Electric pump pressure type liquid oxygen methane rocket main and auxiliary power integrated system

Abstract

An electric pump pressure type liquid oxygen methane rocket main and auxiliary power integrated system adopts an electric pump to pressurize a low-pressure propellant in a rocket storage tank, the pressurized propellant can be controlled to enter an attitude and orbit control engine or return to the rocket storage tank through reversing of a reversing valve, and if the reversing valve continuously supplies the propellant into the attitude and orbit control engine, the propellant can enter the attitude and orbit control engine; continuous and stable work of the attitude and orbit control engine can be realized; if the reversing valve supplies propellants into the attitude and orbit control engine and then immediately switches to the rocket storage tank, pulse work of the attitude and orbit control engine can be achieved through circulation. The reversing valve can keep the electric pump in a normal circulation state at the downstream moment, and the electric pump can work normally and stably no matter whether the attitude and orbit control engine works stably or in a pulse mode. The cavitation pipe is installed in front of the reversing valve, when the attitude and orbit control engine works in a pulse mode, the rotating speed and the power of the electric pump are kept unchanged, the pressure and the flow behind the pump can be constant, the flow entering the attitude and orbit control engine is constant, and it can be guaranteed that thrust generated by the attitude and orbit control engine in each pulse work is constant.

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 have the advantages of abundant propellant resources, reusability, low cost, non-toxicity, pollution-free, easy to use and maintain, and good comprehensive performance. In recent years, many rocket design schemes with liquid oxygen-methane engines as the main power have appeared at home and abroad. Since it is difficult to achieve constant pulse operation for attitude and orbit control engine groups using pump-type propellant supply systems, currently most rocket attitude and orbit control engines use conventional toxic propellants and perform pulse operation through high-pressure extrusion propellant supply systems. The disadvantage of this scheme is that it cannot share the low-pressure propellant tank with the rocket main engine, and a high-pressure tank and high-pressure extrusion gas cylinder need to be set up separately. The rocket structure and test and launch process are very complicated, which is not conducive to flight-based space transportation. Summary of the invention

[0003] The technical problem to be solved by the present invention is: to overcome the shortcomings of the prior art, to provide an electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system, to achieve the goal of pulse operation of the pump-pressure attitude and orbit control engine, to achieve the effect of the main propulsion engine and the attitude and orbit control engine sharing the rocket low-pressure tank, and to 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, comprising 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 comprises a first reversing valve, a second reversing valve, a third reversing valve, and a fourth reversing valve, and the electric pump comprises a first electric pump and a second electric pump;

[0006] The first electric pump and the 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 supplied through the corresponding oxygen supply pipeline and the methane supply pipeline, and the flow rate is kept constant through the oxygen cavitation tube and the methane cavitation tube. The propellant with a constant flow rate can be freely switched to supply the attitude and orbit control engine group or return to the original liquid oxygen tank and the liquid methane tank through the third reversing valve and the fourth reversing valve, so as to realize the pulse operation or continuous and stable operation of the electric pump-pressure 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 the liquid methane tank respectively to supply propellant to the main propulsion engine and the attitude and orbit control engine group. The main propulsion engine and the attitude and orbit control engine share a low-pressure tank;

[0008] Before the main propulsion engine is started for the second time, 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 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 and 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 realize the switching of the reversing 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 the speed and power unchanged to achieve a constant outlet pressure of the electric pump. This method does not require real-time adjustment of the speed and power of the electric pump to keep the propellant pressure and flow rate at the outlet of the electric pump constant, which greatly reduces the difficulty of designing and controlling the electric pump.

[0013] (3) The present invention realizes that the main propulsion engine and the attitude and orbit control engine share the same 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 rocket high-pressure tank or 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 cyclic precooling of the main propulsion engine before the secondary start, thereby reducing the performance loss caused by the current secondary start propellant precooling discharge.

[0015] (5) The present invention realizes power generation 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 the onboard battery, which is beneficial to reducing the volume of the onboard battery. 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 further described in detail below with reference to the accompanying drawings.

[0019] In order to simplify the use and maintenance process of the rocket power system, the present invention proposes an electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system. The system uses an electric pump to pressurize the low-pressure propellant in the rocket tank. The pressurized propellant can be controlled to enter the attitude and orbit control engine or return to the rocket tank through the reversing valve. If the reversing valve continuously supplies the propellant to the attitude and orbit control engine, the attitude and orbit control engine can work continuously and stably; if the reversing valve supplies the propellant to the attitude and orbit control engine and then immediately switches to the rocket tank, the reciprocating cycle can realize the pulse operation of the attitude and orbit control engine. The reversing valve can keep the downstream of the electric pump in a normal flow state at all times. Whether the attitude and orbit control engine is working stably or in pulse operation, the electric pump can maintain normal and stable operation. A cavitation tube is installed in front of the reversing valve. When the attitude and orbit control engine is working in pulse operation, the electric pump keeps the speed and power unchanged, so that the pressure and flow after the pump are constant. The constant flow 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. 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 the low-pressure tank, and the main and auxiliary power to share the same propellant to achieve integration of the main and auxiliary power.

[0020] At present, when recovering liquid oxygen-methane rockets, the main propulsion engine needs to be ignited for the second time. Before ignition, the engine needs to be precooled so that the cryogenic propellant remains in a liquid state when entering the pump to prevent cavitation of the main pump. If the propellant of the precooled engine is discharged directly, a part of the propellant will be lost. The propellant pressurized by the electric pump can be input into the main propulsion engine through the reversing valve to perform cyclic precooling of the main propulsion engine. After the precooling of the engine, the propellant can be returned to the rocket tank, reducing the propellant consumed by the engine discharge precooling.

[0021] At present, rockets carry batteries for convenient power supply. The present invention adds an electric pump to the existing rocket system. When the attitude and orbit control engine is working or the secondary start precooling, the electric pump will cause an increase in power consumption. The present invention proposes to use the high speed of the turbo pump when the main propulsion engine is working to generate electricity, or use the temperature difference between the low temperature part of the liquid oxygen and liquid methane supply system and the high temperature part of the combustion device to generate electricity to charge the battery, which can be used to drive the electric pump, valves, spark plugs and servo mechanisms, etc.

[0022] An electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system, comprising 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 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, a second electric pump 4-2, such as 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 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, so as to realize the constant thrust pulse operation or continuous and 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 return 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 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) Directional 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) An electric pump 4, which is driven by a motor and can pump cryogenic liquid.

[0030] (3) A methane supply pipeline 10 is led out 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 pipeline 10 is led 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 pipeline 10 is led out 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 pipeline 10 is led out from an 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 pipeline 10 is led out from another outlet of the second reversing valve 3-2 and connected to the inlet of the methane cavitation pipe 12;

[0036] (9) A methane supply pipeline 10 is led 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 pipeline 10 is led 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;

[0038] (11) A methane supply pipeline 10 is led 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 pipeline 9 is led out 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 pipeline 9 is led out 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 pipeline 9 is led out 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 pipeline 9 is led out from an outlet of the first reversing valve 3-1 and connected to the inlet of the oxygen turbo pump 5;

[0043] (16) An oxygen supply pipeline 9 is led out 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 pipeline 9 is led out from another 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 led 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 pipeline 9 is led out from an 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 pipeline 9 is led out from another outlet of the third reversing valve 3-3 and connected to the top interface of the liquid oxygen storage tank 2.

[0048] (21) The methane turbopump 6 and the oxygen turbopump 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 as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution 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 solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. An electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system, characterized in that: It 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 a corresponding oxygen supply pipeline (9) and a methane supply pipeline (10), and the flow rate is kept constant through an oxygen cavitation tube (13) and a methane cavitation tube (12); the propellant with a constant flow rate can be freely switched through a third reversing valve (3-3) and a fourth reversing valve (3-4) to supply an attitude and orbit control engine group (11) or return to the original liquid oxygen tank (2) and the liquid methane tank (1), thereby realizing pulse operation or continuous stable operation of the electric pump pressure type liquid oxygen and methane attitude and orbit control engine; An oxygen supply pipeline (9) and a methane supply pipeline (10) are respectively drawn out from the liquid oxygen tank (2) and the liquid methane tank (1) 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 circulation precooling of the main propulsion engine (8), and the precooled propellant of the engine can be returned to the liquid oxygen tank (2) and the liquid methane tank (1); The high 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 an inlet and two outlets. When working, 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 is 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 is characterized in that: A methane supply pipeline (10) is led out from the bottom of the liquid methane storage tank (1) and connected to the inlet of a methane turbine pump (6) of the main propulsion engine (8); a methane supply pipeline (10) is led out from the bottom of the liquid methane storage tank (1) and connected to the inlet of a second electric pump (4-2); a methane supply pipeline (10) is led out from the outlet of the second electric pump (4-2) and connected to the inlet of a second reversing valve (3-2); a methane supply pipeline (10) is led out from an outlet of the second reversing valve (3-2) and connected to the inlet of a methane turbine pump (6); a methane supply pipeline (10) is led out from an outlet of the methane turbine pump (6) and connected to the inlet of a methane turbine pump (6); a methane supply pipeline (10) is led out from an outlet of the methane turbine pump (6) and connected to the inlet of a second reversing valve (3-2); A methane supply pipeline (10) is led out from another outlet of the second reversing valve (3-2) and connected to the inlet of a methane cavitation tube (12); a methane supply pipeline (10) is led 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 led 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 led out from another 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 is characterized in that: An oxygen supply pipeline (9) is led 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 led 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 led 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 led 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 led out from one outlet of the oxygen turbine pump (5) The oxygen supply pipeline (9) is connected to the inlet of the liquid oxygen storage tank (2); an oxygen supply pipeline (9) is led out from the other outlet of the first reversing valve (3-1) and connected to the inlet of the oxygen cavitation pipe (13); an oxygen supply pipeline (9) is led out from the outlet of the oxygen cavitation pipe (13) and connected to the inlet of the reversing valve (3-3); an oxygen supply pipeline (9) is led 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 led out from the other outlet of the third reversing valve (3-3) and connected to the top interface of the liquid oxygen storage tank (2).

6. The electric pump-pressure liquid oxygen-methane rocket main and auxiliary power integrated system according to claim 1 is 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 is 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), so that the pressure and flow rate after the pump can be kept 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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