A multiple ignition device for a piston reusable liquid rocket engine

Abstract

The utility model is suitable for liquid rocket engine technical field provides a piston type reusable liquid rocket engine multiple ignition device, including liquid cavity shell, liquid cavity shell includes cylinder, liquid cavity head, export device, diaphragm and exhaust device, export device is welded in liquid cavity head, diaphragm is connected with export device screw thread, gas cavity shell, gas cavity shell includes gas cavity connector and gas cavity head, and gas cavity head is welded in the cylinder far away from liquid cavity head, piston assembly, piston assembly includes piston head, in the utility model, external gas source enters gas cavity through gas cavity connector, the pressure of ignition agent stored in liquid cavity rises fast, diaphragm is pressed and is cracked, ignition agent enters downstream pipeline and is transported to rocket engine inner chamber, and finally completes ignition action, and external gas source can be filled with air through gas cavity connector for many times, so that diaphragm is sealed state is many times to be released, and then realizes multiple ignition function, and the operation is simple.

Description

Technical Field

[0001] This utility model belongs to the field of liquid rocket engine technology, and in particular relates to a reusable piston-type liquid rocket engine multiple ignition device. Background Technology

[0002] The rocket engine ignition device is a core component used to ignite the propellant mixture in the combustion chamber (or ignition subsystem) during the engine start-up phase. Its core function is to provide initial energy (high-temperature flame / electric spark, etc.) to trigger the continuous combustion of the propellant and lay the foundation for the engine to generate thrust. It is a crucial factor that directly determines whether the engine can start successfully and whether the start-up is stable. Currently, rocket engine ignition devices generally adopt two structural forms: ignition conduits or diaphragm propellant tanks. However, both have certain limitations. Ignition conduits are single-use products and cannot achieve multiple ignitions, making operation cumbersome. While diaphragm propellant tanks can achieve multiple ignitions, they cannot be disassembled after each test of a liquid rocket engine, leading to increased cleaning difficulties and dead zones inside the diaphragm propellant tank that are not thoroughly cleaned. As a result, residual materials remain in the diaphragm propellant tank, causing these materials to detach during subsequent use and increasing the risk of ignition tests. Therefore, a piston-type reusable liquid rocket engine multiple ignition device is needed to solve these problems. Utility Model Content

[0003] The purpose of this utility model embodiment is to provide a reusable piston-type liquid rocket engine multiple ignition device to solve the problems mentioned in the background art.

[0004] To achieve the above objectives, this utility model provides the following technical solution: A reusable piston-type liquid rocket engine multiple ignition device includes: A liquid cavity housing includes a cylinder, a liquid cavity head, an outlet device, a diaphragm, and an exhaust device. The cylinder is hollow. The non-flange end of the liquid cavity head is welded to the cylinder, forming a liquid cavity with the cylinder. The outlet device is welded to the end of the liquid cavity head away from the cylinder. The diaphragm is threadedly connected to the outlet device. The exhaust device is welded to the cylinder. A gas chamber housing is provided, which is connected to the liquid chamber housing by a thread. The gas chamber housing includes a gas chamber nozzle and a gas chamber end cap. The gas chamber nozzle is welded to the gas chamber end cap and is connected to an external gas source. The gas chamber end cap is welded to the end of the cylinder away from the liquid chamber end cap and forms a gas chamber with the cylinder. A piston assembly is disposed inside the cylinder. The piston assembly includes a piston head, wherein the piston head forms a gas chamber on the side near the gas chamber end cap and a liquid chamber on the side near the liquid chamber end cap.

[0005] In a further technical solution, the piston assembly also includes a pair of seals, which are rubber O-rings. One of the seals is disposed between the piston head and the inner wall of the cylinder, and the other seal is disposed at the connection between the gas chamber housing and the liquid chamber housing.

[0006] In a further technical solution, the piston assembly further includes a guide ring and a pressure cap, wherein the guide ring is threadedly connected to the piston head, and the pressure cap is threadedly connected to the guide ring.

[0007] In a further technical solution, the piston assembly also includes a plug head, which is made of a non-metallic material and is threadedly connected to one end of the piston head by a clamping bolt.

[0008] In a further technical solution, the piston assembly also includes a pair of anti-friction rings, which are made of plastic. One of the anti-friction rings is disposed between the piston head and the guide ring, and the other anti-friction ring is disposed between the guide ring and the pressure cap.

[0009] In a further technical solution, the cylinder is provided with multiple vent holes at intervals, and the vent holes are connected to the liquid chamber.

[0010] Compared with the prior art, the beneficial effects of this utility model are: This invention utilizes a piston assembly housed within a cylinder. The piston assembly includes a piston head, with one side of the piston head near the gas chamber end cap forming a gas chamber, and the other side near the liquid chamber end cap forming a liquid chamber. An external gas source enters the gas chamber through a gas chamber inlet, increasing the pressure within. The high-pressure gas in the gas chamber then exerts an axial thrust on the piston head, pushing it along the cylinder's axial direction towards the liquid chamber end cap. During this movement, the piston head continuously compresses the internal space of the liquid chamber, rapidly increasing the pressure of the ignition agent stored within. When the liquid chamber pressure reaches a rupture threshold, the diaphragm at the outlet device ruptures, releasing the diaphragm's seal. The high-pressure ignition agent then enters the downstream pipeline through the outlet device and is ultimately delivered to the rocket engine's internal cavity, completing the ignition process. After ignition, the diaphragm returns to its sealed state. For multiple ignitions, the external gas source can repeatedly inflate the diaphragm through the gas chamber inlet, allowing for multiple ignition cycles and simplifying the operation. This invention incorporates a plug head made of non-metallic material, which is threadedly connected to one end of the piston head via a clamping bolt. By including the plug head, direct contact between the metal piston head and the metal liquid chamber seal is prevented during piston head movement, thus avoiding wear and the generation of impurities.

[0011] To more clearly illustrate the structural features and effects of this utility model, the following detailed description is provided in conjunction with the accompanying drawings and specific embodiments. Attached Figure Description

[0012] Figure 1 This is a cross-sectional view of the present invention.

[0013] In the diagram: 1. Liquid chamber shell; 11. Cylinder; 111. Exhaust port; 12. Liquid chamber head; 121. Liquid chamber; 13. Outlet device; 14. Diaphragm; 15. Exhaust device; 2. Gas chamber shell; 21. Gas chamber nozzle; 22. Gas chamber head; 221. Gas chamber; 3. Piston assembly; 31. Piston head; 32. Seal; 33. Guide ring; 34. Gland; 35. Plug; 36. Anti-friction ring. Detailed Implementation

[0014] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit the present utility model.

[0015] The specific implementation of this utility model will be described in detail below with reference to specific embodiments.

[0016] like Figure 1 As shown, this utility model embodiment provides a reusable piston-type liquid rocket engine multiple ignition device, comprising: The liquid chamber housing 1 includes a cylinder 11, a liquid chamber head 12, an outlet device 13, a diaphragm 14, and an exhaust device 15. The cylinder 11 is hollow. The non-flange end of the liquid chamber head 12 is welded to the cylinder 11 and forms a liquid chamber 121 with the cylinder 11. The outlet device 13 is welded to the end of the liquid chamber head 12 away from the cylinder 11. The diaphragm 14 is threadedly connected to the outlet device 13. The exhaust device 15 is welded to the cylinder 11. The air chamber housing 2 is connected to the liquid chamber housing 1 by a thread. The air chamber housing 2 includes an air chamber nozzle 21 and an air chamber head 22. The air chamber nozzle 21 is welded to the air chamber head 22 and is connected to an external air source. The air chamber head 22 is welded to the end of the cylinder 11 away from the liquid chamber head 12 and forms an air chamber 221 with the cylinder 11. Piston assembly 3 is disposed inside cylinder 11. Piston assembly 3 includes piston head 31. Piston head 31 has a gas chamber 221 on the side near gas chamber end cap 22 and a liquid chamber 121 on the side near liquid chamber end cap 12. In this embodiment, during use, an external gas source enters the gas chamber 221 through the gas chamber inlet 21, causing the pressure in the gas chamber 221 to increase. Subsequently, the high-pressure gas in the gas chamber 221 generates an axial thrust on the piston head 31, pushing the piston head 31 to move axially along the cylinder 11 towards the liquid chamber head 12. During the movement of the piston head 31, the piston head 31 continuously compresses the internal space of the liquid chamber 121, causing the pressure of the ignition agent stored in the liquid chamber 121 to increase rapidly. When the pressure in the liquid chamber 121 reaches the rupture threshold of the diaphragm 14, the diaphragm 14 at the outlet device 13 is ruptured, thus releasing the sealing state of the diaphragm 14. Then, the high-pressure ignition agent enters the downstream pipeline through the outlet device 13 and is finally delivered to the inner cavity of the rocket engine, ultimately completing the ignition action. After ignition, the diaphragm 14 is reset to the sealed state. When multiple ignitions are required, the external gas source can be filled multiple times through the gas chamber inlet 21 to allow the diaphragm 14 to be unsealed multiple times, thereby achieving the multiple ignition function, which is simple to operate. Specifically, the piston assembly 3 also includes a pair of seals 32, which are rubber O-rings. One seal 32 is disposed on the piston head 31 and the inner wall of the cylinder 11, and the other seal 32 is disposed at the connection between the gas chamber housing 2 and the liquid chamber housing 1. In this embodiment, by setting a pair of seals 32, the gas source in the gas chamber 221 and the ignition agent in the liquid chamber 121 are effectively prevented from crossing the chamber. In addition, the rubber has strong chemical stability, which can effectively avoid the ignition agent from reacting with ordinary O-rings (such as swelling or failure), and ensure long-term sealing reliability. Specifically, the piston assembly 3 also includes a guide ring 33 and a gland 34. The guide ring 33 is threadedly connected to the piston head 31, and the gland 34 is threadedly connected to the guide ring 33. Specifically, the piston assembly 3 also includes a plug head 35, which is made of non-metallic material and is threaded to one end of the piston head 31 by a clamping bolt; In this embodiment, by providing a plug head 35, the metal piston head 31 is prevented from directly contacting the metal liquid chamber seal head 12 when the piston head 31 moves, thus avoiding wear and the generation of impurities. Specifically, the piston assembly 3 also includes a pair of anti-friction rings 36, which are made of plastic. One anti-friction ring 36 is disposed between the piston head 31 and the guide ring 33, and the other anti-friction ring 36 is disposed between the guide ring 33 and the gland 34. In this embodiment, the anti-friction ring 36 guides and lubricates the piston head 31 to prevent tilting during movement, thereby avoiding jamming. Specifically, the cylinder 11 is provided with a plurality of vent holes 111 at intervals, and the vent holes 111 are connected to the liquid chamber 121; In this embodiment, by providing multiple vent holes 111, an external gas source can enter the cylinder 11 through the vent holes 111, which can accommodate manual filling and gas compression filling, and the filling method is diversified.

[0017] The working principle of this utility model is as follows: During use, an external air source enters the air chamber 221 through the air chamber inlet 21, causing the pressure in the air chamber 221 to increase; subsequently, the high-pressure gas in the air chamber 221 generates an axial thrust on the piston head 31, pushing the piston head 31 to move along the cylinder 11 axially and toward the direction close to the liquid chamber end cap 12. During the movement of the piston head 31, the piston head 31 continuously squeezes the internal space of the liquid chamber 121, causing the pressure of the ignition agent stored in the liquid chamber 121 to rise rapidly. When the pressure in the liquid chamber 121 reaches the rupture threshold of the diaphragm 14, the diaphragm 14 at the outlet device 13 is ruptured, thus releasing the sealing state of the diaphragm 14. Then, the high-pressure ignition agent enters the downstream pipeline through the outlet device 13 and is finally delivered to the inner cavity of the rocket engine, thus completing the ignition action. After ignition, the diaphragm 14 returns to the sealed state. When multiple ignitions are required, the external air source can be filled with air multiple times through the air chamber inlet 21 so that the diaphragm 14 can be unsealed multiple times, thereby realizing the multiple ignition function. The operation is simple.

[0018] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A reusable piston-type liquid rocket engine multiple ignition device, characterized in that, include: The liquid chamber housing (1) includes a cylinder (11), a liquid chamber head (12), an outlet device (13), a diaphragm (14), and an exhaust device (15). The cylinder (11) is hollow. The non-flange end of the liquid chamber head (12) is welded to the cylinder (11) and forms a liquid chamber (121) with the cylinder (11). The outlet device (13) is welded to the end of the liquid chamber head (12) away from the cylinder (11). The diaphragm (14) is threaded to the outlet device (13). The exhaust device (15) is welded to the cylinder (11). The air chamber housing (2) is connected to the liquid chamber housing (1) by a thread. The air chamber housing (2) includes an air chamber nozzle (21) and an air chamber head (22). The air chamber nozzle (21) is welded to the air chamber head (22). The air chamber nozzle (21) is connected to an external air source. The air chamber head (22) is welded to the end of the cylinder (11) away from the liquid chamber head (12) and forms an air chamber (221) with the cylinder (11). Piston assembly (3) is disposed inside the cylinder (11). The piston assembly (3) includes a piston head (31). The piston head (31) has a gas chamber (221) on the side near the gas chamber end cap (22) and a liquid chamber (121) on the side near the liquid chamber end cap (12).

2. The reusable piston-type liquid rocket engine multiple ignition device according to claim 1, characterized in that: The piston assembly (3) further includes a pair of seals (32), which are rubber O-rings. One of the seals (32) is disposed on the inner wall of the piston head (31) and the cylinder (11), and the other seal (32) is disposed at the connection between the gas chamber housing (2) and the liquid chamber housing (1) by a thread.

3. The reusable piston-type liquid rocket engine multiple ignition device according to claim 2, characterized in that: The piston assembly (3) further includes a guide ring (33) and a pressure cap (34). The guide ring (33) is threadedly connected to the piston head (31), and the pressure cap (34) is threadedly connected to the guide ring (33).

4. The reusable piston-type liquid rocket engine multiple ignition device according to claim 3, characterized in that: The piston assembly (3) also includes a plug head (35), which is made of non-metallic material and is threaded to one end of the piston head (31) by a clamping bolt.

5. A reusable piston-type liquid rocket engine multiple ignition device according to claim 4, characterized in that: The piston assembly (3) also includes a pair of anti-friction rings (36), which are made of plastic. One of the anti-friction rings (36) is located between the piston head (31) and the guide ring (33), and the other anti-friction ring (36) is located between the guide ring (33) and the pressure cap (34).

6. The reusable piston-type liquid rocket engine multiple ignition device according to claim 4, characterized in that: The cylinder (11) is provided with a plurality of vent holes (111) at intervals, and the vent holes (111) are connected to the liquid cavity (121).

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