Miniature fuel gas generator for barrel type launching and barrel type launching device

Abstract

The invention relates to the technical field of aircraft power systems, and discloses a barrel type launching miniature fuel gas generator and a barrel type launching device.The barrel type launching miniature fuel gas generator comprises a shell, a main charging column, an igniter and an easily-broken part, a containing cavity is formed in the shell, the shell is provided with a first end wall, and a first vent hole communicated with the containing cavity is formed in the first end wall; the main charging column is limited in the containing cavity, and a through groove extending in the axial direction of the shell is formed in the main charging column. The igniter comprises an explosive blocking shell and an ignition tube, part of the explosive blocking shell is located in the through groove, the breakable piece is arranged between the first end wall and one end of the explosive blocking shell in a sealed mode so as to seal the first vent hole and enable the containing cavity to be a sealed cavity, and the ignition tube is limited in the explosive blocking shell; and a power line of the ignition tube penetrates through the explosive blocking shell and the first end wall in a sealed mode to be connected with an external power source, the ignition tube is used for igniting the main charging column so as to generate fuel gas, and the fuel gas can break through the easily-broken part and then rushes out of the shell from the first vent hole. And the total envelope size is small.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft power systems, and in particular to a micro gas generator for canister-type launching and a canister-type launching device. Background Art

[0002] Small patrol drones, with their advantages of low cost and low detectability, can be widely used to perform tasks in various complex environments such as long-term reconnaissance. They have the advantages of fast take-off, high efficiency and high reliability. Small patrol drones usually adopt ground take-off and electric power systems, which limits their endurance and has certain disadvantages in performing long-distance battlefields. In order to overcome the above defects, the current tendency is to adopt an airborne hanging flight delivery method, that is, a large number of small patrol drones can be hung on large drones, usually using a barrel launch type. In order to consider the mounting capacity of large drones and give full play to the combat effectiveness of patrol drones, it is necessary to carry out a strong constraint on the small size structure performance integration of patrol drones and their launch devices to increase the maximum number of single drones. Among them, the gas generator, as the core power component of the launch device, can provide the required initial flight speed for the patrol drone. However, the existing gas generator is usually large in shaft-to-diameter ratio, which makes the effective volume of the cavity in the launch device small, resulting in space waste and excessive dead weight of the launch device.

[0003] Therefore, there is an urgent need for a micro gas generator for canister launch and a canister launch device to solve the above problems. Summary of the invention

[0004] Based on the above, the purpose of the present invention is to provide a micro gas generator for canister launch and a canister launch device. The total envelope size of the micro gas generator for canister launch is small and the structure is compact. The effective volume of the cavity of the canister launch device is large and the launch overload is small.

[0005] To achieve the above object, the present invention adopts the following technical solutions:

[0006] A micro gas generator for canister launch, comprising a shell, a main charge, an igniter and a breakable part, wherein the shell has a receiving cavity, the shell has a first end wall, a first vent hole connected to the receiving cavity is formed on the first end wall, the main charge is limited in the receiving cavity, and a through groove extending along the axial direction of the shell is formed in the main charge;

[0007] The igniter includes a medicine blocking shell and an ignition tube, wherein a portion of the medicine blocking shell is located in the through groove, the fragile part is sealably arranged between the first end wall and one end of the medicine blocking shell to close the first vent hole and make the accommodating cavity a sealed cavity, the ignition tube is limited in the medicine blocking shell, and the power line of the ignition tube seals and passes through the medicine blocking shell and the first end wall to be connected to an external power source, the ignition tube is used to ignite the main charge column to generate fuel gas, and the fuel gas can break through the fragile part and rush out of the first vent hole to the outside of the outer shell.

[0008] As a preferred solution for a micro gas generator for canister launch, the outer shell includes a shell and an end cover, the first end of the shell has the first end wall, the second end is an open end, and the end cover is detachably and sealably connected to the open end.

[0009] As a preferred solution of a micro gas generator for barrel-type launch, it also includes a front medicine baffle plate, the medicine baffle shell includes a barrel and an end plate, part of the barrel is located in the through groove, the fragile part is sealed between the first end wall and the end plate, a fixed step is formed between the end plate and the outer wall of the barrel wall, the front medicine baffle plate is sleeved outside the barrel and abuts against the fixed step, a rear medicine column is convexly provided in the end cover, and the main medicine column abuts between the front medicine baffle plate and the rear medicine column.

[0010] As a preferred solution of the micro gas generator for canister launch, it also includes a limit plate, which is in an annular structure, is sleeved outside the main charge column, and is sealed and crimped between the end cover and the shell.

[0011] As a preferred solution of a micro gas generator for cylinder-type launching, a sealing film is provided at one end of the cylinder away from the end plate, and the sealing film can be torn under a preset impact force.

[0012] As a preferred solution for a cylinder-type launch micro gas generator, the inner wall of the cylinder is provided with a limiting step surface, the limiting step surface faces the sealing film, and one end of the ignition tube away from the sealing film abuts against the limiting step surface.

[0013] As a preferred solution of a micro gas generator for a cylinder-type launch, it also includes a connecting seat, the outer periphery of which is provided with connecting threads, the connecting threads are used to connect with the launch device, one end of the connecting seat is formed with a mounting groove, a first connecting column is provided in the mounting groove, a second connecting column is protruding from the outer side of the first end wall, and the second connecting column is connected to the first connecting column.

[0014] As a preferred solution of the micro gas generator for canister launch, the shell and / or the connecting seat are made of titanium alloy.

[0015] A barrel-type launching device comprises a launching barrel and a barrel-type launching micro gas generator as described in any one of the above technical solutions located inside the launching barrel.

[0016] The beneficial effects of the present invention are:

[0017] The present invention provides a micro gas generator for canister launch, which realizes maximum radial space utilization of the micro gas generator for canister launch by setting a powder retaining shell and an inner and outer arrangement of a main charge column, reduces axial occupied space and the overall length of the micro gas generator for canister launch, thereby effectively increasing the effective volume of the inner cavity of the launch tube, effectively reducing peak overload and average recoil force of launch, creating a good environment inside the launch tube, that is, reducing the wall thickness requirement of the launch tube structure, and achieving the purpose of lightweight design. Compared with the prior art, the micro gas generator for canister launch has a smaller size, which also enables the launch tube to which it is applied to achieve lightweight.

[0018] The present invention also provides a barrel-type launching device, which includes a launching barrel and the above-mentioned barrel-type launching micro gas generator, has a larger effective volume of the cavity, can achieve lightweight, and thus increase the number of UAVs that can be mounted. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments of the present invention. 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 the contents of the embodiments of the present invention and these drawings without paying any creative work.

[0020] Figure 1 It is a schematic structural diagram of a micro gas generator for canister-type launch provided by an embodiment of the present invention;

[0021] Figure 2 is a cross-sectional view of a micro gas generator for canister-type launch provided by an embodiment of the present invention;

[0022] Figure 3 It is a schematic diagram of the internal structure of the tube-type launching device provided in an embodiment of the present invention.

[0023] In the figure:

[0024] 1. End cap; 2. Shell; 3. Connecting seat; 4. Electric wire; 5. Connecting thread; 6. Drug-blocking shell; 7. Main drug column; 8. Front drug-blocking plate; 9. Rear drug-blocking column; 10. Limiting piece; 11. Launch tube; 12. Piston;

[0025] 100. First air vent; 200. Micro gas generator for cylinder-type launch. DETAILED DESCRIPTION

[0026] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only parts related to the present invention, rather than all structures, are shown in the accompanying drawings.

[0027] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" 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 an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between 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.

[0028] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0029] In the description of the present embodiment, the terms "upper", "lower", "left", "right" and other directions or positional relationships are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of description and simplification of operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation of the present invention. In the description of the present invention, unless otherwise specified, the meaning of "plurality" is two or more. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0030] like Figures 1 to 3As shown, this embodiment provides a barrel-type launch device, which includes a launch barrel 11 and a barrel-type launch micro gas generator 200 located in the launch barrel 11. The barrel-type launch micro gas generator 200 can be detachably mounted on the launch barrel 11, and a cavity is formed in the launch barrel 11. The high-temperature gas generated by the barrel-type launch micro gas generator 200 pushes the piston 12 to move in the cavity, and the piston 12 pushes the UAV in the launch barrel 11 to move, so that the UAV reaches the initial velocity of the launch barrel.

[0031] Specifically, Figure 1 and Figure 2 As shown, the micro gas generator 200 for cylinder-type launch provided in this embodiment includes an outer shell, a main charge column 7, an igniter and a fragile part. The outer shell has a accommodating cavity, the outer shell has a first end wall, and a first air vent 100 connected to the accommodating cavity is opened on the first end wall. The main charge column 7 is limited in the accommodating cavity, and a through groove extending along the axial direction of the outer shell is formed in the main charge column 7; the igniter includes a charge blocking shell 6 and an ignition tube, a part of the charge blocking shell 6 is located in the through groove, the fragile part is sealed between the first end wall and one end of the charge blocking shell 6 to close the first air vent 100 and make the accommodating cavity a sealed cavity, the ignition tube is limited in the charge blocking shell 6, and the ignition tube's power-on wire 4 seals and passes through the charge blocking shell 6 and the first end wall to be connected to an external power supply, the ignition tube is used to ignite the main charge column 7 to generate gas, and the gas can break through the fragile part and rush out of the outer shell from the first air vent 100. By arranging the part of the drug-blocking shell 6 and the main charge column 7 inside and outside, the radial space of the micro gas generator 200 for barrel-type launch is maximized, and the axial occupied space and the overall length of the micro gas generator 200 for barrel-type launch are reduced, so that the effective volume of the inner cavity of the launch barrel 11 can be effectively increased, and the peak overload and the average recoil force of the launch can be effectively reduced, creating a good internal environment of the launch barrel 11, that is, the wall thickness requirements of the launch barrel 11 structure can be reduced, and the purpose of lightweight design can be achieved. Compared with the prior art, the micro gas generator 200 for barrel-type launch has a smaller size, which also enables the launch barrel 11 to which it is applied to achieve lightweight, thereby increasing the number of drones that can be mounted.

[0032] Exemplarily, the total envelope size of the micro gas generator 200 for canister launch is not greater than, the total weight is not greater than 45g, the launch overload within the effective stroke is not greater than 250g, and the maximum pressure in the launch canister 11 during combustion is not greater than 3.5MPa.

[0033] In this embodiment, the main charge column 7 uses a high-energy double-base propellant with a burning rate to reduce the launch time of the patrol UAV. For example, the main components of the propellant are nitrocellulose and nitroglycerin, which have the characteristics of being smokeless, high energy, low pressure index and low burning rate temperature coefficient.

[0034] Furthermore, the cylinder-type launch micro gas generator 200 also includes a connection seat 3, the outer periphery of the connection seat 3 is provided with a connection thread 5, the connection thread 5 is used to connect with the launch tube 11, one end of the connection seat 3 is formed with a mounting groove, a first connection column is provided in the mounting groove, a second connection column is convexly provided on the outer side of the first end wall, and the second connection column is connected to the first connection column, for example, integrally formed or threaded. Under the above structure, the size of the shell in the radial direction is smaller than the size of the connection seat 3 in the radial direction, and there is a gap between the first vent hole 100 and the groove wall of the mounting groove. The cylinder-type launch micro gas generator 200 is installed in the launch tube 11 through the connection thread 5 on the connection seat 3, and the notch of the mounting groove is installed toward the cavity of the launch tube 11 during installation, so that the mounting groove and the cavity form a closed cavity after installation. When ignited and launched, the gas rushes out from the first vent hole 100 to the closed cavity to push the piston 12, thereby pushing the drone in the launch device out of the tube. Preferably, a sealing ring is provided between the connecting seat 3 and the wall of the launching tube 11 to improve the sealing performance of the closed cavity.

[0035] Specifically, the housing includes a shell 2 and an end cover 1, wherein the first end of the shell 2 has the above-mentioned first end wall, the second end is an open end, and the end cover 1 is detachably and sealedly connected to the open end. The detachable end cover 1 facilitates the disassembly and assembly of the main charge column 7 and the igniter inside. The end cover 1 can be optionally but not limited to being connected to the second end of the shell 2 by a thread. Preferably, the outer peripheral wall of the second end of the shell 2 is provided with a first positioning step, and the inner peripheral wall of the end cover 1 is provided with a second positioning step, and the second positioning step and the first positioning step can be positioned and abutted, so that the axial position of the shell 2 and the end cover 1 is relatively stable and reliable.

[0036] Optionally, the shell 2 is cylindrical and suitable for a launch tube 11 for tube-type launch.

[0037] In order to limit and fix the main charge column 7 in the accommodating chamber, the cylinder-type launch micro gas generator 200 also includes a front charge plate 8, the charge-blocking shell 6 includes a cylinder and an end plate, most of the cylinder is located in the through groove, the fragile part is sealed and arranged between the first end wall and the end plate, the ignition tube is limited in the cylinder, a fixed step is formed between the end plate and the outer wall of the cylinder wall, the front charge plate 8 is sleeved outside the cylinder and abuts against the fixed step, a rear charge column 9 is convexly provided in the end cover 1, and the main charge column 7 abuts between the front charge plate 8 and the rear charge column 9. The cylinder provides a limiting and supporting function for the front charge plate 8, so that the position of the front charge plate 8 is fixed, and the space utilization rate is high; the rear charge plate is limited and fixed by the end cover 1, and the structure is simple and reliable, and the structure is highly compact. The main charge column 7 is axially limited by the front charge plate 8 and the rear charge column 9 to prevent the main charge column 7 from slipping in the axial direction and rubbing against other components, thereby ensuring the overall structural compactness and stability of the cylinder-type launch micro gas generator 200 and its reliability in use.

[0038] Preferably, the cylinder-type launch micro gas generator 200 further includes a limit plate 10, which is annular in structure, and is sleeved outside the main charge column 7, and is sealed and crimped between the end cover 1 and the shell 2. The limit plate 10 can effectively limit the radial displacement of the main charge column 7, ensure the stability of the position of the main charge column 7, and facilitate assembly, saving assembly time, and can also play a sealing role on the end cover 1 and the shell 2, improving the compactness of the structure.

[0039] In this embodiment, the outer shell, i.e., the shell 2 and the end cover 1, and / or the connecting seat 3 are made of titanium alloy, such as titanium alloy TC4, with a tensile strength of 895 MPa and a shear strength of 358 MPa, thereby ensuring safety in use.

[0040] Furthermore, a sealing film is provided at one end of the tube away from the end plate. The sealing film may be selected from but not limited to tin foil, and the sealing film can be torn under a preset impact force. The ignition tube includes a semiconductor bridge, explosive and pyrotechnic powder. The semiconductor bridge is connected to an external power source through a power line 4. The semiconductor fire tube bridge is energized to ignite the explosive, the explosive ignites the pyrotechnic powder, the pyrotechnic powder ignites the main charge column 7, and the main charge column 7 burns to produce high-temperature combustion gas. The high-temperature combustion gas breaks through the sealing sheet from the second vent hole, and then rushes out of the shell through the first vent hole 100, that is, it subsequently enters the cavity of the launch device to push the piston 12 to move. Among them, the semiconductor bridge adopts a semiconductor bridge ignition element with a high instantaneous degree, so that the burning time within the effective stroke is not more than 30ms, and it has a fast launch response capability, which effectively reduces the ignition delay time, thereby reducing the launch time of the patrol drone in the launch device.

[0041] Preferably, the inner wall of the cylinder is provided with a limiting step surface, the limiting step surface faces the sealing film, and the end of the ignition tube away from the sealing film abuts against the limiting step surface. The limiting step surface limits the ignition tube, preventing the ignition tube from moving too much in the axial direction in the cylinder.

[0042] The micro gas generator 200 for canister launch provided in this embodiment has a smaller envelope size, higher space utilization, and better structural compactness; the canister launch device has a lighter mass and a larger effective volume of the cavity, which can effectively reduce the average recoil force of the launch, thereby reducing the launch overload and time.

[0043] Note that the above are only preferred embodiments of the present invention and the technical principles used. Those skilled in the art will understand that the present invention is not limited to the specific embodiments described herein, and that various obvious changes, readjustments and substitutions can be made by those skilled in the art without departing from the scope of protection of the present invention. Therefore, although the present invention has been described in more detail through the above embodiments, the present invention is not limited to the above embodiments, and may include more other equivalent embodiments without departing from the concept of the present invention, and the scope of the present invention is determined by the scope of the appended claims.

Claims

1. A micro gas generator for canister launch, characterized in that: The invention comprises a shell, a main charge column, an igniter and a breakable part, wherein the shell has a receiving cavity, the shell has a first end wall, a first vent hole communicating with the receiving cavity is formed on the first end wall, the main charge column is limited in the receiving cavity, and a through groove extending along the axial direction of the shell is formed in the main charge column; The igniter includes a medicine blocking shell and an ignition tube, wherein a portion of the medicine blocking shell is located in the through groove, the fragile part is sealably arranged between the first end wall and one end of the medicine blocking shell to close the first vent hole and make the accommodating cavity a sealed cavity, the ignition tube is limited in the medicine blocking shell, and the power line of the ignition tube seals and passes through the medicine blocking shell and the first end wall to be connected to an external power source, the ignition tube is used to ignite the main charge column to generate fuel gas, and the fuel gas can break through the fragile part and rush out of the first vent hole to the outside of the outer shell.

2. The micro gas generator for canister launch according to claim 1, characterized in that: The housing comprises a shell and an end cover. The first end of the shell has the first end wall, the second end is an open end, and the end cover is detachably and sealingly connected to the open end.

3. The micro gas generator for canister launch according to claim 2, characterized in that: The medicine-blocking shell includes a cylinder and an end plate, a portion of the cylinder is located in the through groove, the fragile component is sealed between the first end wall and the end plate, a fixed step is formed between the end plate and the outer wall of the cylinder, the front medicine-blocking plate is sleeved outside the cylinder and abuts against the fixed step, a rear medicine-blocking column is convexly provided in the end cover, and the main medicine column abuts between the front medicine-blocking plate and the rear medicine-blocking column.

4. The micro gas generator for canister launch according to claim 3, characterized in that: It also includes a limiting plate, which is in an annular structure. The limiting plate is sleeved outside the main charge column and is sealed and crimped between the end cover and the shell.

5. The micro gas generator for canister launch according to claim 1, characterized in that: A sealing film is arranged at one end of the cylinder away from the end plate, and the sealing film can be torn under a preset impact force.

6. The micro gas generator for canister launch according to claim 5, characterized in that: The inner wall of the cylinder is provided with a limiting step surface, the limiting step surface faces the sealing film, and one end of the ignition tube away from the sealing film abuts against the limiting step surface.

7. The micro gas generator for canister launch according to claim 1, characterized in that: It also includes a connecting seat, the outer periphery of which is provided with connecting threads, the connecting threads are used to connect to the launching device, one end of the connecting seat is formed with a mounting groove, a first connecting column is arranged in the mounting groove, a second connecting column is protruded from the outer side of the first end wall, and the second connecting column is connected to the first connecting column.

8. The micro gas generator for canister launch according to claim 7, characterized in that: The shell and / or the connecting seat are made of titanium alloy.

9. A tube-type launching device, characterized in that: The invention comprises a launching tube and a micro gas generator for launching in a tube as claimed in any one of claims 1 to 8, which is located in the launching tube.

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