Deep throttling system of open type circulating liquid rocket engine

Abstract

The invention discloses a deep throttling system of an open circulating liquid rocket engine, and belongs to the technical field of rocket engines. The throttling system comprises a thrust chamber, an oxidant pump, a fuel pump and a turbine, the oxidant pump comprises an oxidant pump inlet and an oxidant pump outlet, the oxidant pump inlet is communicated with an oxygen storage tank, the oxidant pump outlet comprises a first outlet and a second outlet, and the first outlet is communicated with the thrust chamber; the second outlet is communicated with the combustion device, and the combustion device is a thrust chamber or a generator; the fuel pump comprises a fuel pump inlet and a fuel pump outlet, the fuel pump inlet is communicated with the fuel storage tank, and the fuel pump outlet is communicated with the thrust chamber; the turbine comprises a turbine gas inlet and a turbine exhaust port, the turbine gas inlet is communicated with the combustion device, and a gas adjusting valve is arranged between the turbine gas inlet and the combustion device. The problem that an existing open-type circulating liquid rocket engine is inconvenient to control in the aspect of deep throttling can be solved.

Description

Technical Field

[0001] This application relates to the field of rocket engine technology, and in particular to a deep throttling system for an open-circulation liquid rocket engine. Background Technology

[0002] Currently, the pump-jet engines used in launch vehicles and spacecraft mainly fall into two categories: open cycle and closed cycle. Among them, open cycle liquid rocket engines have become the main choice for commercial spaceflight due to their simple system, low manufacturing cost, and relatively high thrust-to-weight ratio.

[0003] Open-cycle liquid rocket engines utilize the combustion of an oxidizer and fuel to generate gas, which in turn produces thrust to propel the rocket. The oxidizer is supplied by an oxidizer pump, and the fuel by a fuel pump; both pumps are driven by a turbine. In existing technologies, deep throttling of open-cycle liquid rocket engines is typically achieved by adjusting valves in the oxidizer pump outlet pipe and the fuel pump outlet pipe; however, this method presents challenges in control. Summary of the Invention

[0004] The main objective of this application is to provide a deep throttling system for an open-cycle liquid rocket engine, which aims to solve the technical problem of inconvenient control in deep throttling of existing open-cycle liquid rocket engines.

[0005] To achieve the above objectives, this application provides a deep throttling system for an open-cycle liquid rocket engine, comprising: a thrust chamber, an oxidizer pump, a fuel pump, and a turbine. The thrust chamber is used to mix and burn fuel and oxidizer to generate combustion gas, thereby forming thrust. The oxidizer pump includes an oxidizer pump inlet and an oxidizer pump outlet. The oxidizer pump inlet is connected to an oxygen storage tank via a pipeline. The oxidizer pump outlet includes a first outlet and a second outlet. The first outlet is connected to the thrust chamber via a pipeline and is used to deliver oxidizer from the oxygen storage tank to the thrust chamber. The second outlet is connected to a combustion device via a pipeline and is used to deliver oxidizer from the oxygen storage tank to the combustion device. The combustion device is used to mix and burn fuel and oxidizer to generate combustion gas, thereby forming thrust. The combustion device is either the thrust chamber or... The generator; the fuel pump includes a fuel pump inlet and a fuel pump outlet, the fuel pump inlet is connected to a fuel tank via a pipe, and the fuel pump outlet is connected to the thrust chamber via a pipe, the fuel pump outlet being used to deliver fuel from the fuel tank to the thrust chamber; the turbine includes a turbine gas inlet and a turbine exhaust port, the turbine gas inlet is connected to the combustion device via a pipe, and is used to drive the turbine using the thrust generated by the combustion device; a gas regulating valve is installed on the pipe between the turbine gas inlet and the combustion device, the gas regulating valve being used to control the opening of the pipe between the turbine gas inlet and the combustion device; the turbine exhaust port is used to discharge the gas passing through the turbine; wherein, the turbine is used to drive the oxidizer pump and the fuel pump.

[0006] Optionally, when the combustion device is the generator, the generator is located on one side of the thrust chamber, and the thrust generated by the thrust chamber is used to drive the rocket launch.

[0007] Optionally, the fuel pump further includes a fuel pump auxiliary outlet, which is connected to the generator via a pipeline, and the fuel pump auxiliary outlet is used to deliver fuel from the fuel tank to the generator.

[0008] Optionally, a fuel auxiliary valve is connected to the pipeline between the fuel pump auxiliary outlet and the generator, the fuel auxiliary valve being used to control the opening degree of the pipeline between the fuel pump auxiliary outlet and the generator.

[0009] Optionally, when the combustion device is the thrust chamber, part of the thrust generated by the thrust chamber is used to drive the rocket launch, and another part is used to drive the turbine to work.

[0010] Optionally, the thrust chamber includes a main combustion chamber and a pre-combustion chamber, the first outlet is connected to the main combustion chamber of the thrust chamber via a pipe, and the second outlet is connected to the pre-combustion chamber of the thrust chamber via a pipe.

[0011] Optionally, the turbine gas inlet is connected to the pre-combustion chamber of the thrust chamber via a pipeline, and the gas regulating valve is disposed between the turbine gas inlet and the pre-combustion chamber of the thrust chamber.

[0012] Optionally, an oxygen main valve is connected to the pipeline between the first outlet and the thrust chamber, and the oxygen main valve is used to control the opening degree of the pipeline between the first outlet and the thrust chamber.

[0013] Optionally, an oxygen auxiliary valve is connected to the pipeline between the second outlet and the combustion device, the oxygen auxiliary valve being used to control the opening degree of the pipeline between the second outlet and the combustion device.

[0014] Optionally, a fuel main valve is connected to the pipeline between the fuel pump outlet and the thrust chamber, and the fuel main valve is used to control the opening degree of the pipeline between the fuel pump outlet and the thrust chamber.

[0015] Based on the deep throttling system for an open-cycle liquid rocket engine proposed in this application, during engine operation, oxidizer first flows out of the oxygen tank, enters the oxidizer pump through the oxidizer pump inlet, and is then delivered to the thrust chamber from the first outlet of the oxidizer pump, and to the combustion device (i.e., the aforementioned thrust chamber or generator) from the second outlet of the oxidizer pump. Simultaneously, fuel flows out of the fuel tank, enters the fuel pump through the fuel pump inlet, and is then delivered to the thrust chamber from the fuel pump outlet. In the thrust chamber, fuel and oxidizer combust to generate gas, forming thrust to propel the rocket. Simultaneously, in the combustion device, fuel and oxidizer also combust to generate gas, forming thrust to drive the turbine, which in turn drives the connected oxidizer pump and fuel pump, achieving continuous delivery of oxidizer and fuel. When it is necessary to adjust the engine's operating conditions to achieve deep throttling, only the opening of the gas regulating valve between the turbine gas inlet and the combustion device needs to be adjusted. For example, reducing the opening of the gas regulating valve increases the flow resistance of the gas, leading to a decrease in the gas flow rate into the turbine and consequently reducing the turbine's power. This reduced turbine power also decreases the rotational speeds of the oxidizer and fuel pumps, further reducing the flow of fuel and oxidizer into the thrust chamber. This lowers the engine's operating conditions, ultimately achieving low-operational-condition operation and realizing deep throttling of the open-cycle liquid rocket engine. The entire adjustment process requires no complex control of the oxidizer and fuel paths; it can be accomplished simply by adjusting the flow rate of the gas entering the turbine. This simple, efficient, and easy-to-implement control method also simplifies the engine system. Attached Figure Description

[0016] Figure 1 A schematic diagram illustrating the connection relationships of various components in a deep throttling system for an open-circulation liquid rocket engine, provided as an embodiment of this application; Figure 2 This is a schematic diagram showing the connection relationship of various components of another open-circulation liquid rocket engine deep throttling system provided in an embodiment of this application.

[0017] In the diagram, 1 is the thrust chamber; 2 is the main oxygen valve; 3 is the secondary oxygen valve; 4 is the secondary fuel valve; 5 is the oxidizer pump; 6 is the fuel pump; 7 is the turbine; 8 is the generator; 9 is the gas regulating valve; and 10 is the main fuel valve.

[0018] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0019] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0020] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0021] In this invention, unless otherwise explicitly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0022] Furthermore, if the embodiments of this invention involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the meaning of "and / or" throughout the text includes three parallel solutions; for example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this invention.

[0023] Please see Figure 1 , Figure 2 This application provides a deep throttling system for an open-cycle liquid rocket engine. The system includes a thrust chamber 1, an oxidizer pump 5, a fuel pump 6, and a turbine 7. The thrust chamber 1 mixes fuel and oxidizer for combustion to generate fuel gas, thus creating thrust. The oxidizer pump 5 includes an oxidizer pump inlet and an oxidizer pump outlet. The oxidizer pump inlet is connected to an oxygen storage tank via a pipe. The oxidizer pump outlet includes a first outlet and a second outlet. The first outlet is connected to the thrust chamber 1 via a pipe and is used to deliver oxidizer from the oxygen storage tank to the thrust chamber 1. The second outlet is connected to a combustion device via a pipe and is used to deliver oxidizer from the oxygen storage tank to the combustion device. The combustion device mixes fuel and oxidizer for combustion to generate fuel gas, thus creating fuel gas. The combustion device generates thrust, and the combustion device is either a thrust chamber 1 or a generator 8. The fuel pump 6 includes a fuel pump inlet and a fuel pump outlet. The fuel pump inlet is connected to the fuel tank through a pipe, and the fuel pump outlet is connected to the thrust chamber 1 through a pipe. The fuel pump outlet is used to transport fuel from the fuel tank to the thrust chamber 1. The turbine 7 includes a turbine gas inlet and a turbine exhaust port. The turbine gas inlet is connected to the combustion device through a pipe and is used to drive the turbine 7 to work using the thrust generated by the combustion device. A gas regulating valve 9 is installed on the pipe between the turbine gas inlet and the combustion device. The gas regulating valve 9 is used to control the opening of the pipe between the turbine gas inlet and the combustion device. The turbine exhaust port is used to discharge the gas that has passed through the turbine 7. The turbine 7 is used to drive the oxidizer pump 5 and the fuel pump 6 to work.

[0024] In this embodiment, during engine operation, oxidizer first flows out of the oxygen tank, enters the oxidizer pump 5 through the oxidizer pump inlet, and is then delivered to the thrust chamber 1 from the first outlet of the oxidizer pump 5, and to the combustion device (i.e., the aforementioned thrust chamber 1 or generator 8) from the second outlet of the oxidizer pump 5. Simultaneously, fuel flows out of the fuel tank, enters the fuel pump 6 through the fuel pump inlet, and is then delivered to the thrust chamber 1 from the fuel pump outlet. In the thrust chamber 1, fuel and oxidizer combust to generate gas, forming thrust to propel the rocket launch. Simultaneously, in the combustion device, fuel and oxidizer also combust to generate gas, forming thrust to drive the turbine 7, which in turn drives the connected oxidizer pump 5 and fuel pump 6, achieving continuous delivery of oxidizer and fuel. When it is necessary to adjust the engine's operating conditions to achieve deep throttling, only the opening of the gas regulating valve 9 between the turbine gas inlet and the combustion device needs to be adjusted. For example, reducing the opening of the gas regulating valve 9 increases the flow resistance of the gas, leading to a decrease in the gas flow rate into turbine 7 and a corresponding reduction in turbine 7 power. This reduction in turbine 7 power also decreases the rotational speeds of oxidizer pump 5 and fuel pump 6, further reducing the flow of fuel and oxidizer into thrust chamber 1. This lowers the engine's operating conditions, ultimately achieving low-operational-condition operation and realizing deep throttling of the open-cycle liquid rocket engine. The entire adjustment process requires no complex control of the oxidizer and fuel paths; it can be accomplished simply by adjusting the flow rate of the gas entering turbine 7. The control method is simple, efficient, and easy to implement, while also simplifying the engine system.

[0025] Furthermore, in some possible implementations, when the combustion device is a generator 8, the generator 8 is located on one side of the thrust chamber 1, and the thrust generated by the thrust chamber 1 is used to drive the rocket launch.

[0026] The generator 8 is used to mix fuel and oxidant and burn them to generate gas, which generates thrust to drive the turbine 7, thereby providing power to the oxidant pump 5 and the fuel pump 6, ensuring the continuous delivery of oxidant and fuel.

[0027] It should be understood that, in this embodiment, the oxidant required by generator 8 can be delivered through the second outlet of oxidant pump 5.

[0028] Optionally, the fuel required by generator 8 can be delivered by fuel pump 6 or by other means, without limitation.

[0029] When the fuel required by the generator 8 is delivered by the fuel pump 6, the fuel pump 6 may also include a fuel pump auxiliary outlet, which is connected to the generator 8 by a pipeline. The fuel pump auxiliary outlet is used to deliver fuel from the fuel tank to the generator 8.

[0030] Based on this, during engine operation, oxidizer flows from the oxygen tank, enters oxidizer pump 5 through the oxidizer pump inlet, and is then delivered to thrust chamber 1 from the first outlet of oxidizer pump 5 and to generator 8 from the second outlet of oxidizer pump 5. Simultaneously, fuel flows from the fuel tank, enters fuel pump 6 through the fuel pump inlet, and is then delivered to thrust chamber 1 from the fuel pump outlet. In thrust chamber 1, fuel and oxidizer combust to generate gas, forming thrust to propel the rocket. Simultaneously, in generator 8, fuel and oxidizer also combust to generate gas, driving turbine 7, which in turn drives the connected oxidizer pump 5 and fuel pump 6, achieving continuous delivery of oxidizer and fuel. When it is necessary to adjust the engine's operating conditions to achieve deep throttling, only the opening of the gas regulating valve 9 between the turbine gas inlet and generator 8 needs to be adjusted. For example, if the opening of the gas regulating valve 9 is reduced, the flow resistance of the gas regulating valve 9 to the gas will increase, resulting in a reduction in the gas flow rate entering the turbine 7, and the power of the turbine 7 will decrease accordingly. After the power of the turbine 7 decreases, the rotation speed of the oxidizer pump 5 and the fuel pump 6 will also decrease, which in turn reduces the flow rate of fuel and oxidizer entering the thrust chamber 1, reduces the engine operating conditions, and ultimately achieves low-condition operation, realizing deep throttling of the open-cycle liquid rocket engine.

[0031] Please see Figure 2 In some possible implementations, a fuel auxiliary valve 4 can be connected to the pipeline between the fuel pump auxiliary outlet and the generator 8. The fuel auxiliary valve 4 is used to control the opening degree of the pipeline between the fuel pump auxiliary outlet and the generator 8.

[0032] In this embodiment, by connecting a fuel auxiliary valve 4 to the pipeline between the fuel pump auxiliary outlet and the generator 8, precise control of the amount of fuel entering the generator 8 can be achieved. The opening degree of the fuel auxiliary valve 4 directly determines the flow area of ​​the pipeline between the fuel pump auxiliary outlet and the generator 8, thereby controlling the fuel flow rate. When it is necessary to increase the fuel supply in the generator 8, the opening degree of the fuel auxiliary valve 4 can be increased to allow more fuel to flow into the generator 8; conversely, when it is necessary to reduce the fuel supply, the fuel auxiliary valve 4 can be decreased or closed. By flexibly adjusting the opening degree of the fuel auxiliary valve 4, it can be ensured that the engine maintains optimal performance output under various operating conditions.

[0033] Furthermore, in some possible implementations, when the combustion device is a thrust chamber 1, the thrust generated by the thrust chamber 1 is used partly to drive the rocket launch and partly to drive the turbine 7 to work.

[0034] Based on this, during engine operation, oxidizer flows from the oxygen tank, enters oxidizer pump 5 through the oxidizer pump inlet, and is then delivered to thrust chamber 1 from both the first and second outlets of oxidizer pump 5. Simultaneously, fuel flows from the fuel tank, enters fuel pump 6 through the fuel pump inlet, and is then delivered to thrust chamber 1 from the fuel pump outlet. In thrust chamber 1, fuel and oxidizer combust to generate combustion gases, forming thrust that propels the rocket for launch. Simultaneously, some of the combustion gases generated in thrust chamber 1 drive turbine 7, which in turn drives the connected oxidizer pump 5 and fuel pump 6, ensuring continuous delivery of oxidizer and fuel. When it is necessary to adjust the engine's operating conditions to achieve deep throttling, only the opening of the gas regulating valve 9 between the turbine gas inlet and thrust chamber 1 needs to be adjusted. For example, if the opening of the gas regulating valve 9 is reduced, the flow resistance of the gas regulating valve 9 to the gas will increase, resulting in a reduction in the gas flow rate entering the turbine 7, and the power of the turbine 7 will decrease accordingly. After the power of the turbine 7 decreases, the rotation speed of the oxidizer pump 5 and the fuel pump 6 will also decrease, which in turn reduces the flow rate of fuel and oxidizer entering the thrust chamber 1, reduces the engine operating conditions, and ultimately achieves low-condition operation, realizing deep throttling of the open-cycle liquid rocket engine.

[0035] It should be noted that thrust chamber 1 not only performs the core function of mixing and burning fuel and oxidizer to generate thrust, but also cleverly utilizes a portion of the thrust to drive turbine 7. This design achieves efficient energy utilization, ensuring both the rocket's propulsion requirements and providing power support for the engine's internal circulation system. In actual operation, by precisely controlling the distribution ratio of the gas in thrust chamber 1, the amount of gas driving turbine 7 can be flexibly adjusted, thereby achieving fine-tuning of engine operating conditions and ensuring that the engine maintains optimal operating status at different stages.

[0036] Furthermore, in some possible implementations, the thrust chamber 1 includes a main combustion chamber and a pre-combustion chamber, with a first outlet connected to the main combustion chamber of the thrust chamber 1 via a pipe and a second outlet connected to the pre-combustion chamber of the thrust chamber 1 via a pipe.

[0037] In this embodiment, the thrust chamber 1 adopts a dual-chamber design with a main combustion chamber and a pre-combustion chamber. This structure allows for more precise control of the fuel-oxidant mixing and combustion process. Specifically, the connection between the first outlet and the main combustion chamber ensures that most of the oxidant can directly enter the main combustion chamber and fully combust with the fuel, thereby generating powerful thrust. The connection between the second outlet and the pre-combustion chamber allows a small portion of the oxidant to undergo preliminary combustion with the fuel in the pre-combustion chamber, generating fuel-rich gas. This gas then enters the main combustion chamber for supplementary combustion, further improving combustion efficiency and thrust output. This dual-chamber design not only optimizes the combustion process but also provides favorable conditions for deep throttling of the engine. By adjusting the flow ratio of the first and second outlets, the combustion intensity in the main combustion chamber and the pre-combustion chamber can be flexibly controlled, thereby achieving precise adjustment of the engine operating conditions.

[0038] Furthermore, in some possible implementations, the turbine gas inlet is connected to the pre-combustion chamber of the thrust chamber 1 via a pipeline, and the gas regulating valve 9 is located between the turbine gas inlet and the pre-combustion chamber of the thrust chamber 1.

[0039] Specifically, the turbine gas inlet is connected to the pre-combustion chamber of thrust chamber 1 via a pipeline, and the gas regulating valve 9 is positioned between the two. This layout has significant advantages. During engine operation, the fuel and oxidizer undergo preliminary combustion in the pre-combustion chamber, producing fuel-rich gas. A portion of this gas flows to the turbine gas inlet through the connecting pipeline, while the gas regulating valve 9 plays a crucial role in flow control.

[0040] Please see Figure 1 , Figure 2 In some possible implementations, an oxygen main valve 2 is connected to the pipeline between the first outlet and the thrust chamber 1. The oxygen main valve 2 is used to control the opening degree of the pipeline between the first outlet and the thrust chamber 1.

[0041] The oxygen main valve 2 is designed to precisely regulate the oxidant flow rate into the thrust chamber 1 from the first outlet, thereby flexibly adjusting the oxidant supply according to different engine operating stages and conditions. This regulation mechanism helps optimize engine combustion efficiency, improve overall performance, and ensure stable engine operation under various working conditions.

[0042] Please see Figure 1 , Figure 2 In some possible implementations, an oxygen auxiliary valve 3 is connected to the pipe between the second outlet and the combustion device. The oxygen auxiliary valve 3 is used to control the opening degree of the pipe between the second outlet and the combustion device.

[0043] In some embodiments, an oxygen auxiliary valve 3 is connected to the pipe between the second outlet and the combustion device. The presence of the oxygen auxiliary valve 3 provides the engine with an additional means of oxidant regulation; by controlling the opening degree of the oxygen auxiliary valve 3, the oxidant flow rate entering the combustion device can be further fine-tuned. The configuration of the oxygen auxiliary valve 3 allows the engine to control the oxidant supply more flexibly and precisely in response to changes in different operating conditions.

[0044] Please see Figure 1 , Figure 2 In some possible implementations, a fuel main valve 10 is connected to the pipeline between the fuel pump outlet and the thrust chamber 1. The fuel main valve 10 is used to control the opening of the pipeline between the fuel pump outlet and the thrust chamber 1.

[0045] Specifically, a fuel main valve 10 is connected to the pipeline between the fuel pump outlet and the thrust chamber 1. The fuel main valve 10 is mainly used to control the fuel flow rate from the fuel pump outlet into the thrust chamber 1. By adjusting the opening of the fuel main valve 10, it can be ensured that the fuel and oxidizer are mixed and burned in an appropriate ratio within the thrust chamber 1, thereby achieving efficient engine operation.

[0046] The above are merely preferred embodiments of this application and do not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.

Claims

1. An open cycle liquid rocket engine deep throttling system, characterized by, The application relates to a rocket engine, comprising: a thrust chamber (1) for generating thrust by burning fuel and oxidizer; an oxidizer pump (5) comprising an oxidizer pump inlet and an oxidizer pump outlet, the oxidizer pump inlet being connected to an oxidizer tank via a pipe, the oxidizer pump outlet comprising a first outlet and a second outlet, the first outlet being connected to the thrust chamber (1) via a pipe for delivering oxidizer from the oxidizer tank to the thrust chamber (1), the second outlet being connected to a combustion device via a pipe for delivering oxidizer from the oxidizer tank to the combustion device, the combustion device being used for burning fuel and oxidizer to generate thrust, the combustion device being the thrust chamber (1) or a generator (8); a fuel pump (6) comprising a fuel pump inlet and a fuel pump outlet, the fuel pump inlet being connected to a fuel tank via a pipe, the fuel pump outlet being connected to the thrust chamber (1) via a pipe for delivering fuel from the fuel tank to the thrust chamber (1); a turbine (7) comprising a turbine gas inlet and a turbine exhaust, the turbine gas inlet being connected to the combustion device via a pipe for driving the turbine (7) to work by using the thrust generated by the combustion device, a gas regulating valve (9) being arranged on the pipe between the turbine gas inlet and the combustion device, the gas regulating valve (9) being used for controlling the opening degree of the pipe between the turbine gas inlet and the combustion device, the turbine exhaust being used for discharging gas after passing through the turbine (7); wherein the turbine (7) is used for driving the oxidizer pump (5) and the fuel pump (6) to work.

2. The open cycle liquid rocket engine deep throttling system of claim 1, wherein, In the case that the combustion device is the generator (8), the generator (8) is arranged on one side of the thrust chamber (1), and the thrust generated by the thrust chamber (1) is used for driving the rocket to launch.

3. The open cycle liquid rocket engine deep throttling system of claim 2, wherein, The fuel pump (6) further comprises a fuel pump additional outlet, the fuel pump additional outlet being connected to the generator (8) via a pipe, and the fuel pump additional outlet is used for delivering fuel from the fuel tank to the generator (8).

4. The open cycle liquid rocket engine deep throttling system of claim 3, wherein, A fuel auxiliary valve (4) is connected to the pipe between the fuel pump additional outlet and the generator (8), and the fuel auxiliary valve (4) is used for controlling the opening degree of the pipe between the fuel pump additional outlet and the generator (8).

5. The open cycle liquid rocket engine deep throttling system of claim 1, wherein, In the case that the combustion device is the thrust chamber (1), part of the thrust generated by the thrust chamber (1) is used for driving the rocket to launch, and the other part is used for driving the turbine (7) to work.

6. The open cycle liquid rocket engine deep throttling system of claim 5, wherein, The thrust chamber (1) comprises a main combustion chamber and a pre-combustion chamber, the first outlet being connected to the main combustion chamber of the thrust chamber (1) via a pipe, and the second outlet being connected to the pre-combustion chamber of the thrust chamber (1) via a pipe.

7. The open cycle liquid rocket engine deep throttling system of claim 6, wherein, The turbine gas inlet is connected to the pre-combustion chamber of the thrust chamber (1) via a pipe, and the gas regulating valve (9) is arranged between the turbine gas inlet and the pre-combustion chamber of the thrust chamber (1).

8. The open cycle liquid rocket engine deep throttling system of any one of claims 1 to 7, wherein, An oxygen main valve (2) is connected to the pipeline between the first outlet and the thrust chamber (1), and is used to control the opening size of the pipeline between the first outlet and the thrust chamber (1).

9. The open cycle liquid rocket engine deep throttling system of any one of claims 1 to 7, wherein, An oxygen auxiliary valve (3) is connected to the pipeline between the second outlet and the combustion device, and is used to control the opening size of the pipeline between the second outlet and the combustion device.

10. The open cycle liquid rocket engine deep throttling system of any one of claims 1 to 7, wherein, A fuel main valve (10) is connected to the pipeline between the fuel pump outlet and the thrust chamber (1), and is used to control the opening size of the pipeline between the fuel pump outlet and the thrust chamber (1).

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