Main and auxiliary integrated power system and liquid rocket

Abstract

The utility model relates to the technical field of liquid rockets, and discloses a main and auxiliary integrated power system and a liquid rocket, the main and auxiliary integrated power system comprises a main engine, an energy storage device and an auxiliary power engine, the energy storage device is connected with the main engine and used for storing propellants generated by the main engine, and the auxiliary power engine is connected with the main engine. The main engine is connected with the auxiliary power engine, the auxiliary power engine is connected with the energy storage device, and a propellant in the energy storage device is used for combustion of the auxiliary power engine. According to the auxiliary power system, the high-purity propellant generated by the main engine can be utilized, the cost is reduced, meanwhile, excessive storage boxes or gas cylinders do not need to be configured, the system structure is simple, and the weight reduction effect is effectively achieved compared with an auxiliary power system meeting engines of the same thrust specification.

Description

Technical Field

[0001] The utility model relates to the technical field of liquid rockets, in particular to a main-auxiliary integrated power system and a liquid rocket. Background Art

[0002] The auxiliary propulsion system is an important component of the space launch system and spacecraft. The functions of the auxiliary propulsion system include attitude control, speed correction, position maintenance, propellant sinking, and various auxiliary power devices on the spacecraft.

[0003] The existing liquid rocket propulsion system consists of a main engine and an auxiliary power system, each of which has its own propellant and is supplied separately. Since the main engine and the auxiliary power system use their own propellants to work, it is necessary to configure the auxiliary power system with additional high-pressure gas cylinders, tanks and other components, which will increase the structural complexity of the system and make the system heavier. Utility Model Content

[0004] In view of this, the utility model provides a main-auxiliary integrated power system and a liquid rocket to solve the problems that the main and auxiliary power systems of the existing liquid rockets use their own propellants to work, the system structure is highly complex and the system has a large deadweight.

[0005] In a first aspect, the utility model provides a main-auxiliary integrated power system, comprising:

[0006] Main engine systems, including main engines;

[0007] an energy storage device connected to the main engine, the energy storage device being used to store gas propellant generated by the main engine;

[0008] The auxiliary power engine is connected to the energy storage device, and the propellant in the energy storage device is used for combustion of the auxiliary power engine.

[0009] Beneficial effects: By setting up an energy storage device connected to the main engine, which is connected to the auxiliary engine, the gas propellant required for the auxiliary power engine is directly drawn from the main engine, and the high-purity propellant produced by the main engine can be utilized to reduce costs. At the same time, there is no need to configure too many tanks or gas cylinders. The system structure is simple and effectively achieves weight reduction compared to the auxiliary power system of engines that meet the same thrust specifications.

[0010] In an optional embodiment, the energy storage device includes a gas storage cylinder, and the gas storage cylinder is used to store gas propellant.

[0011] Beneficial effect: By setting up gas storage cylinders, the gas storage cylinders only need to store the gas used for auxiliary power in the gliding section of the rocket, and do not need to carry the gas for the entire flight. Therefore, there is no need to configure too many tanks or gas cylinders. The system structure is simple and can achieve effective weight reduction of the system.

[0012] In an optional embodiment, the gas storage cylinder includes a first gas cylinder for storing an oxidant and a second gas cylinder for storing a fuel, the first gas cylinder is connected to the main engine via a first pipeline, and the second gas cylinder is connected to the main engine via a second pipeline.

[0013] Beneficial effect: By arranging the first gas cylinder and the second gas cylinder to store the oxidant and the fuel respectively, the working capacity of the auxiliary power system of the rocket's gliding phase can be guaranteed.

[0014] In an optional embodiment, a first inflation valve is provided on the first pipeline, and the first inflation valve is used to inflate the first gas cylinder.

[0015] Beneficial effect: By setting the first inflation valve, the gas oxidant can be filled into the first gas cylinder through the first pipeline, and the pressure in the first gas cylinder is conveniently controlled. In actual use, a safety valve can be set in the third pipeline to ensure that the pressure in the first gas cylinder does not exceed a safe value.

[0016] In an optional implementation, the first gas cylinder is connected to the auxiliary power engine via a third pipeline, and a first pressure reducing valve is provided on the third pipeline.

[0017] Beneficial effect: By setting the first pressure reducing valve to effectively reduce the pressure, the oxidant can be used for auxiliary power engine after being reduced in pressure by the first pressure reducing valve. The structural principle is simple and the pressure regulation response speed is fast, which can ensure the stability of the system's air supply pressure. At the same time, the system has pressure setting and adjustment functions, ensuring the reliability of the system function.

[0018] In an optional implementation, a second inflation valve is provided on the second pipeline, and the second inflation valve is used to inflate the second gas cylinder.

[0019] Beneficial effect: By setting the second charging valve, the gaseous combustion agent can be filled into the second gas cylinder through the second pipeline, and the pressure in the second gas cylinder is conveniently controlled. In actual use, a safety valve can be set in the fourth pipeline to ensure that the pressure in the second gas cylinder does not exceed the safety value.

[0020] In an optional implementation, the second gas cylinder is connected to the auxiliary power engine via a fourth pipeline, and a second pressure reducing valve is provided on the fourth pipeline.

[0021] Beneficial effect: By setting up the second pressure reducing valve to effectively reduce the pressure, the fuel can be used for auxiliary power engine after being reduced in pressure by the second pressure reducing valve. The structural principle is simple and the pressure regulation response speed is fast, which can ensure the stability of the system's air supply pressure. At the same time, the system has pressure setting and adjustment functions, ensuring the reliability of the system function.

[0022] In an optional embodiment, the main engine system further comprises a tank for storing liquid propellant of the main engine.

[0023] Beneficial effect: By setting up a tank to store liquid propellant, the application range is wide and it can be stored for a long time to provide liquid propellant for the main engine.

[0024] In an optional embodiment, the main engine system also includes a main engine boost circuit branch, which includes a heat exchanger and a regenerative cooling circuit, one end of the main engine boost circuit branch is connected to the heat exchanger or the regenerative cooling circuit, and the other end of the main engine boost circuit branch is connected to the energy storage device.

[0025] Beneficial effect: By utilizing the main engine boost circuit, high-purity propellant steam heated by the main engine is supplied to the auxiliary power through a heat exchanger or a regenerative cooling circuit branch, thereby ensuring the combustion stability of the auxiliary power engine and improving the working efficiency and reliability of the auxiliary power engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the specific implementation methods of the utility model or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0027] Figure 1 It is a structural schematic diagram of a main-auxiliary integrated power system according to an embodiment of the utility model.

[0028] Description of reference numerals:

[0029] 1. Main engine; 201. First gas cylinder; 202. Second gas cylinder; 3. Auxiliary power engine; 4. First inflation valve; 5. Second inflation valve; 6. First pressure reducing valve; 7. Second pressure reducing valve; 8. Regeneration cooling circuit; 9. Heat exchanger. DETAILED DESCRIPTION

[0030] In order to make the purpose, technical solution and advantages of the embodiment of the utility model clearer, the technical solution in the embodiment of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiment of the utility model. Obviously, the described embodiment is a part of the embodiment of the utility model, not all the embodiments. Based on the embodiment of the utility model, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the utility model.

[0031] In the related art, the liquid rocket propulsion system is composed of a main engine and an auxiliary power system, each of which has its own propellant and is supplied separately. Since the main engine and the auxiliary power system use their own propellants to work, it is necessary to configure additional components such as high-pressure gas cylinder tanks for the auxiliary power system, which increases the structural complexity of the system and makes the system heavier.

[0032] Based on the above problems, an embodiment of the utility model provides a main-auxiliary integrated power system and liquid rocket that can realize the integrated integration of the main engine and auxiliary power, greatly reduce the weight of the power system, and at the same time can be reused to reduce costs.

[0033] Combine the following Figure 1 , describing an embodiment of the utility model.

[0034] According to an embodiment of the utility model, on the one hand, a main-auxiliary integrated power system is provided, which includes: a main engine system, an energy storage device and an auxiliary power engine 3, the main engine system includes a main engine 1, the energy storage device is connected to the main engine 1, the energy storage device is used to store the propellant generated by the main engine 1, the auxiliary power engine 3 is connected to the energy storage device, the propellant in the energy storage device is used for the combustion of the auxiliary power engine 3, and also includes a thrust chamber, the thrust chamber generates thrust through the combustion of the propellant, the thrust chamber includes a propellant nozzle, a combustion chamber and a nozzle assembly, the propellant is injected into the combustion chamber through an injector, and combustion products are generated through processes such as atomization, evaporation, mixing and combustion, and are ejected from the Laval nozzle at high speed to generate thrust.

[0035] The main-auxiliary integrated power system of this embodiment is provided with an energy storage device connected to the main engine 1. The energy storage device is connected to the auxiliary engine, and the propellant required by the auxiliary power engine 3 is directly drawn from the main engine 1. The high-purity propellant steam generated by the main engine 1 can be utilized to reduce costs. At the same time, there is no need to configure too many tanks or gas cylinders. The system structure is simple, and compared with the auxiliary power system of the engine that meets the same thrust specification, it effectively achieves weight reduction.

[0036] In one embodiment, the energy storage device includes a gas cylinder for storing gas propellant. By providing the gas cylinder, the gas cylinder only needs to store the gas used for auxiliary power and does not need to carry the gas for the entire flight. Therefore, there is no need to configure too many tanks or gas cylinders, and the system structure is simple, so the system can effectively reduce weight.

[0037] like Figure 1 As shown, in one embodiment, the gas storage cylinder includes a first gas cylinder 201 for storing an oxidant and a second gas cylinder 202 for storing a fuel, the first gas cylinder 201 is connected to the heat exchanger 9 of the main engine 1 through a first pipeline, and the second gas cylinder 202 is connected to the regenerative cooling circuit 8 of the main engine 1 through a second pipeline. By arranging the first gas cylinder 201 and the second gas cylinder 202 to store the oxidant and the fuel respectively, the working capacity of the auxiliary power system of the rocket glide stage can be guaranteed through the main engine boost circuit branch.

[0038] like Figure 1 As shown, in one embodiment, a first charging valve 4 is provided on the first pipeline, and the first charging valve 4 is used to charge the first gas cylinder 201. By providing the first charging valve 4, the oxidant can be charged into the first gas cylinder 201 through the first pipeline, and the pressure in the first gas cylinder 201 can be easily controlled. In actual use, a safety valve can be provided in the third pipeline to prevent the pressure in the first gas cylinder 201 from exceeding a safe value.

[0039] like Figure 1 As shown, in one embodiment, the first gas cylinder 201 is connected to the auxiliary power engine 3 through the third pipeline. The third pipeline is provided with a first pressure reducing valve 6, which can effectively reduce the pressure before the oxidant enters the auxiliary power engine 3, so that the oxidant can be used for the auxiliary power engine 3 after being reduced in pressure. The structural principle is simple and the pressure regulation response speed is fast, which can ensure the stability of the gas supply pressure of the system. At the same time, the system has the pressure setting and adjustment functions, which ensures the reliability of the system function.

[0040] like Figure 1 As shown, in one embodiment, a second charging valve 5 is provided on the second pipeline, and the second charging valve 5 is used to charge the second gas cylinder 202. By providing the second charging valve 5, the second gas cylinder 202 can be charged with a combustion agent through the second pipeline, and the pressure in the second gas cylinder 202 can be easily controlled. In actual use, a safety valve can be provided in the fourth pipeline to prevent the pressure in the second gas cylinder 202 from exceeding a safety value.

[0041] like Figure 1As shown, in one embodiment, the second gas cylinder 202 is connected to the auxiliary power engine 3 through a fourth pipeline. A second pressure reducing valve 7 is provided on the fourth pipeline, which can effectively reduce the pressure before the fuel enters the auxiliary power engine 3, so that the fuel can be used in the auxiliary power engine 3 after being reduced in pressure. The structural principle is simple and the pressure regulation response speed is fast, which can ensure the stability of the gas supply pressure of the system. At the same time, the system has the pressure setting and regulation functions, which ensures the reliability of the system function.

[0042] Since the gas ejected from the combustion chamber is high in speed and high in temperature, and the pressure can reach 200 atmospheres (about 200 MPa) and the temperature can reach 300°C to 4000°C, the main engine 1 needs to be cooled.

[0043] Based on the above reasons, Figure 1 As shown, in this embodiment, the main engine system also includes a main engine boost circuit branch, a heat exchanger 9 and a regenerative cooling circuit 8, one end of the main engine boost circuit branch is connected to the heat exchanger 9 or the regenerative cooling circuit 8, and the other end of the boost circuit branch is connected to the energy storage device.

[0044] Specifically, it also includes a heat exchanger 9, one end of the heat exchanger 9 is connected to the turbo pump, one end of the regenerative cooling circuit 8 is connected to the turbo pump, and the other end is connected to the second gas cylinder 202 storing the fuel. Before entering the combustion chamber, the low-temperature fuel flows through the combustion chamber tube wall and absorbs and takes away the heat of the high-temperature and high-pressure gas generated by the combustion, and heats the fuel while cooling the main engine 1. The volume of the fuel expands rapidly after being heated, so that this part of the gas is used to drive the turbo pump, thereby forming an expansion cycle that uses the engine high temperature to heat part of the fuel to drive the turbo pump. The outlet of the second gas cylinder 202 is roughly divided into several parts after passing through the turbo pump. One part is used for the pressurization of the second gas cylinder 202 through the heat exchanger 9, one part is used to drive the turbo pump, and one part directly goes to the main engine 1 to participate in the combustion. Therefore, by setting the regenerative cooling circuit 8, not only the temperature of the main engine 1 is reduced, its normal operation is ensured, and the working efficiency and reliability of the main engine 1 are improved, but also there is no heat energy loss, the structure is simple, the reliability is strong, and it is conducive to repeated use. By utilizing the main engine boost circuit, the propellant gas is led out from the main engine boost circuit through the heat exchanger or the regeneration cooling circuit 8, so that the high-purity propellant gas heated by the main engine 1 is supplied to the auxiliary power for use, and the purity of the propellant burned by the auxiliary power engine 3 is ensured, thereby ensuring the combustion efficiency, stability and safety of the auxiliary power engine 3 and improving the working efficiency and reliability of the auxiliary power engine 3.

[0045] In order to further understand the main and auxiliary integrated power system of this embodiment, Figure 1 , the working process of the main-auxiliary integrated power system of this embodiment is described:

[0046] The main engine 1 generates high-concentration oxidant and fuel vapor, and the oxidant and fuel vapor are stored in the first gas cylinder 201 and the second gas cylinder 202 respectively; in the operation stage of the main engine 1, the two high-pressure gases pass through the first charging valve 4 and the second charging valve 5, a part of which is used for charging the first gas cylinder 201 and the second gas cylinder 202, and a part of which is directly transported to the first pressure reducing valve 6 and the second pressure reducing valve 7 of the auxiliary power engine 3, and is used for the auxiliary power engine 3 after being reduced in pressure by the first pressure reducing valve 6 and the second pressure reducing valve 7; in the taxiing section, the two high-pressure gases stored in the gas cylinders are reduced in pressure by the pressure reducing valves and filled in front of the first pressure reducing valve 6 and the second pressure reducing valve 7 of the auxiliary power engine 3; under the action of the arrow command, the solenoid valve of the auxiliary power engine 3 is controlled to be on and off to ensure the normal operation of the auxiliary power engine 3.

[0047] In this embodiment, the main engine system further includes a tank, which is used to store liquid propellant of the main engine 1 .

[0048] Specifically, the storage tank stores the oxidant and the fuel respectively in the form of liquid two-components. For example, the oxidant is liquid oxygen and the fuel is kerosene, or the oxidant is liquid oxygen and the fuel is liquid hydrogen, etc. By using an oxidant and a fuel as propellants, combustion produces high-temperature and high-pressure combustion gas, which has a wide range of applications and can be stored for a long time.

[0049] In other embodiments, the auxiliary power can also use a gaseous monopropellant as a propellant. The single-path high-purity fuel gas generated by the main engine 1 is used as the propellant for the auxiliary power. No combustion occurs in the thrust chamber, and the gas is directly ejected through the nozzle to generate thrust. Specifically, during the operation stage of the main engine 1, the single-path high-pressure gas passes through the gas cylinder charging valve, a part of which is used for charging the gas cylinder, and a part is directly transported to the front of the pressure reducing valve of the auxiliary power engine 3, and is used by the auxiliary power engine 3 after being reduced in pressure by the pressure reducing valve. During the gliding section, the two-path high-pressure gas stored in the gas cylinder is reduced in pressure by the pressure reducing valve and filled in front of the valve of the auxiliary power engine 3. The auxiliary power solenoid valve is powered on and off under the control of the arrow command.

[0050] According to an embodiment of the present utility model, on the other hand, a liquid rocket is also provided, comprising the above-mentioned main-auxiliary integrated power system.

[0051] The liquid rocket of this embodiment is provided with a main-auxiliary integrated power system. The main-auxiliary integrated power system is provided with an energy storage device connected to the main engine 1. The energy storage device is connected to the auxiliary engine. The propellant required for the auxiliary power engine 3 is directly drawn from the main engine 1. The high-purity propellant produced by the main engine 1 can be utilized to reduce costs. At the same time, there is no need to configure too many tanks or gas cylinders. The system structure is simple, which reduces the overall weight and volume of the carrier rocket, thereby improving the load capacity and carrying efficiency of the liquid rocket.

[0052] Although the embodiments of the present invention are described in conjunction with the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A main-auxiliary integrated power system, characterized in that: include: A main engine system, comprising a main engine (1); an energy storage device connected to the main engine (1), the energy storage device being used to store gas propellant generated by the main engine (1); An auxiliary power engine (3) is connected to the energy storage device, and the propellant in the energy storage device is used for combustion of the auxiliary power engine (3).

2. The main-auxiliary integrated power system according to claim 1, characterized in that: The energy storage device comprises a gas storage cylinder, and the gas storage cylinder is used for storing gas propellant.

3. The main-auxiliary integrated power system according to claim 2, characterized in that: The gas storage cylinder comprises a first gas cylinder (201) storing an oxidant and a second gas cylinder (202) storing a fuel, wherein the first gas cylinder (201) is connected to a main engine (1) via a first pipeline, and the second gas cylinder (202) is connected to the main engine (1) via a second pipeline.

4. The main-auxiliary integrated power system according to claim 3, characterized in that: The first pipeline is provided with a first inflation valve (4), and the first inflation valve (4) is used to inflate the first gas cylinder (201).

5. The main-auxiliary integrated power system according to claim 4, characterized in that: The first gas cylinder (201) is connected to the auxiliary power engine (3) via a third pipeline, and a first pressure reducing valve (6) is provided on the third pipeline.

6. The main-auxiliary integrated power system according to claim 3, characterized in that: The second pipeline is provided with a second inflation valve (5), and the second inflation valve (5) is used to inflate the second gas cylinder (202).

7. The main-auxiliary integrated power system according to claim 6, characterized in that: The second gas cylinder (202) is connected to the auxiliary power engine (3) via a fourth pipeline, and a second pressure reducing valve (7) is provided on the fourth pipeline.

8. The main-auxiliary integrated power system according to claim 1, characterized in that: The main engine system further includes a tank for storing liquid propellant for the main engine.

9. The main-auxiliary integrated power system according to any one of claims 1 to 8, characterized in that: The main engine system also includes a main engine boost circuit branch, which includes a heat exchanger (9) and a regenerative cooling circuit (8), one end of the main engine boost circuit branch is connected to the heat exchanger (9) or the regenerative cooling circuit (8), and the other end of the main engine boost circuit branch is connected to the energy storage device.

10. A liquid rocket, characterized in that: A main-auxiliary integrated power system comprising any one of claims 1 to 9.

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