A two-stage gas generator for catapult launch and its control method

Abstract

A two-stage gas generator for ejection includes a cylinder, a gas generating assembly one, and a gas generating assembly two. The gas generating assembly one includes a first igniter, a first bursting disc, and a throttle valve. The gas generating assembly two includes a second igniter and a second bursting disc. The first igniter includes an electric detonator one for bursting the first bursting disc to make the high-pressure inert gas in the cylinder flow through a third gas guide hole on the throttle valve, the first bursting disc position, a first gas guide hole on the first igniter, and into a working chamber in the launching cylinder. The second igniter includes an electric detonator two for bursting the second bursting disc to cooperate with the first igniter to make the remaining high-pressure inert gas in the cylinder flow through the second bursting disc position and a second gas guide hole on the second igniter, and into the working chamber in the launching cylinder. The present application can meet the initial low overload requirement in the take-off stage of the ejection object and the speed requirement out of the cylinder in the middle and later stages, has a simple structure and light weight, produces clean propelling gas without residues, and does not expose the launching point.

Description

Technical Field

[0001] This invention relates to the field of catapult technology, and more specifically, to a gas generator. Background Technology

[0002] This section provides only background information relevant to this disclosure and is not necessarily prior art.

[0003] In modern warfare, drones, missiles, and other similar products are playing an increasingly important role. The launch methods for drones, missiles, and similar products mainly include high-pressure cold gas ejection, rocket ejection, and artillery firing. The advantages of using high-pressure cold gas ejection are that the launch is unaffected by temperature, the overload curve exhibits good consistency between high and low temperatures at room temperature, low cost, and the gas produced is clean and residue-free.

[0004] The inventors discovered through research that current high-pressure cold gas catapult systems primarily utilize high-pressure gas cylinders directly connected to the launch tube via pipelines, controlled by solenoid valves. However, limitations imposed by pipeline diameter and solenoid valve operating time result in significant losses when supplying gas pressure from the cylinders to the launched product, leading to low efficiency and a complex, heavy device structure. Furthermore, current common catapult systems rely on propellant combustion for propulsion, depending on the propellant type and formulation to ensure the required speed and overload. This method is expensive, and the high-temperature exhaust gases produced during launch easily expose the launch point. Therefore, a novel high-pressure cold gas catapult system is needed to meet the demands of modern warfare. Summary of the Invention

[0005] To address the aforementioned problems in the background art, the present invention provides a two-stage gas generator for catapult launch, which can achieve low cost, light weight, clean and residue-free gas, and output performance curve unaffected by ambient temperature.

[0006] This invention is achieved through the following technical solution: a two-stage gas generator for catapult launch, comprising a cylinder, a first gas generating component for meeting the initial low overload requirements of the launch target during takeoff, and a second gas generating component for cooperating with the first gas generating component to meet the exit velocity requirements of the launch target in the later stages of launch; the first gas generating component and the second gas generating component are respectively connected to both ends of the cylinder; the first gas generating component includes a first igniter, a first rupture disc, and a throttle valve; the first rupture disc is located between the first igniter and the throttle valve, and is connected to the first igniter; the throttle valve is located inside the cylinder and is connected to the first igniter; the first igniter and the throttle valve are respectively provided with a first gas guide hole and a third gas guide hole. The first igniter includes a base and an electric detonating tube installed in the base for detonating a first rupture disc to allow high-pressure inert gas inside the cylinder to flow sequentially through a third vent on a throttle valve, the position of the first rupture disc, and the first vent, finally entering the working chamber inside the launch tube; the second gas generating assembly includes a second igniter and a second rupture disc; the second rupture disc is located inside the cylinder and connected to the second igniter; the second igniter has a second vent; the second igniter includes a base and an electric detonating tube installed in the base for detonating a second rupture disc to cooperate with the first igniter so that the remaining high-pressure inert gas inside the cylinder enters the working chamber inside the launch tube through the position of the second rupture disc and the second vent.

[0007] The area of ​​the first air guide hole is larger than the area of ​​the third air guide hole.

[0008] The area of ​​the second air guide hole is larger than the area of ​​the third air guide hole.

[0009] The first electric detonator is assembled inside the first base, and the assembly and fixation are completed by the flange of the first base; the first rupture disc is located at the first step at the lower end of the electric detonator; the throttle valve is pressed into the tail end of the first base and fixed by interference fit.

[0010] The first rupture disc is fixed to the base by laser welding.

[0011] The second electric detonator is assembled inside the second base, and the assembly and fixation are completed by the flange of the second base; the second rupture disc is located at the first step at the lower end of the second electric detonator.

[0012] The second rupture disc is fixed to the base two by laser welding.

[0013] The distance between the first igniter and the first rupture disc is between 1mm and 5mm.

[0014] The distance between the second igniter and the second rupture disc is between 1mm and 5mm.

[0015] An air inlet is provided on the cylinder, and a high-pressure ball plug is installed at the air inlet.

[0016] In another aspect, the present invention also provides a control method for the above-mentioned two-stage gas generator for catapult launch: the ignition control signal is first sent to the first igniter, and after the first igniter receives the ignition command, the electric detonator is activated. The energy excited by the electric detonator directly acts on the first rupture disc. After the first rupture disc ruptures, the high-pressure inert gas inside the cylinder will flow sequentially through the third gas guide hole on the throttle valve, the position of the first rupture disc, and the first gas guide hole, and finally enter the launch tube. The area of ​​the third gas guide hole is smaller than the area of ​​the first gas guide hole. At this time, the high-pressure gas inside the cylinder is slowly released to meet the low overload requirement of the initial launch target.

[0017] As the working chamber increases, the area of ​​the single third vent is insufficient to support the velocity requirements of the ejected object exiting the tube. The ignition control signal continues to send commands to the second igniter. After receiving the ignition command, the second igniter activates the second electric detonator. The energy generated by the second electric detonator directly acts on the second rupture disc. After the second rupture disc ruptures, the remaining high-pressure inert gas inside the tube will enter the launch tube through the location of the second rupture disc and the second vent. At this time, the first vent and the second vent simultaneously release high-pressure gas into the launch tube. The pressure of the two is superimposed, which can rapidly release the high-pressure gas inside the tube to meet the minimum initial exit velocity requirements of the ejected object in the later stages of the ejection process.

[0018] Compared with the prior art, the beneficial effects of the present invention are as follows: The bipolar gas generator provided by the present invention can meet the initial low overload requirements of the launch phase and the mid-to-late stage exit velocity requirements of the launched object. It has a simple structure, is lightweight, and does not require a complex pipeline system. The generated propellant gas source is clean and residue-free, and will not expose the launch point. Compared with propellant-based pyrotechnic agents, the present invention is filled with inert gas, and the output thrust performance is basically unaffected by the ambient temperature, resulting in excellent performance. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of the structure of the present invention;

[0021] Figure 2 This is a schematic diagram of the first igniter;

[0022] Figure 3 This is a schematic diagram of the second igniter;

[0023] Figure 4The second schematic diagram of the first igniter;

[0024] Figure 5 This is the second schematic diagram of the second igniter. Detailed Implementation

[0025] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0026] Techniques, methods, and equipment known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and equipment should be considered part of the specification.

[0027] like Figure 1 As shown, this embodiment provides a two-stage gas generator for catapult launch, including a cylinder 110, a first gas generating component for meeting the initial low overload requirements of the launch target during takeoff, and a second gas generating component for cooperating with the first gas generating component to meet the exit velocity requirements of the launch target in the later stages of launch. The first and second gas generating components are respectively connected to both ends of the cylinder 110. The first gas generating component includes a first igniter 120, a first rupture disc 130, and a throttle valve 140; the second gas generating component includes a second igniter 150 and a second rupture disc 160.

[0028] The first igniter 120 and the second igniter 150 are respectively connected to both ends of the cylinder 110; the first rupture disc 130 is located between the first igniter 120 and the throttle valve 140, and is connected to the first igniter 120; the throttle valve 140 is located inside the cylinder and is connected to the first igniter; the second rupture disc 160 is located inside the cylinder and is connected to the second igniter 150; the first igniter, the second igniter, and the throttle valve are respectively provided with a first gas guide hole 121, a second gas guide hole 151, and a third gas guide hole 141. After receiving the ignition signal, the first electric igniter 120 and the second electric igniter 150 work independently, each opening its rupture disc, thereby allowing the high-pressure gas inside the cylinder to be introduced into the launch tube through the gas guide hole, for overload launching of drones, missiles, and other products according to regulations.

[0029] like Figure 2As shown, the first igniter 120 includes a base, and an electric detonating tube 11 installed within the base for detonating a first rupture disc 130. This allows high-pressure inert gas inside the tube to flow sequentially through the third vent 141 on the throttle valve 140, the position of the first rupture disc 130, and the first vent 121, ultimately entering the working chamber inside the launch tube. The electric detonating tube 11 is assembled within the base 10 and fixed by the flange of the base 10. The first rupture disc 130 is located at the first step at the lower end of the electric detonating tube 11, 1mm-5mm from the end face of the electric detonating tube. This distance has been verified to ensure the stability of the rupture disc during operation. The first rupture disc 130 is fixed to the base by laser welding or other methods, maintaining good high-pressure sealing to ensure no gas leakage during storage. A complete gas passage is maintained between the first rupture disc 130 and the electric detonator 11, which allows high-pressure gas to be discharged smoothly during operation and finally enter the working chamber through the first gas guide hole 121 to complete the ejection of specific overloads.

[0030] The throttle valve 141 is pressed into the tail end of the base by an interference fit and fixed by laser welding or other methods. A third air guide hole 141 is provided at the center of the throttle valve 141, and the area S3 of the third air guide hole 141 is smaller than the area S1 of the first air guide hole 121.

[0031] like Figure 3 As shown, the second igniter 150 includes a base 2 and an electric detonating tube 2, which is installed in the base 2 and used to detonate a second rupture disc 160 to cooperate with the first igniter. This allows the remaining high-pressure inert gas inside the tube to enter the working chamber inside the launch tube through the position of the second rupture disc 160 and the second gas guide hole 151. The electric detonating tube 2 51 is assembled and fixed in the base 2 50 by the flange of the base 2 50. The second rupture disc 160 is located at the first step at the lower end of the electric detonating tube 2 51, 1mm-5mm away from the end face of the electric detonating tube 2 51. This distance has been verified by testing to ensure the stability of the rupture disc during operation. The second rupture disc 160 is fixed to the base by laser welding or other methods to maintain good high-pressure sealing and ensure that the gas does not leak during storage. A complete gas channel is also maintained between the second rupture disc 160 and the electric detonating tube 2, allowing the high-pressure gas to be smoothly discharged during operation and finally enter the working chamber through the second gas guide hole 151 to complete the ejection of the specific overload.

[0032] like Figure 4 , Figure 5 As shown, the distance D1 between the first rupture disc and the first electric detonator is between 1mm and 5mm. The distance D2 between the second rupture disc and the second electric detonator is between 1mm and 5mm.

[0033] After the first igniter 120 and the second igniter 150 are assembled, they are pressed into the left and right ends of the cylinder 110 by interference fit, and finally fixed by laser welding or other methods to ensure sealing under high pressure.

[0034] An air inlet is also provided on the cylinder 110. After all the parts are assembled, an inert gas of a certain pressure is injected into the air inlet by an air compressor. Finally, the air inlet is sealed by resistance welding using a high-pressure ball plug 170, thus completing the assembly of the two-stage gas generator.

[0035] The bipolar gas generator is installed inside the launch tube. The launch tube is existing technology, containing a piston. The target object (such as a drone or missile) is placed above the piston inside the launch tube, while the bipolar gas generator is located in the working chamber below the piston. After ignition, the bipolar gas generator produces gas that pushes the piston upwards, providing an upward thrust to launch the target object.

[0036] The inventors discovered that catapult-launched missiles and drones typically require thrust and speed that are low in the early stages and high in the later stages. If a pressure vessel of fixed volume has only one vent, according to the pressure release principle, the overload of the launched object will exceed a0 in the initial stage of launch, damaging internal precision electronic components. In the later stages of launch, insufficient thrust will prevent the minimum exit velocity V0 from being reached. Therefore, this invention utilizes vents at both ends. In the initial stage, only a smaller third vent is opened to provide thrust. As the internal pressure of the gas cylinder decreases, a larger second vent is opened after a certain interval. This simultaneous exhaust from two vents of different sizes compensates for the insufficient thrust of a single vent in the later stages, ultimately ensuring that the launch object does not exceed the maximum overload a0 throughout the entire launch process and that the exit velocity is greater than V0.

[0037] During the takeoff phase, the overload requirement for a catapult-launched object is generally slow at first and then fast. The control method of the two-stage gas generator used in this invention for catapult launch is as follows:

[0038] The ignition control signal is first sent to the first igniter 120. After receiving the ignition command, the first igniter 120 activates the electric detonator. The energy generated by the electric detonator directly acts on the first rupture disc 130. After the first rupture disc 130 ruptures, the high-pressure inert gas inside the cylinder 110 will flow sequentially through the third vent 141 on the throttle valve 140, the position of the first rupture disc 130, and the first vent 121, and finally enter the launch tube, pushing the piston upward. Since the area of ​​the third vent 141 is smaller than the area of ​​the first vent 121, the high-pressure gas inside the cylinder 110 is slowly released to meet the low overload requirement of the initial ejection target.

[0039] As the piston moves upward and the working chamber gradually increases, the area of ​​the single third vent 141 is insufficient to support the velocity requirements of the ejected object exiting the tube. At time t1, the ignition control signal continues to send commands to the second igniter 150. After receiving the ignition command, the second igniter 150 activates the second detonator. The energy generated by the second detonator directly acts on the second rupture disc 160. After the second rupture disc 160 ruptures, the remaining high-pressure inert gas inside the tube 110 will enter the launch tube through the position of the second rupture disc 160 and the second vent 151. At this time, the first vent 121 and the second vent 151 simultaneously release high-pressure gas into the launch tube. The pressure of the two is superimposed, which can rapidly release the high-pressure gas in the tube to meet the minimum initial exit velocity V0 required by the ejected object in the later stages. The duration of the pressure superposition is t2.

[0040] The relationship between t1, t2, the area S2 of the second air guide hole, and the area S3 of the third air guide hole is as follows:

[0041]

[0042]

[0043] In the above formula: S2 is the effective area of ​​the second air guide hole, m 2 S3 is the effective area of ​​the third air guide hole, in meters. 2 P1 is the initial filling pressure inside the gas generator, MPa; P2 is the gas pressure inside the gas generator when the second vent is open, MPa; P3 is the equilibrium pressure inside the working chamber when the piston stroke reaches its maximum, MPa; P a The pressure inside the working chamber of the launch tube, in MPa; generally taken as... t1 is the time required for the internal pressure of the generator to decrease from P1 to P2, in milliseconds; t2 is the time required for the internal pressure of the generator to decrease from P2 to P3, in milliseconds; m is the mass of the projectile, in kilograms; A is the cross-sectional area of ​​the piston, in meters. 2 V is the volume of the gas generator, in meters. 3 V0 is the initial velocity of the projectile, in m / s; T s denoted as K, where K is the initial temperature of the gas in the gas generator; a0 is the maximum overload required by the projectile; g is the specific heat ratio, which is 1.66 for monatomic gases, 1.4 for diatomic gases, and approximately 1.33 for gases with three or more atoms.

[0044] The above description is merely an exemplary 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 principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A two-stage gas generator for ejection, characterized by: The application relates to a launching device, which comprises a cylinder (110), a gas generating assembly I for meeting the initial low-overload requirement of a launching object in a take-off stage, and a gas generating assembly II for meeting the speed requirement of the launching object in a middle-late stage. The gas generating assembly I and the gas generating assembly II are respectively connected to two ends of the cylinder (110). The gas generating assembly I comprises a first igniter (120), a first bursting disc (130) and a throttle valve (140); the first bursting disc (130) is located between the first igniter (120) and the throttle valve (140) and is connected with the first igniter (120); the throttle valve (140) is located in the cylinder and is connected with the first igniter (120); the first igniter (120) and the throttle valve (140) are respectively provided with a first air guide hole (121) and a third air guide hole (141). The first igniter (120) comprises a base I and an electric detonating tube I (11) arranged in the base I and used for blasting the first bursting disc (130) so that high-pressure inert gas in the cylinder sequentially flows through the third air guide hole (141) on the throttle valve (140), the position of the first bursting disc (130) and the first air guide hole (121) into a working chamber in the launching cylinder. The gas generating assembly II comprises a second igniter (150) and a second bursting disc (160); the second bursting disc (130) is located in the cylinder (110) and is connected with the second igniter (150); the second igniter (150) is provided with a second air guide hole (151). The second igniter (150) comprises a base II and an electric detonating tube II (51) arranged in the base II and used for blasting the second bursting disc (160) so as to cooperate with the first igniter to make the remaining high-pressure inert gas in the cylinder flow through the position of the second bursting disc (160) and the second air guide hole (151) into the working chamber in the launching cylinder.

2. A two-stage gas generator for ejection according to claim 1, characterized in that: The area of the first air guide hole (121) is larger than that of the third air guide hole (141).

3. A two-stage gas generator for ejection according to claim 1, characterized in that: The electric detonating tube I is assembled in the base I and is fixed by a flange of the base I; the first bursting disc (130) is located at a first step at a lower end of the electric detonating tube I; and the throttle valve (140) is press-fitted into a tail end of the base I and is fixed.

4. A two-stage gas generator for ejection according to claim 3, characterized in that: The first bursting disc (130) is fixed to the base I by laser welding.

5. A two-stage gas generator for ejection according to claim 1, characterized in that: The electric detonating tube II is assembled in the base II and is fixed by a flange of the base II; the second bursting disc (160) is located at a first step at a lower end of the electric detonating tube II.

6. A two-stage gas generator for ejection according to claim 5, characterized in that: The second bursting disc (160) is fixed to the base II by laser welding.

7. A two-stage gas generator for ejection according to claim 1, characterized in that: The distance between the first igniter (120) and the first bursting disc (130) is 1mm-5mm.

8. A two-stage gas generator for ejection according to claim 1, characterized in that: The distance between the second igniter (150) and the second bursting disc (160) is 1mm-5mm.

9. A two-stage gas generator for ejection according to claim 1, characterized in that: The cylinder (110) is provided with a gas charging port, and a high-pressure ball plug is arranged at the gas charging port.

10. A method of controlling a two-stage gas generator for ejection according to any one of claims 1 to 9, characterized in that: The ignition control signal is sent to the first igniter (120) first. After receiving the ignition instruction, the first igniter (120) moves the electric detonator one. The energy excited by the electric detonator one directly acts on the first rupture disc (130). After the first rupture disc (130) breaks, the high-pressure inert gas in the cylinder (110) will flow through the third gas guide hole (141) on the throttle valve (140), the position of the first rupture disc (130), and the first gas guide hole (121) in turn, and finally enter the launch barrel; The area of the third gas guide hole (141) is smaller than that of the first gas guide hole (121). At this time, the high-pressure gas in the cylinder (110) is slowly released to meet the initial demand of the low overload of the ejected object; With the increase of the working chamber, the area of the single third gas guide hole (141) is not enough to support the speed requirement of the ejected object out of the barrel. The ignition control signal continues to send instructions to the second igniter (150). After receiving the ignition instruction, the second igniter (150) moves the electric detonator two. The energy excited by the electric detonator two directly acts on the second rupture disc (160). After the second rupture disc (160) breaks, the remaining high-pressure inert gas in the cylinder (110) will enter the launch barrel through the position of the second rupture disc (160) and the second gas guide hole (151). At this time, the first gas guide hole (121) and the second gas guide hole (151) release high-pressure gas into the launch barrel at the same time. The pressure of the two is in a superimposed state, which can make the high-pressure gas in the cylinder be released quickly to meet the minimum initial launch speed requirement of the ejected object in the middle and late stages.

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