CN217029124U - Precooling device for liquid rocket engine and liquid carrier rocket - Google Patents
Precooling device for liquid rocket engine and liquid carrier rocket Download PDFInfo
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- CN217029124U CN217029124U CN202220033690.0U CN202220033690U CN217029124U CN 217029124 U CN217029124 U CN 217029124U CN 202220033690 U CN202220033690 U CN 202220033690U CN 217029124 U CN217029124 U CN 217029124U
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Abstract
The utility model provides a precooling device for a liquid rocket engine and a liquid carrier rocket, which comprise a cooling system arranged on a first substage of the rocket, wherein the cooling system is used for precooling a pump body on a second substage of the rocket and a conveying pipeline between a large storage tank and the pump body; the cooling system is connected with the pump body through a connecting pipeline, a discharge valve is arranged on the connecting pipeline located in the second substage of the rocket and used for controlling the connecting pipeline to be opened or closed, and compared with the prior art, the device has the advantages of reasonable design, safety and reliability, and meanwhile, the reliability of the rocket engine is improved.
Description
Technical Field
The utility model relates to the technical field of rocket engines, in particular to a precooling device of a liquid rocket engine and a liquid carrier rocket.
Background
With the rapid development of the aerospace industry, various technologies related to the rocket field also realize the rapid development.
In particular to a liquid rocket, which is energy-saving and environment-friendly and is convenient to recover and is developed rapidly. The low-temperature liquid rocket engine which is an important component of the liquid rocket is the core of the whole liquid rocket. The low-temperature liquid rocket engine has the advantages that the engine and a supercharging conveying system thereof must be fully precooled before starting due to the low-temperature characteristic, and an internal flow passage of the engine is kept in a low-temperature state. If precooling is not carried out or precooling is insufficient, the temperature of the pipeline and the turbine pump assembly is higher than that of the low-temperature liquid propellant, when the low-temperature liquid propellant passes through the high-temperature pipeline and the turbine pump assembly, the low-temperature liquid propellant can generate violent phase change and enters the pipeline, the pump and other assemblies in a gas phase or gas-liquid two-phase mixed fluid state, pump cavitation is caused, the pressure in the pump and the flow of the low-temperature liquid propellant in the pipeline fluctuate, the working abnormality of the engine is caused, even the starting of the engine is completely failed, and the flying of the rocket is influenced.
It is urgently needed to provide a precooling device for a liquid rocket engine, which has reasonable design, safety and reliability and is a problem to be solved at present.
Disclosure of Invention
The utility model aims to overcome the defects of the prior art and provides a precooling device of a liquid rocket engine and a liquid carrier rocket, which have the advantages of reasonable design, safety and reliability and can improve the reliability of the rocket engine.
The utility model provides a precooling device for a liquid rocket engine, which comprises a cooling system arranged on a first substage of a rocket, wherein the cooling system is used for precooling a pump body on a second substage of the rocket and a conveying pipeline between a large storage tank and the pump body; wherein the content of the first and second substances,
the cooling system is connected with the pump body through a connecting pipeline, a discharge valve is arranged on the connecting pipeline located in the second sub-stage of the rocket and used for controlling the connecting pipeline to be opened or closed.
Further, the cooling system comprises a small storage tank for storing low-temperature liquid propellant, a gas pipeline, a gas cylinder electromagnetic valve and a control system; the two ends of the gas pipeline are respectively connected with the small storage tank and the gas cylinder, the gas cylinder electromagnetic valve is installed on the gas pipeline, and the control system is used for controlling the opening/closing of the gas cylinder electromagnetic valve so as to enable the interior of the gas pipeline to be switched on/off.
Furthermore, one end of the small storage tank is connected with the gas pipeline, and the other end of the small storage tank is connected with the connecting pipeline.
Furthermore, the gas pipeline is a U-shaped conduit structure with two communicated ends and a flow channel arranged inside, and two ends of the U-shaped conduit structure are respectively connected with the small storage tank and one end of the gas cylinder close to the rocket secondary stage.
Further, the control system includes a pressure sensor for measuring a pressure of the gas line.
Further, the connecting line includes a first portion disposed within the rocket first substage and a second portion disposed within the rocket second substage, the first portion and the second portion separating upon separation of the rocket first substage and the rocket second substage.
Further, the center lines of the ports on the side where the first part and the second part are close to each other coincide with each other.
Further, the diameter of the pipeline of the first part close to the second part is smaller than that of the pipeline of the second part close to the first part, the joint of the first part and the second part is connected in a sleeving manner, wherein the outer wall of the first part at the joint is tightly attached to the inner wall of the second part and can freely move along the inner wall of the second part.
Further, the discharge valve is an electromagnetic valve or a pneumatic valve.
The utility model also provides a liquid carrier rocket which is prepared by the precooling device of the liquid rocket engine.
The precooling device for the liquid rocket engine provided by the embodiment of the utility model is composed of a cooling system arranged on a first substage of the rocket, wherein the cooling system is used for precooling a pump body on a second substage of the rocket and a conveying pipeline between a large storage tank and the pump body. When the device is used, the cooling system conveys the low-temperature liquid propellant into the pump body and the conveying pipeline through the connecting pipeline, the whole pump body and the conveying pipeline are cooled, a cold environment is provided for the pump body and the conveying pipeline, the phenomenon that the low-temperature liquid propellant entering the pump body from the large storage tank is gasified due to overhigh temperature of the pump body and the conveying pipeline is avoided, the state conveying pipeline generating gas-phase or gas-liquid two-phase mixed fluid enters the pipeline and the pump body, the pressure in the pump and the flow of the low-temperature liquid propellant in the pipeline fluctuate, and the abnormal work of an engine is caused.
In addition, because the cooling system is arranged in the first substage of the rocket, after the first substage and the second substage of the rocket are separated, the weight of the second substage of the rocket can be reduced, the carrying capacity of the second substage of the rocket can be improved, the number of satellites in the fairing can be increased, and the working efficiency and the economic benefit are improved.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the utility model, as claimed.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the utility model and together with the description, serve to explain the principles of the utility model.
FIG. 1 is a schematic view of the configuration of a rocket first substage, a rocket second substage and a cooling system in an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a joint between a first portion and a second portion in an embodiment of the present invention.
Description of reference numerals:
1 rocket one-sub-stage 2 rocket two-sub-stage
3 pump body 4 large storage tank
5 conveying pipeline 6 connecting pipeline
7-discharge valve 8 small storage tank
9 gas pipeline 10 gas cylinder
11 gas cylinder solenoid valve 12 first part
13 second part
Detailed Description
Reference will now be made in detail to various exemplary embodiments of the utility model, the detailed description should not be construed as limiting the utility model but as a more detailed description of certain aspects, features and embodiments of the utility model.
It will be apparent to those skilled in the art that various modifications and variations can be made in the specific embodiments of the present disclosure without departing from the scope or spirit of the disclosure. Other embodiments will be apparent to those skilled in the art from consideration of the specification. The specification and examples are exemplary only.
One aspect of the utility model provides a liquid rocket engine precooling apparatus. As shown in fig. 1, the device comprises a cooling system arranged in the rocket first substage 1 for precooling the pump bodies 3 on the rocket second substage 2 and the transfer lines 5 between the large tanks 4 and the pump bodies 3. The cooling system is connected with the pump body 3 through a connecting pipeline 6, a discharge valve 7 is arranged on the connecting pipeline 6 in the rocket secondary stage 2, and the discharge valve 7 is used for controlling the opening or closing of the connecting pipeline 6.
Specifically, the precooling device for the liquid rocket engine provided by the embodiment of the utility model is composed of a cooling system arranged on a rocket primary substage 1, and the cooling system is used for precooling a pump body 3 on a rocket secondary substage 2 and a conveying pipeline 5 between a large tank 4 and the pump body 3. During the application, the cooling system conveys the low-temperature liquid propellant to the pump body 3 and the conveying pipeline 5 through the connecting pipeline, the whole pump body 3 and the conveying pipeline 5 are cooled, a cold environment is provided for the pump body 3 and the conveying pipeline 5, the phenomenon that the low-temperature liquid propellant entering the pump body 3 from the large storage tank 4 is gasified due to overhigh temperature of the pump body 3 and the conveying pipeline 5 is avoided, the conveying pipeline 5 in a state of generating gas phase or gas-liquid two-phase mixed fluid enters the pipeline and the pump body 3, the pressure in the pump body 3 and the flow of the low-temperature liquid propellant in the pipeline fluctuate, the abnormal work of an engine is caused, and the whole device ensures the safe and reliable operation of the liquid rocket engine. In addition, because the cooling system is arranged in the first substage of the rocket, when the first substage and the second substage of the rocket are separated, the weight of the second substage of the rocket can be reduced, the carrying capacity of the second substage of the rocket can be improved, the number of satellites in the fairing can be increased, and the working efficiency and the economic benefit are improved.
In the present embodiment, the cooling system includes a small tank 8 for storing a low-temperature liquid propellant, a gas line 9, a gas cylinder 10, a gas cylinder solenoid valve 11, and a control system. Wherein, two ends of the gas pipeline 9 are respectively connected with the small storage tank 8 and the gas bottle 10. For convenience in mounting and dismounting the cylinder solenoid valve 11, for example, the cylinder solenoid valve 11 is mounted on the gas line 9. In order to accurately control the flow rate of the gas in the gas line 9, for example, a control system is used to control the opening/closing of the gas cylinder solenoid valve 11 to turn on/off the inside of the gas line 9.
It is worth mentioning that in order to facilitate the transport of the cryogenic liquid propellant in the small tank 8, for example, one end of the small tank 8 is connected to the gas line 9 and the other end is connected to the connecting line 6. When the low-temperature liquid propellant pump is applied, high-pressure gas in the gas cylinder 10 enters the small storage tank 8 through the gas pipeline 9, so that the pressure in the small storage tank 8 is increased, and in order to ensure the pressure in the small storage tank 8, the low-temperature liquid propellant in the small storage tank 8 enters the pump body 3 and the conveying pipeline 5 through the connecting pipeline 6 and then enters the large storage tank 4. In the whole process, low-temperature liquid propellant can be saved (the low-temperature liquid propellant in the small storage tank enters the large storage tank), the pump body 3 and the conveying pipeline 5 can be effectively cooled, the work of the pump body in the rocket secondary level 2 is facilitated, and the safe starting of the rocket secondary level engine is further facilitated.
It should be noted that, in order to facilitate the gas to enter the small storage tank 8 from the gas cylinder, for example, the gas pipeline 9 is a U-shaped pipe structure with two ends communicated and a flow passage provided inside. In order to allow the gas in the cylinder to rapidly enter the small tank 8, for example, the two ends of the U-shaped conduit structure are connected to the small tank 8 and the cylinder 10, respectively, near the end of the rocket secondary stage 2.
In addition, in order to grasp the internal pressure of the gas line 9 in time and facilitate the supply of the gas, for example, the control system includes a pressure sensor for measuring the pressure of the gas line 9.
As shown in fig. 1 and 2, in order to facilitate the separation of the connecting lines when the first and second substages of the rocket are separated, for example, the connecting lines 6 include a first portion 12 disposed in the first substage 1 of the rocket and a second portion 13 disposed in the second substage 2 of the rocket, and the first portion 12 and the second portion 13 are separated as the first substage 1 of the rocket and the second substage 2 of the rocket are separated.
In addition, in order to ensure the convenience of installation of the first part 12 and the second part 13, for example, the center lines of the ports on the sides of the first part 12 and the second part 13 close to each other coincide with each other.
In the present embodiment, in order to ensure that the first portion 12 and the second portion 13 are separated smoothly, for example, the diameter of the pipeline of the first portion 12 close to the second portion 13 is smaller than the diameter of the pipeline of the second portion 13 close to the first portion 12, and the joint of the first portion 12 and the second portion 13 is connected in a sleeving manner, wherein the outer wall of the first portion 12 at the joint is tightly attached to the inner wall of the second portion 13 and can move freely along the inner wall of the second portion 13.
It should be mentioned in particular that the bleed valve 7 is controlled for convenience, for example, the bleed valve 7 is a solenoid valve or a pneumatic valve.
The utility model also provides a liquid carrier rocket which is prepared by the precooling device of the liquid rocket engine.
The above description is only an exemplary embodiment of the present invention, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principle of the present invention shall fall within the protection scope of the present invention.
Claims (10)
1. A precooling device for a liquid rocket engine is characterized by comprising a cooling system arranged on a first substage of a rocket, wherein the cooling system is used for precooling a pump body on a second substage of the rocket and a conveying pipeline between a large storage tank and the pump body; wherein, the first and the second end of the pipe are connected with each other,
the cooling system is connected with the pump body through a connecting pipeline, a discharge valve is arranged on the connecting pipeline located in the rocket secondary stage, and the discharge valve is used for controlling the connecting pipeline to be opened or closed.
2. The liquid rocket engine precooling apparatus of claim 1, wherein the cooling system comprises a small tank for storing a cryogenic liquid propellant, a gas line, a gas cylinder solenoid valve, and a control system; the gas cylinder electromagnetic valve is installed on the gas pipeline, and the control system is used for controlling the opening/closing of the gas cylinder electromagnetic valve so as to enable the interior of the gas pipeline to be switched on/off.
3. A liquid rocket engine precooling apparatus according to claim 2, wherein one end of the small tank is connected to the gas line, and the other end is connected to the connecting line.
4. The liquid rocket engine precooling apparatus according to claim 2, wherein the gas pipeline is a U-shaped conduit structure with two ends communicated and a flow channel provided therein, and two ends of the U-shaped conduit structure are respectively connected to the small tank and one end of the gas cylinder near the rocket secondary stage.
5. The liquid rocket engine precooling apparatus of claim 2, wherein the control system includes a pressure sensor for measuring the pressure of the gas line.
6. The liquid rocket engine precooling apparatus according to claim 1, wherein the connecting conduit comprises a first section disposed within the rocket first substage and a second section disposed within the rocket second substage, the first section and the second section separating as the rocket first substage and the rocket second substage separate.
7. The liquid rocket engine precooling apparatus of claim 6, wherein port centerlines of the first and second portions on sides adjacent to each other coincide with each other.
8. The liquid rocket engine precooling apparatus according to claim 6, wherein a diameter of a pipe of the first section adjacent to the second section is smaller than a diameter of a pipe of the second section adjacent to the first section, and a joint of the first section and the second section is in a sleeved connection, wherein an outer wall of the first section at the joint is in close contact with an inner wall of the second section and can freely move along the inner wall of the second section.
9. The liquid rocket engine precooling apparatus of claim 1, wherein the bleed valve is a solenoid valve or a pneumatic valve.
10. A liquid launch vehicle comprising a liquid rocket engine precooling apparatus as recited in any one of claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220033690.0U CN217029124U (en) | 2022-01-07 | 2022-01-07 | Precooling device for liquid rocket engine and liquid carrier rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220033690.0U CN217029124U (en) | 2022-01-07 | 2022-01-07 | Precooling device for liquid rocket engine and liquid carrier rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217029124U true CN217029124U (en) | 2022-07-22 |
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ID=82445745
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220033690.0U Active CN217029124U (en) | 2022-01-07 | 2022-01-07 | Precooling device for liquid rocket engine and liquid carrier rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217029124U (en) |
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2022
- 2022-01-07 CN CN202220033690.0U patent/CN217029124U/en active Active
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