Gas oxygen methane propelling system and liquid rocket

Abstract

The utility model discloses a gaseous oxygen methane propulsion system and liquid rocket, including a plurality of sub-propulsion systems, each sub-propulsion system includes methane pipeline structure, oxygen pipeline structure, torch igniter and thrust chamber, methane pipeline structure one end is connected with methane storage tank, the other end is divided into two branch, one branch is connected with thrust chamber, and the other branch is connected with the torch igniter. The other branch is connected with a torch igniter; a methane main valve is arranged on a main pipeline where the methane pipeline structure is connected with the methane storage tank, and a methane auxiliary valve is arranged on a branch pipeline where the methane pipeline structure is connected with the torch igniter; one end of the oxygen pipeline structure is connected with the oxygen storage tank, the other end of the oxygen pipeline structure is divided into two branches, one branch is connected with the thrust chamber, and the other branch is connected with the torch igniter; an oxygen main valve is arranged on a main pipeline for connecting the oxygen pipeline structure and the oxygen storage tank; and an oxygen auxiliary valve is arranged on a branch pipeline for connecting the oxygen pipeline structure and the torch igniter. According to the system, thrust for attitude adjustment can be provided for the rocket by using oxygen and methane in the storage tank.

Description

Technical Field

[0001] The utility model relates to the field of launch vehicles, in particular to an oxygen-methane propulsion system and a liquid rocket. Background Art

[0002] With the rapid development of the aerospace industry, various technologies involved in the field of rockets have also achieved rapid progress, especially the liquid oxygen-methane engine technology has gradually matured in recent years. However, during the flight of the rocket, the evaporation of the liquid propellant in the tank will cause the pressure in the tank to increase. In order to ensure the safety of the tank, a safety valve needs to be set. When the tank pressure exceeds the set value, the tank safety valve opens to discharge the excess tank evaporation gas, resulting in a waste of propellant. As the rocket flies, the propellant continues to be consumed, the volume of the air pillow in the tank becomes larger and larger, and the tank gas available during the entire flight process has a considerable volume and mass. Therefore, the oxygen and methane evaporated from the tank are reused to provide bottom thrust or gliding thrust during flight, which can improve the utilization rate of the propellant. Without the need to carry additional oxygen cylinders and methane cylinders, the weight of the entire rocket can be reduced, and the rocket carrying efficiency can also be improved.

[0003] Therefore, there is an urgent need to provide a propulsion system that can make full use of the evaporated oxygen and methane in the tank to provide gliding thrust for the rocket. While improving the utilization rate of the propellant, it can also reduce the weight of the rocket body and improve the rocket's carrying efficiency. Summary of the invention

[0004] The purpose of the utility model is to overcome the deficiencies of the prior art and to provide a gas-oxygen-methane propulsion system that can fully utilize the gas-oxygen-methane evaporated in the tank to provide a gliding thrust for the rocket, thereby improving the utilization rate of the propellant and reducing the weight of the rocket body, thereby improving the rocket's carrying efficiency.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: an oxygen-methane propulsion system, comprising a plurality of sub-propulsion systems arranged on the surface of each rocket sub-stage along the circumference of the rocket sub-stage and used to adjust the aerial posture of the rocket sub-stage, each of the sub-propulsion systems at least comprising a methane pipeline structure, an oxygen pipeline structure, a torch igniter and a thrust chamber, wherein:

[0006] One end of the methane pipeline structure is connected to the methane tank on the rocket sub-stage, and the other end is divided into two branches, one branch is connected to the thrust chamber, and the other branch is connected to the torch igniter; wherein, a methane main valve is provided on the main pipeline connecting the methane pipeline structure to the methane tank, and a methane auxiliary valve is provided on the branch pipeline connecting the methane pipeline structure to the torch igniter;

[0007] One end of the oxygen pipeline structure is connected to the oxygen tank on the rocket sub-stage, and the other end is divided into two branches, one branch is connected to the thrust chamber, and the other branch is connected to the torch igniter; wherein, the main pipeline connecting the oxygen pipeline structure to the oxygen tank is provided with an oxygen main valve, and the branch pipeline connecting the oxygen pipeline structure to the torch igniter is provided with an oxygen auxiliary valve;

[0008] The torch igniter is used to generate an electric spark to burn the oxygen gas and the methane gas.

[0009] Furthermore, the methane pipeline structure comprises a methane main pipeline, a first methane branch and a second methane branch, wherein:

[0010] The input end of the methane main line is connected to the top of the methane tank, and the output end is connected to the input ends of the first methane branch line and the second methane branch line respectively.

[0011] The output of the first methane branch is connected to the bottom of the thrust chamber, and the output end of the second methane branch is connected to the torch igniter.

[0012] Furthermore, the methane secondary valve is arranged on the second methane branch.

[0013] Furthermore, the oxygen pipeline structure comprises an oxygen main pipeline, a first oxygen branch and a second oxygen branch, wherein:

[0014] The input end of the oxygen main line is connected to the top of the oxygen tank, and the output end is connected to the input ends of the first oxygen branch and the second oxygen branch. The output end of the first oxygen branch is connected to the top of the thrust chamber, and the output end of the second oxygen branch is connected to the torch igniter.

[0015] Furthermore, the oxygen secondary valve is arranged on the second oxygen branch line.

[0016] Furthermore, the oxygen secondary valve is a one-way valve structure.

[0017] Furthermore, a blowing device is provided, and the blowing device is used to blow out the oxygen head cavity of the thrust chamber through the pipeline at the connection position between the oxygen pipeline structure and the torch igniter.

[0018] Furthermore, the blow-off device comprises a high-pressure gas cylinder and a blow-off pipeline, the gas outlet of the high-pressure gas cylinder is connected to the inlet of the blow-off pipeline, and the outlet of the blow-off pipeline is connected to the pipeline of the oxygen pipeline structure and the torch igniter connection part.

[0019] Furthermore, the methane tank and the oxygen tank are cylindrical in shape with arc-shaped raised cover plates at both ends, and the arc-shaped raised cover plates are convex upwards away from the bottom relative to the bottom.

[0020] The utility model also provides a liquid rocket, comprising any one of the above-mentioned oxygen-methane propulsion systems.

[0021] Compared with the prior art, the utility model has at least one of the following beneficial effects:

[0022] The oxygen-methane propulsion system includes a plurality of sub-propulsion systems, each of which is composed of at least a methane tank, a methane pipeline structure, an oxygen tank, an oxygen pipeline structure, a torch igniter and a thrust chamber.

[0023] A methane main valve is provided on the main pipe connecting the methane pipeline structure and the methane tank, and an oxygen main valve is provided on the main pipe connecting the oxygen pipeline structure and the oxygen tank. The methane main valve and the oxygen main valve are provided to facilitate the control of the flow of gas methane and gas oxygen output from the methane tank and the oxygen tank, and the flow of gas oxygen and gas methane is adjusted by adjusting the valve opening, so that the thrust chamber generates different thrusts, thereby quickly adjusting the flight attitude of each sub-stage of the rocket.

[0024] In addition, a methane auxiliary valve is provided on the branch connecting the methane pipeline structure and the flare igniter, and an oxygen auxiliary valve is provided on the branch connecting the oxygen pipeline structure and the flare igniter. The setting of the oxygen auxiliary valve and the methane auxiliary valve can control the flow of gas oxygen and gas methane passing through their respective branches, while allowing a small amount of gas oxygen and gas methane to burn quickly with the cooperation of the flare igniter, thereby igniting a large amount of gas methane and gas oxygen entering the thrust chamber from the methane tank and the oxygen tank through the main pipeline.

[0025] The propulsion system of the present application can make full use of the evaporated oxygen and methane in the tank to provide thrust for the rocket's attitude adjustment. While improving the utilization rate of the propellant, it can reduce the installation of gas cylinder equipment, thereby reducing the weight of the rocket and improving the rocket's carrying efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a simplified structural diagram of the propulsion system and rocket sub-stage of the utility model;

[0027] Figure 2 It is a simplified structural diagram of the propulsion system of the utility model.

[0028] Description of reference numerals:

[0029] 1 rocket stage 2 methane tank

[0030] 3Methane pipeline structure 4Oxygen storage tank

[0031] 5 oxygen pipeline structure 6 torch igniter

[0032] 7 thrust chamber 8 methane main valve

[0033] 9Methane auxiliary valve 10Oxygen main valve

[0034] 11 oxygen auxiliary valve 12 blow-off device DETAILED DESCRIPTION

[0035] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention more clearly understood, the spirit of the contents disclosed in the present invention will be clearly explained with the accompanying drawings and detailed descriptions below. After understanding the embodiments of the contents of the present invention, any technician in the relevant technical field can change and modify the contents of the present invention according to the techniques taught by the contents of the present invention without departing from the spirit and scope of the contents of the present invention.

[0036] The exemplary embodiments and descriptions of the present invention are used to explain the present invention, but are not intended to limit the present invention. In addition, the same or similar reference numerals used in the drawings and embodiments are used to represent the same or similar parts.

[0037] The terms “first”, “second”, etc. used in this document do not particularly refer to an order or sequence, nor are they used to limit the present invention. They are only used to distinguish elements or operations described with the same technical terms.

[0038] The directional terms used in this document, such as up, down, left, right, front or back, etc., are only used to refer to the directions of the drawings. Therefore, the directional terms used are used to illustrate and not to limit the present invention.

[0039] The words “include,” “including,” “have,” “contain,” etc. used in this document are open-ended terms, meaning including but not limited to.

[0040] As used herein, "and / or" includes any or all combinations of the items described.

[0041] The terms "substantially" and "approximately" used herein are used to modify any quantity or error that may vary slightly, but these slight changes or errors do not change their essence. Generally speaking, the range of slight changes or errors modified by such terms may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments, or other values. Those skilled in the art should understand that the aforementioned values ​​can be adjusted according to actual needs and are not limited thereto.

[0042] Certain terms used to describe the present application are discussed below or elsewhere in this specification to provide additional guidance to those skilled in the art regarding the description of the present application.

[0043] See also Figure 1 and Figure 2As shown, an embodiment of the utility model provides a gas-oxygen-methane propulsion system, which can fully utilize the gas-oxygen-methane evaporated in the tank to provide thrust for attitude adjustment of the rocket. While improving the utilization rate of the propellant, it can reduce the installation of equipment and improve the rocket's carrying efficiency.

[0044] Let’s take the attitude adjustment of the second stage of a liquid rocket as an example.

[0045] In order to achieve the above-mentioned purpose, the utility model provides the following technical solutions: a gas oxygen methane propulsion system is provided, comprising a plurality of sub-propulsion systems arranged on the surface of the rocket sub-stage 1 (liquid rocket second sub-stage) along the circumference of each rocket sub-stage and used to adjust the aerial posture of the rocket sub-stage 1. Each sub-propulsion system at least comprises a methane pipeline structure 3, an oxygen pipeline structure 5, a torch igniter 6 and a thrust chamber 7. Among them, one end of the methane pipeline structure 3 is connected to the methane tank 2 on the rocket sub-stage, and the other end is divided into two branches, one branch is connected to the thrust chamber 7, and the other branch is connected to the torch igniter 6. A methane main valve 8 is provided on the main pipeline connecting the methane pipeline structure 3 and the methane tank 2, and a methane sub-valve 9 is provided on the branch connecting the methane pipeline structure 3 and the torch igniter 6.

[0046] One end of the oxygen pipeline structure 5 is connected to the oxygen storage tank 4 on the rocket sub-stage, and the other end is divided into two branches, one branch is connected to the thrust chamber 7, and the other branch is connected to the torch igniter 6; wherein, the main line connecting the oxygen pipeline structure 5 and the oxygen storage tank 4 is provided with an oxygen main valve 10, and the branch line connecting the oxygen pipeline structure 5 and the torch igniter 6 is provided with an oxygen auxiliary valve 11.

[0047] The torch igniter 6 is used to generate an electric spark to burn the oxygen gas and the methane gas.

[0048] Specifically, the oxygen-methane propulsion system includes a plurality of sub-propulsion systems, each of which is composed of at least a methane pipeline structure 3, an oxygen pipeline structure 5, a flare igniter 6 and a thrust chamber 7. A methane main valve 8 is provided on the main pipeline connecting the methane pipeline structure 3 and the methane tank 2, and an oxygen main valve 10 is provided on the main pipeline connecting the oxygen pipeline structure 5 and the oxygen tank 4.

[0049] The methane main valve 8 and the oxygen main valve 10 are arranged to control the flow rates of methane and oxygen gas output from the methane tank and the oxygen tank. For example, the flow rates of oxygen and methane gas can be adjusted by adjusting the valve opening, thereby adjusting the thrust chamber 7 to produce different thrusts, so as to better adjust the flight attitude of the rocket sub-stage 1.

[0050] A methane auxiliary valve 9 is provided on the branch line connecting the methane pipeline structure 3 and the torch igniter 6; an oxygen auxiliary valve 11 is provided on the branch line connecting the oxygen pipeline structure 5 and the torch igniter 6. The setting of the oxygen auxiliary valve 11 and the methane auxiliary valve 9 can control the flow of oxygen and methane gas passing through their respective branches, and can also make a small amount of oxygen and methane gas burn quickly with the cooperation of the torch igniter, so as to facilitate the ignition of a large amount of methane and oxygen gas entering the thrust chamber from the methane tank and the oxygen tank through the main line.

[0051] When used, the gas methane and gas oxygen passing through the methane auxiliary valve and the oxygen auxiliary valve first reach the torch igniter 6 through their respective branches, and the torch igniter is started to generate electric sparks to burn the gas methane and gas oxygen. The gas methane and gas oxygen passing through the methane main valve and the oxygen main valve enter the thrust chamber through the pipeline and burn together with the gas methane and gas oxygen ignited by the torch igniter 6. In this solution, by controlling the opening of the methane main valve 8, the oxygen main valve 10, the oxygen auxiliary valve 11 and the methane auxiliary valve 9, the thrust chamber generates different thrusts, and then the attitude of the rocket sub-stage can be adjusted according to actual conditions.

[0052] The propulsion system of the present application can make full use of the evaporated gas oxygen methane in the tank to provide thrust for the rocket to adjust its attitude. While improving the utilization rate of the propellant, it can reduce the installation of gas cylinder equipment and improve the rocket carrying efficiency. In this embodiment, the methane pipeline structure 3 includes a methane main line, a first methane branch and a second methane branch. In order to facilitate the output of gas methane, for example, the input end of the methane main line is connected to the top of the methane tank (the space where the liquid methane is heated and gasified and located at the top of the methane tank), and the output end is connected to the input end of the first methane branch and the second methane branch respectively. In order to facilitate the cooling of the surface of the thrust chamber 7 and avoid deformation of the thrust chamber 7 due to high temperature, for example, the output end of the first methane branch is connected to the bottom of the thrust chamber (a plurality of groove channels are provided to connect the bottom and top of the thrust chamber) (the gas methane of the first methane branch enters the top of the thrust chamber from the plurality of groove channels at the bottom of the thrust chamber), and the output end of the second methane branch is connected to the torch igniter.

[0053] It should be noted that, in order to quickly adjust the flow rate of gaseous methane in the second methane branch, for example, the methane auxiliary valve 9 is arranged on the second methane branch.

[0054] In addition, the oxygen pipeline structure 5 includes an oxygen main pipeline, a first oxygen branch and a second oxygen branch. In order to facilitate the output of gas oxygen, for example, the input end of the oxygen main pipeline is connected to the top of the oxygen tank (the liquid oxygen is heated and gasified in the space above the oxygen tank), and the output end is connected to the input end of the first oxygen branch and the second oxygen branch. In order to facilitate the combustion of gas oxygen and gas methane, for example, the output end of the first oxygen branch is connected to the top of the thrust chamber 7. In addition, the output end of the second oxygen branch is connected to the torch igniter 6. It should be noted that in order to quickly adjust the flow of gas oxygen in the second oxygen branch, for example, the oxygen auxiliary valve is set on the second oxygen branch. In this example, in order to prevent gas oxygen from flowing back in the second oxygen branch, for example, the oxygen auxiliary valve 11 is a one-way valve structure.

[0055] In this embodiment, the propulsion system is also provided with a blowing device 12, which is used to blow out the oxygen head cavity of the thrust chamber through the pipeline at the connection position between the oxygen pipeline structure 5 and the torch igniter 6, so that the oxygen head cavity is blown dry, which is beneficial to the safe ignition of the torch igniter 6.

[0056] Specifically, the purge device 12 includes a high-pressure gas cylinder and a purge pipeline, the gas outlet of the high-pressure gas cylinder is connected to the inlet of the purge pipeline, and the outlet of the purge pipeline is connected to the pipeline of the connecting part of the oxygen pipeline structure and the torch igniter 6.

[0057] In addition, in order to ensure the structural stability of the methane storage tank 2 and the oxygen storage tank 4 while facilitating the output of gaseous oxygen and gaseous methane, for example, the methane storage tank 2 and the oxygen storage tank 4 are cylindrical in shape with arc-shaped raised cover plates at both ends, wherein the arc-shaped raised cover plates are structures that bulge upward away from the bottom relative to the bottom.

[0058] The utility model also provides a liquid rocket, comprising any one of the above-mentioned oxygen-methane propulsion systems.

[0059] The above embodiments can be combined with each other and have corresponding technical effects.

[0060] The above description is only an illustrative specific implementation of the present invention. Without departing from the concept and principle of the present invention, any equivalent changes and modifications made by those skilled in the art should fall within the scope of protection of the present invention.

Claims

1. An oxygen-methane propulsion system, characterized in that: The invention comprises a plurality of sub-propulsion systems which are arranged on the surface of each rocket sub-stage along the circumference of the rocket sub-stage and are used to adjust the aerial attitude of the rocket sub-stage, each of the sub-propulsion systems at least comprising a methane pipeline structure, an oxygen pipeline structure, a torch igniter and a thrust chamber, One end of the methane pipeline structure is connected to the methane tank on the rocket sub-stage, and the other end is divided into two branches, one branch is connected to the thrust chamber, and the other branch is connected to the torch igniter; a methane main valve is provided on the main pipeline connecting the methane pipeline structure to the methane tank, and a methane auxiliary valve is provided on the branch connecting the methane pipeline structure to the torch igniter; One end of the oxygen pipeline structure is connected to the oxygen tank on the rocket sub-stage, and the other end is divided into two branches, one branch is connected to the thrust chamber, and the other branch is connected to the torch igniter; wherein, the main pipeline connecting the oxygen pipeline structure to the oxygen tank is provided with an oxygen main valve, and the branch pipeline connecting the oxygen pipeline structure to the torch igniter is provided with an oxygen auxiliary valve; The torch igniter is used to generate an electric spark to burn the oxygen gas and the methane gas.

2. The oxygen-methane propulsion system according to claim 1, characterized in that: The methane pipeline structure comprises a methane main pipeline, a first methane branch pipeline and a second methane branch pipeline, wherein: The input end of the methane main line is connected to the top of the methane tank, and the output end is connected to the input ends of the first methane branch line and the second methane branch line respectively. The output of the first methane branch is connected to the bottom of the thrust chamber, and the output end of the second methane branch is connected to the torch igniter.

3. The oxygen-methane propulsion system according to claim 2, characterized in that: The methane sub-valve is arranged on the second methane branch line.

4. The oxygen-methane propulsion system according to claim 1, characterized in that: The oxygen pipeline structure comprises an oxygen main pipeline, a first oxygen branch and a second oxygen branch, wherein: The input end of the oxygen main line is connected to the top of the oxygen tank, and the output end is connected to the input ends of the first oxygen branch and the second oxygen branch. The output end of the first oxygen branch is connected to the top of the thrust chamber, and the output end of the second oxygen branch is connected to the torch igniter.

5. The oxygen-methane propulsion system according to claim 4, characterized in that: The oxygen auxiliary valve is arranged on the second oxygen branch line.

6. The oxygen-methane propulsion system according to claim 5, characterized in that: The oxygen auxiliary valve is a one-way valve structure.

7. The oxygen-methane propulsion system according to claim 1, characterized in that: A blowing device is also provided, and the blowing device is used to blow out the oxygen head cavity of the thrust chamber through the pipeline at the connection position between the oxygen pipeline structure and the torch igniter.

8. The oxygen-methane propulsion system according to claim 7, characterized in that: The blow-off device comprises a high-pressure gas cylinder and a blow-off pipeline, the gas outlet of the high-pressure gas cylinder is connected to the inlet of the blow-off pipeline, and the outlet of the blow-off pipeline is connected to the pipeline of the oxygen pipeline structure and the torch igniter connection part.

9. The oxygen-methane propulsion system according to claim 1, characterized in that: The methane tank and the oxygen tank are both cylindrical in shape with arc-shaped raised cover plates at both ends, and the arc-shaped raised cover plates are convex upwards away from the bottom relative to the bottom.

10. A liquid rocket, characterized in that: A gas oxygen methane propulsion system comprising any one of claims 1-9.

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