A liquid rocket engine multiple ignition device

Abstract

The present invention discloses a multiple ignition device for a liquid rocket engine. Most existing liquid igniters use an ignition tube for ignition. If the engine of such an ignition device is to be started multiple times, the ignition tube must be manually replaced, which is cumbersome to operate and cannot achieve multiple continuous ignitions. The present invention provides a multiple ignition device for a liquid rocket engine, comprising a cylinder assembly, an axial sleeve of a bellows assembly inside the cylinder assembly, a liquid cavity head and an air cavity head respectively provided at both ends of the cylinder assembly, an air cavity formed between one end of the bellows assembly and the air cavity head, a liquid cavity formed between the other end of the bellows assembly and the liquid cavity head, an ignition medium pre-installed in the liquid cavity, and the bellows assembly is squeezed out of the liquid cavity in sequence by filling and discharging high-pressure gas in the air cavity to achieve continuous ignition. The ignition device of the present invention can achieve multiple ignition starts by prefabricating the ignition medium, without replacing the ignition tube when the engine is started multiple times. The operation is simple, and the ignition is safe and reliable.

Description

Technical Field

[0001] The invention belongs to the technical field of liquid rocket engines and relates to a multiple ignition device for a liquid rocket engine. Background Art

[0002] Traditional liquid rocket engine ignition devices mostly use solid powder igniters, torch igniters, squibs, and liquid igniters, among which most liquid igniters are packaged with ignition guide tubes.

[0003] For example, CN106050476A discloses a liquid rocket engine ignition device and ignition method thereof, which includes an igniter base, a front head, and a shell. The igniter base is provided with electric ignition tube interfaces on both sides, and the bottom is connected to the front head. The other end of the front head is connected to the shell. A medicine box is installed in the front head, and a medicine rack is installed in the shell. The medicine rack is provided with a powder column, and a medicine baffle is installed between the bottom of the medicine rack and the bottom of the shell. When in use, an electric ignition tube is installed on the igniter base. When the electric ignition tube receives an electrical command from a control system, it can ignite the black powder in the medicine box. The medicine box outputs a flame, ignites the powder column on the powder rack, and generates high-temperature and high-pressure gas, which provides energy for igniting the liquid propellant. If the ignition operation is not performed immediately, a plug is installed at the electric ignition tube interface, and the electric ignition tube is installed again when ignition is required for ignition.

[0004] If the engine is to be started multiple times using an ignition device of this structure, the electric firing tube, i.e., the ignition conduit, must be replaced manually, which is not only troublesome to operate but also dangerous. Summary of the Invention

[0005] In response to the above problems, the present invention provides a multiple ignition device for a liquid rocket engine, which realizes continuous multiple engine ignition by pre-installing ignition medium in the ignition device. The engine can be started multiple times without replacing the ignition guide tube. The operation is simple and the multiple ignitions are safe and reliable.

[0006] In order to achieve the above object, the technical solution adopted by the present invention is as follows:

[0007] A multiple ignition device for a liquid rocket engine includes a cylinder assembly, wherein a bellows assembly is axially sleeved within the cylinder assembly, and a liquid cavity head and an air cavity head are respectively provided at both ends of the cylinder assembly to seal the bellows assembly within the cylinder assembly. An air cavity is formed between one end of the bellows assembly and the air cavity head, and a liquid cavity is formed between the other end of the bellows assembly and the liquid cavity head. The liquid cavity is pre-loaded with an ignition medium, and the air cavity is filled and discharged by squeezing the bellows assembly to sequentially squeeze the ignition medium out of the liquid cavity to achieve multiple ignitions. Furthermore, the bellows assembly includes a moving head, one end of which is sleeved with a diaphragm assembly. The high-pressure gas squeezes the moving head to move and squeeze the ignition medium out of the diaphragm assembly.

[0008] Furthermore, the air cavity sealing head is connected to an air cavity nozzle, and the liquid cavity sealing head is connected to a liquid cavity nozzle.

[0009] Furthermore, the air cavity nozzle is a T-shaped three-way joint, the high-pressure gas flows in and out directly, and a plug is provided in the side joint of the air cavity nozzle; the liquid cavity nozzle is a T-shaped three-way joint, the ignition medium is extruded laterally, and a plug is provided in the straight-through joint at the outer end of the liquid cavity nozzle.

[0010] Furthermore, the bellows assembly is made of AM350 material.

[0011] Furthermore, the cylinder assembly, liquid cavity head, gas cavity head, moving head, gas cavity nozzle, and liquid cavity nozzle are all made of 07Cr17Ni4Cu4Nb material.

[0012] Furthermore, the plug is made of 304 stainless steel.

[0013] Furthermore, the stopper is made of HPb59-1 material.

[0014] The present invention adopts the above technical solution, which has the following advantages and effects:

[0015] (1) The liquid rocket engine multiple ignition device of the present invention has a simple and reliable structure and can be used repeatedly. When in use, the ignition medium is pre-encapsulated in the liquid cavity to realize the pre-installation of the ignition medium. When the ignition device is working, the gas cavity is filled with high-pressure gas to squeeze the bellows assembly. Under the action of the high-pressure gas, the diaphragm of the diaphragm assembly of the bellows assembly is squeezed and cracked, and the ignition medium is squeezed from the liquid cavity into the downstream pipeline to realize ignition. After the ignition is completed, the high-pressure gas is released and the diaphragm assembly is reset. The high-pressure gas can be filled and discharged multiple times to realize multiple squeezing of the bellows assembly, thereby realizing the multiple ignition function.

[0016] (2) The liquid rocket engine multiple ignition device of the present invention can simultaneously pull out the plugs and plugs of the air cavity nozzle and the liquid cavity nozzle when pre-installing the ignition medium to achieve the packaging of the ignition medium. After the ignition medium is packaged, the air cavity nozzle and the liquid cavity nozzle are sealed by the plug and the plug respectively, and a double-layer seal is achieved during ignition. Even if the bellows assembly leaks, it will not cause the ignition medium packaged inside to leak, thereby ensuring the reliability of the ignition medium sealing and avoiding safety accidents. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a structural schematic diagram of the ignition device of the present invention.

[0018] Among them: 1- bellows assembly, 2- cylinder assembly, 3- liquid cavity head, 4- air cavity head, 5- motion head, 6- plug, 7- air cavity nozzle, 8- liquid cavity nozzle, 9- plug, 10- diaphragm assembly. DETAILED DESCRIPTION

[0019] The following will be described in detail with reference to the accompanying drawings to provide a clearer understanding of the objectives, features and advantages of the present invention. It should be understood that the embodiments shown in the accompanying drawings are not intended to limit the scope of the present invention, but are only intended to illustrate the essential spirit of the technical solution of the present invention.

[0020] The present invention provides a multiple ignition device for a liquid rocket engine, comprising a cylinder assembly, wherein a liquid cavity seal and a gas cavity seal are provided at both ends of the cylinder assembly to form a sealed cavity, a bellows assembly is provided in the cavity, an ignition medium is pre-selected and encapsulated in the cavity, and by filling or releasing high-pressure gas in one end of the cavity, a diaphragm of a diaphragm assembly on the bellows assembly is squeezed and ruptured under the action of the high-pressure gas, and the ignition medium is squeezed from the other end of the cavity into a downstream pipeline to realize ignition. Multiple ignitions can be realized without replacing the ignition guide tube when the engine is started multiple times, the operation is simple, and multiple continuous ignitions are safe and reliable.

[0021] like Figure 1 The present invention provides a multiple ignition device for a liquid rocket engine, comprising a cylinder assembly 2, wherein a bellows assembly 1 is axially sleeved within the cylinder assembly 2. A liquid cavity seal 3 and an air cavity seal 4 are respectively provided at both ends of the cylinder assembly 2 to seal the bellows assembly 1 within the cylinder assembly 2. An air cavity is formed between one end of the bellows assembly 1 and the air cavity seal 4, and a liquid cavity is formed between the other end of the bellows assembly 1 and the liquid cavity seal 3. An ignition medium is pre-installed in the liquid cavity. The gas cavity is filled with high-pressure gas, squeezing the bellows assembly 1 to sequentially squeeze the ignition medium out of the liquid cavity to achieve multiple ignitions.

[0022] Specifically, the cylinder assembly 2 is a circular sleeve with both the front and rear ends connected. The liquid cavity head 3 and the air cavity head 4 are both semi-ellipsoidal shell structures. The semi-ellipsoidal shell makes one side of the liquid cavity head 3 and the air cavity head 4 an arc-shaped concave structure. The liquid cavity head 3 and the air cavity head 4 are respectively sealed with the two ends 2 of the cylinder assembly 2. The bellows assembly 1 is sleeved in the cylinder assembly 2. The gap space formed by the top end of the bellows assembly 1 and the arc-shaped concave surface of the liquid cavity head 3 is used as a liquid cavity to encapsulate the ignition medium. The gap space formed by the bottom end of the bellows assembly 1 and the arc-shaped concave surface of the air cavity head 4 is used as an air cavity for charging and discharging high-pressure gas. Each time the high-pressure gas is charged and discharged, the bellows assembly 1 is squeezed through the air cavity, and the ignition medium encapsulated in the liquid cavity is correspondingly squeezed out of a part of the liquid cavity to achieve one ignition. In this way, the ignition medium is encapsulated once, and the engine can achieve multiple continuous ignition starts.

[0023] Furthermore, the bellows assembly 1 includes a moving head 5, one end of which is sleeved with a diaphragm assembly 10. The high-pressure gas squeezes the moving head 5 to move and act on the diaphragm assembly 10 to squeeze out the ignition medium.

[0024] Specifically, the diaphragm assembly 10 is welded from metal diaphragms to form a cylindrical telescopic cavity structure. A movable head 5 is provided at the bottom of the diaphragm assembly 10. The movable head 5 is a T-shaped cylindrical blind hole cavity. The top of the movable head 5 is an ellipsoidal surface, and the bottom has a flange. The bottom opening faces the side of the air cavity head 4. The bottom of the diaphragm assembly 10 is sleeved on the upper end of the flange of the movable head 5. The diaphragm assembly 10 is formed by folding a number of annular diaphragms to form a foldable and telescopic cylindrical cavity structure. The space between the bottom of the movable head 5 and the air cavity head 4 forms an air cavity, and the space between the upper end cavity of the diaphragm assembly 10 and the liquid cavity head 3 forms a liquid cavity. The high-pressure gas squeezes the moving head 5, which moves axially along the cylindrical assembly 2 to squeeze the diaphragm assembly 10. The diaphragm of the diaphragm assembly 10 shrinks and cracks to squeeze the ignition medium out of the liquid cavity to achieve ignition. After one ignition is completed, the high-pressure gas is released, the moving head 5 returns to its original position, and the diaphragm of the diaphragm assembly 10 is reset to prepare for the next ignition.

[0025] Furthermore, the air cavity sealing head 4 is connected to an air cavity nozzle 7 , and the liquid cavity sealing head 3 is connected to a liquid cavity nozzle 8 .

[0026] Specifically, the top outer end of the air cavity seal 4 is connected to an air cavity nozzle 7, and the top outer end of the liquid cavity seal 3 is connected to a liquid cavity nozzle 8. Air cavity nozzle 7 and liquid cavity nozzle 8 are arranged opposite each other along the axial direction of the cylinder assembly 2 and are coaxial with the axis of the cylinder assembly 2. High-pressure gas enters through one end of the air cavity nozzle 7, and the ignition medium is squeezed out of the other end of the liquid cavity nozzle 8 and enters the downstream ignition pipeline. After ignition is completed, the high-pressure gas is released from the end of the air cavity nozzle 7, and the bellows assembly 1 is reset.

[0027] Furthermore, the air cavity nozzle 7 is a T-shaped three-way joint, the high-pressure gas directly enters and exits the air cavity, and a plug 6 is provided in the side joint of the air cavity nozzle 7; the liquid cavity nozzle 8 is a T-shaped three-way joint, the ignition medium is extruded laterally, and a plug 9 is provided in the outer end straight-through joint of the liquid cavity nozzle 8.

[0028] Specifically, the straight-through joint on one side of the air cavity nozzle 7 is connected to the air cavity head 4, and the high-pressure gas enters from the straight-through joint on the other side of the air cavity nozzle 7 and then directly enters the air cavity. The side joint of the air cavity nozzle 7 is used to encapsulate the ignition medium, and the plug 6 is used to seal the side joint after the ignition medium is encapsulated. The straight-through joint on one side of the liquid cavity nozzle 8 is connected to the liquid cavity head 3, and the straight-through joint on the other side of the liquid cavity nozzle 8 is used to encapsulate the ignition medium. After the ignition medium is encapsulated, the straight-through joint on this side is sealed with a plug 9. The side joint of the liquid cavity nozzle 8 is connected to the downstream ignition pipeline, and the ignition medium is squeezed out from the side joint of the liquid cavity nozzle 8 and then enters the downstream ignition pipeline. After ignition is completed, the high-pressure gas is directly released from one end of the air cavity nozzle 7.

[0029] Furthermore, the bellows assembly 1 is made of high-strength stainless steel AM350. The cylinder assembly 2, liquid cavity head 3, air cavity head 4, moving head 5, air cavity nozzle 7, and liquid cavity nozzle 8 are made of precipitation-hardened stainless steel 07Cr17Ni4Cu4Nb, wherein 07Cr17Ni4Cu4Nb has good solubility in the ignition medium. The plug 6 is made of 304 stainless steel, and the plug 9 is made of HPb59-1. The plug 6 and plug 9 are respectively connected to the air cavity nozzle 7 and liquid cavity nozzle 8 by nuts. To ensure sealing and tightening, the top of the plug 6 and plug 9 has a notch for easy disassembly.

[0030] Before using the ignition device of the present invention, first remove the plug 6 and the stopper 9, fill the ignition medium into the liquid cavity from the straight-through joint end of the liquid cavity nozzle 8, and then seal the plug 6 and the stopper 9. During use, one end of the air cavity nozzle 7 is connected to the high-pressure gas, and one end of the liquid cavity nozzle 8 is connected to the downstream ignition pipeline. The high-pressure gas enters the air cavity from the air cavity nozzle 7 in turn and squeezes the moving head 5 of the bellows assembly 1. The moving head 5 moves and squeezes the diaphragm of the diaphragm assembly, causing it to crack. The ignition medium is squeezed out of the liquid cavity through the liquid cavity nozzle 8 and enters the downstream ignition pipeline. Each time the high-pressure gas is inflated and squeezes the bellows assembly 1 once, an ignition is achieved. During ignition, ignition is achieved by controlling the squeezing time of the high-pressure gas. After each ignition is completed, the high-pressure gas is released and the bellows assembly is reset until all the ignition medium encapsulated inside the device is squeezed out. It can then be filled with ignition medium again and reused.

[0031] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A multiple ignition device for a liquid rocket engine, comprising a cylinder assembly (2), wherein a bellows assembly (1) is axially sleeved in the cylinder assembly (2), and both ends of the cylinder assembly (2) are respectively provided with a liquid cavity head (3) and an air cavity head (4) for sealing the bellows assembly (1) in the cylinder assembly (2), an air cavity is formed between one end of the bellows assembly (1) and the air cavity head (4), and a liquid cavity is formed between the other end of the bellows assembly (1) and the liquid cavity head (3), wherein an ignition medium is pre-installed in the liquid cavity, and an ignition medium is pre-installed in the air cavity by filling and discharging high-pressure gas. The bellows assembly (1) squeezes the ignition medium in the liquid cavity out of the liquid cavity in sequence to achieve multiple ignitions; the bellows assembly (1) includes a moving head (5), one end of the moving head (5) is sleeved with a diaphragm assembly (10), the diaphragm assembly (10) is formed by a plurality of annular diaphragms folded together to form a foldable and telescopic cylindrical cavity structure, the high-pressure gas squeezes the moving head (5) to move and act on the diaphragm assembly (10) to squeeze out the ignition medium, and after one ignition is completed, the high-pressure gas is released, the moving head (5) returns to its original position, and the diaphragm of the diaphragm assembly (10) is reset.

2. A liquid rocket engine multiple ignition device according to claim 1, characterized in that: The air cavity sealing head (4) is connected to an air cavity connection nozzle (7), and the liquid cavity sealing head (3) is connected to a liquid cavity connection nozzle (8).

3. A liquid rocket engine multiple ignition device according to claim 2, characterized in that: The air cavity nozzle (7) is a T-shaped three-way joint, the high-pressure gas directly enters and exits, and a plug (6) is provided in the side joint of the air cavity nozzle (7); the liquid cavity nozzle (8) is a T-shaped three-way joint, the ignition medium is extruded laterally, and a plug (9) is provided in the straight-through joint at the outer end of the liquid cavity nozzle (8).

4. A liquid rocket engine multiple ignition device according to claim 3, characterized in that: The bellows assembly (1) is made of AM350 material.

5. The liquid rocket engine multiple ignition device according to claim 3, characterized in that: The cylindrical component (2), liquid cavity sealing head (3), air cavity sealing head (4), moving sealing head (5), air cavity connecting nozzle (7) and liquid cavity connecting nozzle (8) are all made of 07Cr17Ni4Cu4Nb material.

6. The liquid rocket engine multiple ignition device according to claim 3, characterized in that: The plug (6) is made of 304 stainless steel; the stopper (9) is made of HPb59-1.

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