivot seat is coupled with a rear support seat, and the rear support seat corresponds to the pivot seat and has two pivot lugs, each of which has a pivot hole; The pivot hole and each pivot hole are penetrated by a pivot member and a nut member, and are pivotally connected together. Characterized by The unmanned aerial vehicle launch tube structure of claim 1 .

4. The quick release unit has two pivot seats, a pivot member, a pressure contact member, and a rotary handle having an eccentric shaft, which are installed on the bottom end surface of the positioning base; The two pivot seats are pivotally connected to the pivot member, a rotary shaft is installed radially at the center of the pivot member, the pressure contact member is mounted on the rotary shaft, and the end of the rotary shaft is pivotally connected to the eccentric shaft of the rotary handle; The rotary shaft column is rotatably introduced into the engagement groove of the loading section cover, and the rotary handle is pressed against both sides of the engagement groove, corresponding to the pressure contact member, through the eccentric shaft. Characterized by The unmanned aerial vehicle launch tube structure of claim 1 .

5. a connecting edge is provided at a periphery between the electronic ignition unit of the chemical gas generating module and the launch control unit, the connecting edge extending laterally; The connecting edge is provided with a plurality of through holes, and the receiving surface of the loading section cover is provided with a plurality of mating holes, which respectively correspond to the through holes; A plurality of coupling members are respectively passed through the through holes and the combination holes and are fixed by screws, In addition, a gasket is sandwiched between the joining edge and the receiving surface. Characterized by The unmanned aerial vehicle launch tube structure of claim 1 .

6. A plurality of through holes are provided on the periphery of the coupling end; A plurality of screw holes are provided in the peripheral wall, and correspond to the through holes, respectively; The outer periphery of the pipe is fitted with a reinforcing support ring corresponding to the explosion-proof space position, and a plurality of connecting holes are provided on the periphery of the reinforcing support ring, each corresponding to one of the through holes. A plurality of screw members are passed through the connecting holes and the through holes in order, and then fixed to the screw holes. Characterized by The unmanned aerial vehicle launch tube structure of claim 1 .

7. The launch control unit of the chemical gas generating module further comprises a launch command receiving circuit; The firing command receiving circuit is electrically connected to the trigger switch by wire or wirelessly to receive an external activation signal. Characterized by The unmanned aerial vehicle launch tube structure of claim 1 .

8. The tube is made of glass fiber. Characterized by The unmanned aerial vehicle launch tube structure of claim 1 .

Images