Low-overload telescopic folding wing unmanned aerial vehicle launch canister structure

Abstract

The invention relates to the field of unmanned aerial vehicle launching devices, in particular to a low-overload telescopic folding-wing unmanned aerial vehicle launching cylinder structure which comprises an outer cylinder, a sealing shell, a telescopic assembly and a gas generation assembly, a piston assembly is slidably connected into the outer cylinder, and an inner cylinder is arranged between the piston assembly and the end of the outer cylinder in a sleeving mode; a limiting structure is arranged between the inner wall of the outer cylinder and the outer wall of the inner cylinder, and the folding wing unmanned aerial vehicle is installed in the inner cylinder in a sliding mode; the sealing shell is connected to the end, away from the inner barrel, of the outer barrel and communicates with the end of the outer barrel. One end of the telescopic assembly is connected with the radial direction of the inner cylinder, and the other end of the telescopic assembly is connected with the radial direction of the sealing shell; the gas generation assembly is used for filling high-pressure and high-temperature gas into the sealing shell, the high-pressure and high-temperature gas enters the outer barrel and then drives the piston assembly to slide in the outer barrel, and then the folding wing unmanned aerial vehicle is driven to be launched. According to the invention, the flexibility of the transport length of the launch canister is improved, the gas production rate tends to be more uniform, and the launch overload peak value is reduced.

Description

Technical Field

[0001] The invention relates to the field of unmanned aerial vehicle (UAV) launching devices, and in particular to a low-overload telescopic folding-wing UAV launching tube structure. Background Art

[0002] With the rapid development of drones, vehicle-mounted, ship-mounted and other drones and launch devices are attracting more and more attention from various countries due to their flexibility. The development of launch tubes with compact structure and low launch overload can, on the one hand, increase space utilization and improve the clustering operation capability of vehicle-mounted and ship-mounted drone launches; on the other hand, it can reduce the strength requirements of the aircraft fuselage, making it easier to carry more payloads and improve mission capabilities.

[0003] Existing drone launch tubes mainly use gunpowder, compressed air, and gas generators as power sources. Among them, the launch tube that uses gunpowder as the power source involves the management of pyrotechnics, which has high management costs. Generally, there will be light and smoke during launch, which deviates from the concealment. Using compressed air as the power source generally requires gas production and storage devices, and the system is relatively complex and heavy. Using gas generation as the power source, its gas-producing agent is not pyrotechnics, and the system is simple, which is the current mainstream launch method.

[0004] Conventional gas generator launch tubes generally use single-tube single-stage ignition, that is, the launch tube is a guide tube. When launching, the gas generator quickly releases high-pressure gas after being powered on, pushing the piston and the UAV to accelerate. This launch method generally has a launch overload peak of 150g~200g, which has high requirements on the strength of the aircraft fuselage, and the single-stage ignition gas production rate is poorly uniform, and the acceleration process is poorly economical.

[0005] Therefore, it is necessary to provide a low-overload telescopic folding-wing UAV launch tube structure to solve the above problems. Summary of the invention

[0006] The present invention provides a low-overload telescopic folding-wing UAV launch tube structure to solve the problems that the launch overload peak of the existing launch tube is generally 150g~200g, the aircraft fuselage strength requirement is relatively high, the single-stage ignition gas production rate uniformity is poor, and the acceleration process economy is poor.

[0007] The low-overload telescopic folding-wing UAV launch tube structure of the present invention adopts the following technical solutions, including: An outer cylinder, in which a piston assembly is slidably connected, an inner cylinder is sleeved between the piston assembly and the end of the outer cylinder, and a limiting structure for limiting the inner cylinder from coming out is provided between the inner wall of the outer cylinder and the outer wall of the inner cylinder, wherein the folding-wing drone is slidably installed in the inner cylinder, and the end of the folding-wing drone passes through the end of the inner cylinder to contact the piston assembly; A sealing shell connected to one end of the outer cylinder away from the inner cylinder and communicated with the end of the outer cylinder; A telescopic assembly, which is arranged along the axial direction of the outer cylinder, one end of which is connected to the radial direction of the inner cylinder, and the other end of which is connected to the radial direction of the sealing shell; And a gas generating assembly is used to fill the sealed shell with high-pressure and high-temperature gas. After the high-pressure and high-temperature gas enters the outer tube, it drives the piston assembly to slide in the outer tube, thereby driving the folding-wing UAV to launch.

[0008] Preferably, the piston assembly comprises: The outer piston is an annular piston with a mounting hole in the middle; The inner piston is sleeved in the mounting hole of the outer piston, wherein the inner piston and the inner cylinder have the same inner diameter; and a shear pin, disposed horizontally and connecting the outer piston and the inner piston; The shear pin is used to break when the inner piston is subjected to high-pressure and high-temperature gas pressure, so that the outer piston and the inner piston are separated.

[0009] Preferably, the bottom area of ​​the outer piston is greater than 1 / 9 of the bottom area of ​​the inner piston.

[0010] Preferably, a positioning boss is provided in the mounting hole of the outer piston, and the positioning boss is used to support and position the inner piston.

[0011] Preferably, the gas generating assembly comprises: The first-stage gas generator is used to generate high-temperature and high-pressure gas as a launch power source during launch ignition to drive the piston assembly and the folding-wing UAV to accelerate movement; And a secondary gas generator, which is used to separate the outer piston and the inner piston of the piston assembly when the launch power source of the first-stage gas generator drives the piston assembly to drive the inner tube to the top of the outer tube and cannot move. At this time, the secondary gas generator generates high-temperature and high-pressure gas to drive the inner piston and the folding-wing UAV to accelerate the launch and escape from the inner tube.

[0012] Preferably, a damping plate is provided at one end of the inner cylinder facing the piston assembly.

[0013] Preferably, the gas production mass ratio between the primary gas generator and the secondary gas generator is 1:1 to 1:1.5.

[0014] Preferably, the diameter of the connecting hole between the sealing shell and the outer cylinder is smaller than the inner diameter of the sealing shell.

[0015] Preferably, the length ratio of the inner cylinder to the outer cylinder is 1:1 to 1:1.3.

[0016] Preferably, a sealing ring is provided between the inner cylinder and the outer cylinder.

[0017] The beneficial effects of the present invention are: 1. By setting up an outer tube, an inner tube and a telescopic assembly, the launch tube is adjusted to a fully retracted state through the telescopic assembly during transportation. Before launching, the inner tube is extended from the outer tube and fixed using the telescopic assembly. This lengthens the launch stroke under the same transport size constraint, effectively solving the problem of oversize when the launch tube is mounted on a vehicle or ship, and improving the flexibility of the launch tube's transport length without affecting the launch performance.

[0018] 2. By arranging a first-stage gas generator, a second-stage gas generator and a combined piston assembly (inner piston, outer piston and shear pin) on the sealed shell, when the first-stage gas generator generates power source, the piston assembly has a low movement speed and a small gas production demand. When the second-stage gas generator generates power source, the gas production demand is large. At this time, the inner piston of the piston assembly is separated from the outer piston, and the inner piston moves at a high speed. That is, through the matching setting of the two-stage acceleration stroke and the gas production of the two-stage gas generator, the gas production rate is more matched with the actual situation, the launch overload is more uniform, the launch overload peak can be significantly reduced, the aircraft fuselage strength requirements are reduced, and it is convenient to carry more loads to improve the mission capability.

[0019] 3. According to the different lengths of UAVs, the length of the inner tube extending out of the outer tube is adjusted through the telescopic component to adapt the extension length of the inner tube and improve the compatibility and versatility of the launch tube. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] 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 some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0021] Figure 1 It is a schematic diagram of a low-overload telescopic folding-wing UAV launch tube structure in a retracted state according to the present invention; Figure 2 This is a state diagram of a low-overload telescopic folding-wing UAV launch tube structure portion of the present invention when it is extended; Figure 3 This is a state diagram of a low-overload telescopic folding-wing UAV launch tube structure of the present invention when it is fully extended.

[0022] In the figure: 1. inner cylinder; 2. electric telescopic rod; 3. outer cylinder; 4. sealing ring; 5. damping plate; 6. sealing shell; 7. primary gas generator; 8. outer piston; 9. shear pin; 10. inner piston; 11. secondary gas generator. DETAILED DESCRIPTION

[0023] 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.

[0024] An embodiment of a low-overload telescopic folding-wing UAV launch tube structure of the present invention is as follows: Figure 1 As shown, it includes: an outer tube 3, a telescopic component, a sealed shell and a gas generating component; a piston component is slidably connected in the outer tube 3, an inner tube 1 is sleeved between the piston component and the end of the outer tube 3, a limiting structure for limiting the inner tube 1 from coming out is arranged between the inner wall of the outer tube 3 and the outer wall of the inner tube 1, and a damping plate 5 is arranged at one end of the inner tube 1 facing the piston component, wherein the folding-wing UAV is slidably installed in the inner tube 1, and the end of the folding-wing UAV passes through the end of the inner tube 1 for contacting with the piston component; the sealed shell is connected to the end of the outer tube 3 away from the inner tube 1, and the end face of the sealed shell is a support The support plate has a diameter greater than that of the outer tube 3, the support plate is connected to the end of the outer tube 3, and a connecting hole connecting the outer tube 3 and the sealed shell is provided on the support plate; the telescopic assembly adopts an electric telescopic rod 2, the electric telescopic rod 2 is arranged along the axial direction of the outer tube 3, one end of the electric telescopic rod 2 is connected to a connecting ear arranged radially of the inner tube 1, and the other end of the electric telescopic rod 2 is connected to the support plate of the sealed shell; the gas generating assembly is used to fill the sealed shell with high-pressure and high-temperature gas, and after the high-pressure and high-temperature gas enters the outer tube 3, it drives the piston assembly to slide in the outer tube 3, thereby driving the folding-wing UAV to launch.

[0025] For example, Figure 1 As shown, the limiting structure is a limiting slider arranged radially near the end of the inner cylinder 1, and a limiting step formed by a through hole at the end of the outer cylinder 3 and the inner wall of the outer cylinder 3. The inner cylinder 1 is inserted into the through hole of the outer cylinder 3, and the limiting step and the limiting slider form a limiting structure for limiting the inner cylinder 1 from escaping from the outer cylinder 3. Specifically, a sealing groove is arranged on the outer ring of the limiting slider between the inner cylinder 1 and the outer cylinder 3, and a sealing ring 4 is arranged in the sealing groove.

[0026] For example, Figure 2 As shown, the piston assembly includes: an outer piston 8, an inner piston 10 and a shear pin 9. The outer piston 8 is an annular piston with a mounting hole in the middle; the inner piston 10 is sleeved in the mounting hole of the outer piston 8, wherein the inner piston 10 and the inner cylinder 1 have the same inner diameter, that is, the inner piston 10 slides in the inner cylinder 1; the shear pin 9 is horizontally arranged and connects the outer piston 8 and the inner piston 10; wherein the shear pin 9 is used to break when the inner piston 10 is subjected to high-pressure and high-temperature gas pressure, so as to separate the outer piston 8 and the inner piston 10. Figure 1 and Figure 2As shown, in order to prevent the inner piston 10 from falling off, a positioning boss is provided in the mounting hole of the outer piston 8 , and the positioning boss is used to support and position the inner piston 10 .

[0027] Exemplarily, the gas generating assembly includes: a first-stage gas generator 7 and a second-stage gas generator 11. The first-stage gas generator 7 is used to generate high-temperature and high-pressure gas as a launching power source during launch ignition to drive the piston assembly and the folding-wing UAV to accelerate movement; the second-stage gas generator 11 is used to separate the outer piston 8 and the inner piston 10 of the piston assembly when the launching power source of the first-stage gas generator 7 drives the piston assembly to drive the inner tube 1 to press against the top limiting structure of the outer tube 3 and cannot move. At this time, the inner piston 10 and the folding-wing UAV driven by the high-temperature and high-pressure gas generated by the second-stage gas generator 11 are accelerated to launch and escape from the inner tube 1.

[0028] Specifically, the bottom area of ​​the outer piston 8 is greater than 1 / 9 of the bottom area of ​​the inner piston 8 . In this embodiment, the bottom area of ​​the outer piston 8 is 1.5 times the bottom area of ​​the inner piston 8 .

[0029] Specifically, in this embodiment, the gas production mass ratio of the first-stage gas generator 7 to the second-stage gas generator 11 is 1:1.4.

[0030] Specifically, the diameter of the connecting hole between the sealing shell and the outer cylinder 1 is smaller than the inner diameter of the sealing shell.

[0031] Specifically, in this embodiment, the length ratio of the inner cylinder 1 to the outer cylinder 3 is 1:1.2.

[0032] How it works When in use, the length of the inner tube 1 extending out of the outer tube 3 can be adjusted by controlling the extension and retraction of the electric telescopic rod 2. Figure 1 As shown, in the transport state, the electric telescopic rod 2 is fully retracted, and the inner tube 1 is completely retracted in the outer tube 3. At this time, the tube length of the launch tube structure is the shortest. The outer piston 8 and the inner piston 10 are locked and connected by the shear pin 9 to form a whole.

[0033] like Figure 2 As shown, before launching, the electric telescopic rod 2 is controlled to extend a certain length and fixed as required to meet the launch acceleration stroke requirement. After entering the launch program, the first-stage gas generator 7 is energized to release high-temperature and high-pressure gas, pushing the piston assembly (outer piston 8, shear pin 9, inner piston 10), inner cylinder 1 and the UAV in the inner cylinder 1 to accelerate. When the inner cylinder 1 moves to the end of the outer cylinder 3, the limit step of the outer cylinder 3 and the limit slider of the inner cylinder 1 are in contact, restricting the inner cylinder 1 from moving. At this time, the top of the outer piston 8 hits the damping plate 5 at the bottom of the inner cylinder 1 and is stopped. The shear pin 9 is broken by the force, and the outer piston 8 and the inner piston 10 are separated. At the same time, the second-stage gas generator 11 is energized to further release high-temperature and high-pressure gas. Since the inner diameters of the inner piston 10 and the inner cylinder 1 are the same, as shown in FIG. Figure 3As shown, at this time, the high temperature and high pressure gas will push the inner piston 10 to separate from the outer piston 8, and make the inner piston 10 and the drone in the inner cylinder 1 continue to accelerate in the inner cylinder 1. Until the inner piston 10 moves to the mouth of the inner cylinder 1, the drone exit speed meets the requirements, and the launch is completed.

[0034] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A low-overload telescopic folding-wing UAV launch tube structure, characterized in that: include: An outer cylinder (3) is slidably connected to a piston assembly inside the outer cylinder, an inner cylinder (1) is sleeved between the piston assembly and the end of the outer cylinder (3), and a limiting structure for limiting the inner cylinder (1) from coming out is provided between the inner wall of the outer cylinder (3) and the outer wall of the inner cylinder (1), wherein the folding-wing drone is slidably installed in the inner cylinder (1), and the end of the folding-wing drone passes through the end of the inner cylinder (1) to contact the piston assembly; A sealed housing connected to an end of the outer cylinder (3) facing away from the inner cylinder (1) and communicating with an end of the outer cylinder (3); A telescopic assembly, which is arranged along the axial direction of the outer cylinder (3), one end of which is connected to the radial direction of the inner cylinder (1), and the other end of which is connected to the radial direction of the sealing shell; And a gas generating assembly is used to fill the sealed shell with high-pressure and high-temperature gas, and after the high-pressure and high-temperature gas enters the outer cylinder (3), it drives the piston assembly to slide in the outer cylinder (3), thereby driving the folding-wing UAV to be launched.

2. A low-overload telescopic folding-wing UAV launch tube structure according to claim 1, characterized in that: The piston assembly includes: An outer piston (8), which is an annular piston with a mounting hole in the middle; An inner piston (10) is sleeved in the mounting hole of the outer piston (8), wherein the inner piston (10) and the inner cylinder (1) have the same inner diameter; and a shear pin (9) disposed horizontally and connecting the outer piston (8) and the inner piston (10); The shear pin (9) is used to break when the inner piston (10) is subjected to high-pressure and high-temperature gas pressure, so that the outer piston (8) and the inner piston (10) are separated.

3. The low-overload telescopic folding-wing UAV launch tube structure according to claim 2 is characterized in that: The bottom area of ​​the outer piston (8) is greater than 1 / 9 of the bottom area of ​​the inner piston (8).

4. The low-overload telescopic folding-wing UAV launch tube structure according to claim 2 is characterized in that: A positioning boss is provided in the mounting hole of the outer piston (8), and the positioning boss is used to support and position the inner piston (10).

5. The low-overload telescopic folding-wing UAV launch tube structure according to claim 4 is characterized in that: The gas generating assembly includes: The first-stage gas generator (7) is used to generate high-temperature and high-pressure gas as a launch power source during launch ignition to drive the piston assembly and the folding-wing UAV to accelerate movement; and a secondary gas generator (11) for separating the outer piston (8) and the inner piston (10) of the piston assembly when the launch power source of the primary gas generator (7) drives the piston assembly to drive the inner cylinder (1) to press against the top of the outer cylinder (3) and cannot move. At this time, the secondary gas generator (11) generates high-temperature and high-pressure gas to drive the inner piston (10) and the folding-wing UAV to be launched and released from the inner cylinder (1) at an accelerated speed.

6. The low-overload telescopic folding-wing UAV launch tube structure according to claim 1 is characterized in that: A damping plate (5) is provided at one end of the inner cylinder (1) facing the piston assembly.

7. The low-overload telescopic folding-wing UAV launch tube structure according to claim 1 is characterized in that: The gas production mass ratio between the first-stage gas generator (7) and the second-stage gas generator (11) is 1:1 to 1:1.

5.

8. The low-overload telescopic folding-wing UAV launch tube structure according to claim 1 is characterized in that: The diameter of the connection hole between the sealing shell and the outer cylinder (1) is smaller than the inner diameter of the sealing shell.

9. The low-overload telescopic folding-wing UAV launch tube structure according to claim 1 is characterized in that: The length ratio of the inner tube (1) to the outer tube (3) is 1:1 to 1:1.

3.

10. The low-overload telescopic folding-wing UAV launch tube structure according to claim 1, characterized in that: A sealing ring (4) is provided between the inner cylinder (1) and the outer cylinder (3).

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