An electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system

Abstract

An integrated electric pump-type liquid oxygen-methane rocket main and auxiliary propulsion system uses an electric pump to pressurize the low-pressure propellant in the rocket tank. A reversing valve controls the flow of the pressurized propellant, directing it to the attitude and orbit control engine or back to the rocket tank. If the reversing valve continuously supplies propellant to the attitude and orbit control engine, the engine can operate continuously and stably. If the reversing valve supplies propellant to the engine and then immediately switches it to the rocket tank, this repetitive cycle enables pulsed operation of the engine. The reversing valve maintains normal flow downstream of the electric pump at all times, ensuring stable operation regardless of whether the engine is operating steadily or in pulsed mode. A cavitation tube is installed before the reversing valve. The electric pump maintains constant speed and power during pulsed operation, maintaining constant pressure and flow downstream of the pump. This constant flow into the engine ensures constant thrust generated by each pulse of the engine.

Description

Technical Field

[0001] The invention relates to an electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system, belonging to the technical field of liquid rocket engines. Background Art

[0002] Liquid oxygen-methane rocket engines offer advantages such as abundant propellant resources, reusability, low cost, non-toxicity, ease of use and maintenance, and excellent overall performance. In recent years, numerous rocket designs using liquid oxygen-methane engines as their primary power have emerged both domestically and internationally. However, since attitude and orbit control engines using pump-type propellant supply systems struggle to achieve constant pulse operation, current rocket attitude and orbit control engines mostly use conventional toxic propellants, pulsed via a high-pressure extrusion propellant supply system. This approach suffers from the inability to share low-pressure propellant tanks with the rocket's main engines, requiring separate high-pressure tanks and high-pressure extrusion cylinders. This also complicates the rocket's structure and test and launch procedures, making it unsuitable for regular space transport. Summary of the Invention

[0003] The technical problem to be solved by the present invention is: to overcome the shortcomings of the existing technology, provide an integrated main and auxiliary power system of an electric pump-pressure liquid oxygen-methane rocket, realize the goal of pulse operation of the pump-pressure attitude and orbit control engine, obtain the effect of sharing the rocket low-pressure tank of the main propulsion engine and the attitude and orbit control engine, and achieve the purpose of optimizing the rocket system structure.

[0004] The purpose of the present invention is achieved through the following technical solutions:

[0005] An electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system includes a liquid methane tank, a liquid oxygen tank, a reversing valve, an electric pump, a main propulsion engine oxygen turbopump, a main propulsion engine methane turbopump, a battery, a main propulsion engine, an oxygen supply pipeline, a methane supply pipeline, an attitude and orbit control engine group, a methane cavitation tube, and an oxygen cavitation tube; the reversing valve includes a first reversing valve, a second reversing valve, a third reversing valve, and a fourth reversing valve; and the electric pump includes a first electric pump and a second electric pump;

[0006] A first electric pump and a second electric pump are used to pressurize the low-pressure propellant in the liquid oxygen tank and the liquid methane tank. The pressurized propellant is passed through the corresponding oxygen supply pipeline and the methane supply pipeline, and the flow rate is maintained constant through the oxygen cavitation tube and the methane cavitation tube. The propellant with a constant flow rate can be freely switched through the third reversing valve and the fourth reversing valve to supply the attitude and orbit control engine group or return to the original liquid oxygen tank and the liquid methane tank, thereby realizing the pulsed operation or continuous and stable operation of the electric pump-pressurized liquid oxygen and methane attitude and orbit control engine;

[0007] Oxygen supply pipelines and methane supply pipelines are led out from the liquid oxygen tank and liquid methane tank respectively to supply propellant to the main propulsion engine and attitude and orbit control engine group. The main propulsion engine and attitude and orbit control engine share a low-pressure tank;

[0008] Before the secondary start of the main propulsion engine, the propellant pressurized by the electric pump can be input into the main propulsion engine through the first reversing valve and the second reversing valve to perform a circulation precooling of the main propulsion engine. After the precooling, the propellant of the engine can be returned to the liquid oxygen tank and the liquid methane tank.

[0009] The high speed of the oxygen turbopump and methane turbopump when the main propulsion engine is working is used to generate electricity, or the temperature difference between the low-temperature part of liquid oxygen and liquid methane and the high-temperature part of the combustion chamber is used to generate electricity to charge the battery, and the electricity can drive the electric pump.

[0010] Compared with the prior art, the present invention has the following beneficial effects:

[0011] (1) The present invention utilizes an electric pump to drive the attitude and orbit control engine group to perform pulse operation or stable continuous operation, and proposes a new solution for realizing the pulse operation of the attitude and orbit control engine by utilizing a reversing valve.

[0012] (2) The present invention utilizes a cavitation tube installed behind the electric pump to achieve a switching valve between the tank and the attitude and orbit control engine group. As long as the outlet pressure of the electric pump is constant, the propellant supply flow rate can be kept constant even if the tank pressure is different from the inlet pressure of the attitude and orbit control engine group. Since the propellant flow rate is constant, the electric pump only needs to maintain a constant speed and power to achieve a constant outlet pressure of the electric pump. This method does not require real-time adjustment of the electric pump speed and power to maintain a constant propellant pressure and flow at the outlet of the electric pump, significantly reducing the difficulty of electric pump design and control.

[0013] (3) The present invention realizes that the main propulsion engine and the attitude and orbit control engine share a low-pressure tank, and the main and auxiliary power share the same propellant to achieve the integration of the main and auxiliary power without adding a high-pressure tank to the rocket and other auxiliary devices such as high-pressure gas cylinders, thereby simplifying the rocket body structure and optimizing the test and launch process.

[0014] (4) The present invention realizes the cyclic pre-cooling of the main propulsion engine before the secondary start, thereby reducing the performance loss caused by the current secondary start propellant pre-cooling discharge.

[0015] (5) The present invention realizes the generation of electricity when the main propulsion engine is working. The generated electricity can drive electrical devices such as electric pumps, valves, spark plugs and servo mechanisms, and can also charge onboard batteries, which is beneficial to reducing the volume of onboard batteries. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of the main and auxiliary power integration system of the electric pump-pressure liquid oxygen-methane rocket of the present invention.

[0017] Figure numerals: liquid methane tank-1, liquid oxygen tank-2, reversing valve-3, electric pump-4, oxygen turbopump-5, methane turbopump-6, battery-7, main propulsion engine-8, oxygen supply pipeline-9, methane supply pipeline-10, attitude and orbit control engine group-11, methane cavitation tube-12, oxygen cavitation tube 13, first reversing valve-3-1, second reversing valve-3-2, third reversing valve-3-3, fourth reversing valve-3-4, first electric pump-4-1, second electric pump-4-2. DETAILED DESCRIPTION

[0018] To make the objectives, technical solutions and advantages of the present invention more clear, the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0019] To simplify the use and maintenance of rocket propulsion systems, the present invention proposes an integrated electric pump-type liquid oxygen-methane rocket main and auxiliary propulsion system. This system uses an electric pump to pressurize the low-pressure propellant in the rocket tank. A reversing valve controls the flow of the pressurized propellant, either into the attitude and orbit control engine or back into the rocket tank. If the reversing valve continuously feeds propellant into the attitude and orbit control engine, continuous and stable operation of the engine is achieved. If the reversing valve feeds propellant into the engine and then immediately switches it to the rocket tank, this cycle enables pulsed operation of the engine. The reversing valve maintains normal flow downstream of the electric pump at all times, ensuring stable operation regardless of whether the engine is operating steadily or in pulsed mode. A cavitation tube is installed before the reversing valve. During pulsed operation of the engine, the electric pump maintains constant speed and power, maintaining constant pressure and flow downstream of the pump. This constant flow into the engine ensures constant thrust generated by each pulse of the engine. This plan does not change or add to the rocket tank, nor does it add other auxiliary extrusion devices such as high-pressure gas cylinders. It enables the main propulsion engine and attitude and orbit control engine to share a low-pressure tank, and the main and auxiliary power to share the same propellant to achieve main and auxiliary power integration.

[0020] Currently, when recovering liquid oxygen-methane rockets, the main propulsion engine needs to undergo a secondary ignition. Before ignition, the engine must be pre-cooled to keep the cryogenic propellant in a liquid phase when it enters the pump, preventing cavitation in the main pump. Directly discharging the pre-cooled engine propellant would result in a loss of propellant. A reversing valve allows the propellant, pressurized by the electric pump, to be fed back into the main propulsion engine for cyclic pre-cooling. After pre-cooling, the propellant can then be returned to the rocket tank, reducing the propellant consumed by the engine during pre-cooling.

[0021] Currently, rockets carry batteries for convenient power supply. This invention adds an electric pump to the existing rocket system. This electric pump operation increases power consumption during attitude and orbit control engine operation or secondary start-up pre-cooling. This invention proposes utilizing the high speed of the turbopump during main propulsion engine operation to generate electricity, or utilizing the temperature difference between the low-temperature area of ​​the liquid oxygen and liquid methane supply system and the high-temperature area of ​​the combustion device to generate electricity. This can be used to charge the battery and drive the electric pump, valves, spark plugs, and servo mechanisms.

[0022] An electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system includes a liquid methane tank 1, a liquid oxygen tank 2, a reversing valve 3, an electric pump 4, a main propulsion engine oxygen turbopump 5, a main propulsion engine methane turbopump 6, a battery 7, a main propulsion engine 8, an oxygen supply pipeline 9, a methane supply pipeline 10, an attitude and orbit control engine group 11, a methane cavitation tube 12, and an oxygen cavitation tube 13; the reversing valve 3 includes a first reversing valve 3-1, a second reversing valve 3-2, a third reversing valve 3-3, and a fourth reversing valve 3-4, and the electric pump 4 includes a first electric pump 4-1 and a second electric pump 4-2. Figure 1 shown.

[0023] The first electric pump 4-1 and the second electric pump 4-2 are used to pressurize the low-pressure propellant in the liquid oxygen tank 2 and the liquid methane tank 1. The pressurized propellant is supplied through the oxygen supply line 9 and the methane supply line 10, and the flow rate is maintained constant through the oxygen cavitation tube 13 and the methane cavitation tube 12. The propellant with a constant flow rate can be freely switched through the third reversing valve 3-3 and the fourth reversing valve 3-4 to supply the attitude and orbit control engine group 11 or return to the original liquid oxygen tank 2 and the liquid methane tank 1, thereby realizing constant thrust pulse operation or continuous stable operation of the electric pump-pressure liquid oxygen and methane attitude and orbit control engine.

[0024] Two pipelines are led out from the liquid oxygen tank 2 and the liquid methane tank 1 respectively to supply propellant to the main propulsion engine 8 and the attitude and orbit control engine group 11. The main propulsion engine 8 and the attitude and orbit control engine share a low-pressure tank.

[0025] Before the main propulsion engine 8 is started for the second time, the propellant pressurized by the electric pump 4 can be input into the main propulsion engine 8 through the first reversing valve 3-1 and the second reversing valve 3-2 to perform circulation precooling of the main propulsion engine 8. After the precooling, the propellant of the engine can be returned to the liquid oxygen tank 2 and the liquid methane tank 1.

[0026] The high speed of the oxygen turbopump 5 and the methane turbopump 6 when the main propulsion engine 8 is working is used to generate electricity, or the temperature difference between the low-temperature part of the liquid oxygen and liquid methane and the high-temperature part of the combustion chamber is used to generate electricity to charge the battery 7, and the electricity can drive the electric pump 4, etc.

[0027] More specific:

[0028] (1) Reversing valve 3, which has one inlet and two outlets. When working, the fluid enters from the inlet and can only flow out from one outlet, while the other outlet is closed. The outlet position can be freely selected through electromagnetic control.

[0029] (2) Electric pump 4, which is driven by an electric motor and can pump cryogenic liquid.

[0030] (3) A methane supply line 10 is drawn from the bottom of the liquid methane tank 1 and connected to the inlet of the methane turbopump 6 of the main propulsion engine 8;

[0031] (4) A methane supply pipe 10 is drawn out from the bottom of the liquid methane storage tank 1 and connected to the inlet of the second electric pump 4-2;

[0032] (5) A methane supply line 10 is drawn from the outlet of the second electric pump 4-2 and connected to the inlet of the second reversing valve 3-2;

[0033] (6) A methane supply line 10 is led out from one outlet of the second reversing valve 3-2 and connected to the inlet of the methane turbine pump 6;

[0034] (7) A methane supply pipeline 10 is led out from a discharge port of the methane turbo pump 6 and connected to the inlet of the liquid methane storage tank 1;

[0035] (8) A methane supply line 10 is led out from the other outlet of the second reversing valve 3-2 and connected to the inlet of the methane cavitation pipe 12;

[0036] (9) A methane supply line 10 is drawn out from the outlet of the methane cavitation pipe 12 and connected to the inlet of the reversing valve 3-4;

[0037] (10) A methane supply line 10 is led from one outlet of the fourth reversing valve 3-4 and connected to the methane inlet of the attitude and orbit control engine group 11;

[0038] (11) A methane supply line 10 is drawn out from another outlet of the fourth reversing valve 3-4 and connected to the top interface of the liquid methane storage tank 1.

[0039] (12) An oxygen supply line 9 is drawn from the bottom of the liquid oxygen tank 2 and connected to the inlet of the oxygen turbo pump 5;

[0040] (13) An oxygen supply line 9 is drawn from the bottom of the liquid oxygen tank 2 and connected to the inlet of the first electric pump 4-1;

[0041] (14) An oxygen supply line 9 is drawn from the outlet of the first electric pump 4-1 and connected to the inlet of the first reversing valve 3-1;

[0042] (15) An oxygen supply line 9 is led out from one outlet of the first reversing valve 3-1 and connected to the inlet of the oxygen turbo pump 5;

[0043] (16) An oxygen supply line 9 is drawn from a discharge port of the oxygen turbo pump 5 and connected to the inlet of the liquid oxygen tank 2;

[0044] (17) An oxygen supply line 9 is drawn out from the other outlet of the first reversing valve 3-1 and connected to the inlet of the oxygen cavitation pipe 13;

[0045] (18) An oxygen supply line 9 is drawn out from the outlet of the oxygen cavitation pipe 13 and connected to the inlet of the reversing valve 3-3;

[0046] (19) An oxygen supply line 9 is drawn from one outlet of the third reversing valve 3-3 and connected to the oxygen inlet of the attitude and orbit control engine group 11;

[0047] (20) An oxygen supply line 9 is drawn out from another outlet of the third reversing valve 3-3 and connected to the top interface of the liquid oxygen tank 2.

[0048] (21) The methane turbo pump 6 and the oxygen turbo pump 5 generate electricity to charge the battery 7.

[0049] (22) The first electric pump 4 - 1 and the second electric pump 4 - 2 are powered by the battery 7 .

[0050] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

[0051] Although the present invention has been disclosed above in terms of preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solutions of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the scope of protection of the technical solutions of the present invention.

Claims

1. An electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system, characterized in that: The invention comprises a liquid methane tank (1), a liquid oxygen tank (2), a reversing valve (3), an electric pump (4), a main propulsion engine oxygen turbine pump (5), a main propulsion engine methane turbine pump (6), a battery (7), a main propulsion engine (8), an oxygen supply pipeline (9), a methane supply pipeline (10), an attitude and orbit control engine group (11), a methane cavitation tube (12), and an oxygen cavitation tube (13); the reversing valve (3) comprises a first reversing valve (3-1), a second reversing valve (3-2), a third reversing valve (3-3), and a fourth reversing valve (3-4); and the electric pump (4) comprises a first electric pump (4-1) and a second electric pump (4-2); A first electric pump (4-1) and a second electric pump (4-2) are used to pressurize the low-pressure propellant in the liquid oxygen tank (2) and the liquid methane tank (1). The pressurized propellant is supplied through the corresponding oxygen supply pipeline (9) and the methane supply pipeline (10), and the flow rate is kept constant through the oxygen cavitation tube (13) and the methane cavitation tube (12). The propellant with a constant flow rate can be freely switched to supply the attitude and orbit control engine group (11) or return to the original liquid oxygen tank (2) and the liquid methane tank (1) through the third reversing valve (3-3) and the fourth reversing valve (3-4), thereby realizing the pulse operation or continuous stable operation of the electric pump pressure type liquid oxygen and methane attitude and orbit control engine; An oxygen supply line (9) and a methane supply line (10) are drawn out from the liquid oxygen tank (2) and the liquid methane tank (1) respectively to supply propellant to the main propulsion engine (8) and the attitude and orbit control engine group (11). The main propulsion engine (8) and the attitude and orbit control engine share a low-pressure tank. Before the main propulsion engine (8) is started for the second time, the propellant pressurized by the electric pump (4) can be input into the main propulsion engine (8) through the first reversing valve (3-1) and the second reversing valve (3-2) to perform circulatory precooling of the main propulsion engine (8). After the precooling, the propellant of the engine can be returned to the liquid oxygen tank (2) and the liquid methane tank (1); The high rotation speed of the oxygen turbo pump (5) and the methane turbo pump (6) when the main propulsion engine (8) is in operation is used to generate electricity, or the temperature difference between the low-temperature part of the liquid oxygen and liquid methane and the high-temperature part of the combustion chamber is used to generate electricity to charge the battery (7), and the electricity can drive the electric pump (4).

2. The electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system according to claim 1 is characterized in that: The reversing valve (3) has one inlet and two outlets. When working, the fluid enters from the inlet and can only flow out from one outlet, while the other outlet is closed. The outlet position can be freely selected through electromagnetic control.

3. The electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system according to claim 1, characterized in that: The electric pump (4) is driven by a motor and is used to pump cryogenic liquid.

4. The electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system according to claim 1, characterized in that: A methane supply line (10) is drawn out from the bottom of the liquid methane tank (1) and connected to the inlet of the methane turbine pump (6) of the main propulsion engine (8); a methane supply line (10) is drawn out from the bottom of the liquid methane tank (1) and connected to the inlet of the second electric pump (4-2); a methane supply line (10) is drawn out from the outlet of the second electric pump (4-2) and connected to the inlet of the second reversing valve (3-2); a methane supply line (10) is drawn out from one outlet of the second reversing valve (3-2) and connected to the inlet of the methane turbine pump (6); a methane supply line (10) is drawn out from one outlet of the methane turbine pump (6) and connected to the inlet of the methane turbine pump (6). A methane supply pipeline (10) is connected to the inlet of the liquid methane storage tank (1); a methane supply pipeline (10) is drawn out from the other outlet of the second reversing valve (3-2) and connected to the inlet of the methane cavitation tube (12); a methane supply pipeline (10) is drawn out from the outlet of the methane cavitation tube (12) and connected to the inlet of the reversing valve (3-4); a methane supply pipeline (10) is drawn out from one outlet of the fourth reversing valve (3-4) and connected to the methane inlet of the attitude and orbit control engine group (11); a methane supply pipeline (10) is drawn out from the other outlet of the fourth reversing valve (3-4) and connected to the top interface of the liquid methane storage tank (1).

5. The electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system according to claim 1, characterized in that: An oxygen supply pipeline (9) is drawn out from the bottom of the liquid oxygen tank (2) and connected to the inlet of the oxygen turbine pump (5); an oxygen supply pipeline (9) is drawn out from the bottom of the liquid oxygen tank (2) and connected to the inlet of the first electric pump (4-1); an oxygen supply pipeline (9) is drawn out from the outlet of the first electric pump (4-1) and connected to the inlet of the first reversing valve (3-1); an oxygen supply pipeline (9) is drawn out from one outlet of the first reversing valve (3-1) and connected to the inlet of the oxygen turbine pump (5); an oxygen supply pipeline (9) is drawn out from one outlet of the oxygen turbine pump (5) The oxygen supply pipeline (9) is connected to the inlet of the liquid oxygen tank (2); an oxygen supply pipeline (9) is drawn out from the other outlet of the first reversing valve (3-1) and connected to the inlet of the oxygen cavitation tube (13); an oxygen supply pipeline (9) is drawn out from the outlet of the oxygen cavitation tube (13) and connected to the inlet of the reversing valve (3-3); an oxygen supply pipeline (9) is drawn out from one outlet of the third reversing valve (3-3) and connected to the oxygen inlet of the attitude and orbit control engine group (11); an oxygen supply pipeline (9) is drawn out from the other outlet of the third reversing valve (3-3) and connected to the top interface of the liquid oxygen tank (2).

6. The electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system according to claim 1, characterized in that: The methane turbo pump (6) and the oxygen turbo pump (5) generate electricity to charge the battery (7).

7. The electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system according to claim 1, characterized in that: The first electric pump (4-1) and the second electric pump (4-2) are powered by a battery (7).

8. The electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system according to any one of claims 1 to 7, characterized in that: The electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system can circulate and pre-cool the main propulsion engine (8) before ignition.

9. The electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system according to any one of claims 1 to 7, characterized in that: The cavitation tube is installed before the reversing valve (3), which can make the pressure and flow rate after the pump constant. The constant flow rate entering the attitude and orbit control engine can ensure that the thrust generated by each pulse operation of the attitude and orbit control engine is constant.

10. The electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system according to any one of claims 1 to 7, characterized in that: The main propulsion engine (8) and the attitude and orbit control engine share a low-pressure tank.

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