CN114136635B

CN114136635B - Large-flow quick-response solid-liquid rocket engine ground conveying system

Info

Publication number: CN114136635B
Application number: CN202111477389.5A
Authority: CN
Inventors: 田辉; 蔡国飙; 谭广; 张源俊; 孟祥宇; 魏天放; 辜小明
Original assignee: Beihang University
Current assignee: Beihang University
Priority date: 2021-12-06
Filing date: 2021-12-06
Publication date: 2022-08-23
Anticipated expiration: 2041-12-06
Also published as: CN114136635A

Abstract

The application relates to the technical field of aerospace, in particular to a large-flow fast response solid-liquid rocket engine ground conveying system. The large-flow quick-response ground conveying system of the solid-liquid rocket engine comprises a propellant storage unit, a high-pressure supply unit and a low-pressure supply unit; the output end of the propellant storage unit is respectively communicated with the high-pressure supply unit and the low-pressure supply unit; the output ends of the high-pressure supply unit and the low-pressure supply unit are respectively communicated with the combustion chamber through a main path. The high-pressure supply unit and the low-pressure supply unit are of a parallel arrangement structure, the high-pressure supply unit and the low-pressure supply unit are combined together ingeniously, different supply units can be flexibly switched in the test process, the low-pressure working condition of the combustion chamber can be met, the high-pressure working condition of the combustion chamber can be met, and therefore the efficiency of the large-flow quick-response solid-liquid rocket engine ground conveying system is improved.

Description

Large-flow quick-response solid-liquid rocket engine ground conveying system

Technical Field

The application relates to the technical field of aerospace, in particular to a ground conveying system of a large-flow quick-response solid-liquid rocket engine.

Background

At present, a ground conveying system of a solid-liquid hybrid rocket engine comprises a gas path and a liquid path. The gas circuit has two functions, namely, the gas circuit is used as a pressure increasing road to increase the pressure of the storage tank, so that the storage tank keeps a certain pressure; and secondly, the device is used as a blowing pipeline, a large amount of inert nitrogen is blown into the engine, so that the engine is blown out, and the safe extinguishing of the propellant after the ignition test is finished is ensured. The liquid path is usually pressurized by a storage tank, liquid propellant is sent into a combustion chamber through a series of valves to react with solid propellant, and in order to improve the pressure intensity in the combustion chamber, an electric pump is usually added into the liquid path to pressurize low-pressure liquid in the storage tank again, so that the liquid propellant is ensured to enter the high-pressure combustion chamber at a certain flow rate and then react.

However, because the pressure working conditions of the combustion chamber are different, when the pressure of the combustion chamber is lower, the efficiency of the electric pump conveying system is not high, and the electric pump conveying system cannot meet the condition that the pressure of the combustion chamber is lower.

Therefore, a large-flow quick-response ground conveying system of the solid-liquid rocket engine is needed to solve the technical problems in the prior art to a certain extent.

Disclosure of Invention

An object of the application is to provide a large-traffic quick response solid-liquid rocket engine ground conveying system to adopt the electric pump conveying system among the solution prior art to a certain extent, can't satisfy the technical problem of the lower operating mode of combustion chamber pressure.

The application provides a large-flow quick-response solid-liquid rocket engine ground conveying system which is used for propelling a propellant to a combustion chamber; the large-flow quick-response solid-liquid rocket engine ground conveying system comprises a propellant storage unit, a high-pressure supply unit and a low-pressure supply unit;

the output end of the propellant storage unit is respectively communicated with the high-pressure supply unit and the low-pressure supply unit;

the output ends of the high-pressure supply unit and the low-pressure supply unit are respectively communicated with the combustion chamber through a main path.

In the above technical solution, further, the high pressure supply unit includes a high pressure line;

the high-pressure pipeline is sequentially arranged on the first electromagnetic valve, the first pressure sensor, the electric pump, the second pressure sensor and the first one-way valve;

the first solenoid valve is adjacent the propellant storage unit and the first one-way valve is adjacent the combustion chamber.

In the above technical solution, further, the low pressure supply unit includes a low pressure pipeline;

a second electromagnetic valve and a second one-way valve are sequentially arranged on the low-pressure pipeline; the second solenoid valve is adjacent the propellant storage unit and the second one-way valve is adjacent the combustion chamber.

In the above technical solution, further, the propellant storage unit includes a tank and a propellant supply line;

the propellant supply pipeline is sequentially provided with a filter, an electric ball valve, a first hand valve and a flowmeter; the filter is close to the tank and the flow meter is close to the high pressure supply unit or the low pressure supply unit;

and the storage tank is provided with a third pressure sensor and a filling and discharging valve.

In the above technical solution, further, the main path is sequentially provided with a first regulating valve, a third electromagnetic valve, a third check valve and a sixth pressure sensor;

the first regulating valve is close to the output end of the high-pressure supply unit or the output end of the low-pressure supply unit; the sixth pressure sensor is proximate the combustion chamber.

In the above technical solution, further, the air conditioner further comprises a pressurization unit; the pressurizing unit comprises a gas cylinder and a pressurizing pipeline, wherein the input end of the pressurizing pipeline is communicated with the gas cylinder, and the output end of the pressurizing pipeline is communicated with the propellant storage unit;

a fourth pressure sensor, a fourth electromagnetic valve, a first pressure reducer, a second hand valve and a fifth electromagnetic valve are sequentially arranged on the pressure increasing pipeline;

the fourth pressure sensor is close to the gas cylinder, and the fifth electromagnetic valve is close to the propellant storage unit.

In the above technical solution, further, the apparatus further comprises a blowing unit, wherein the blowing unit comprises a blowing pipeline;

the input end of the blowing pipeline is communicated with the pressurization pipeline, and the output end of the blowing pipeline is communicated with the combustion chamber;

the blowing pipeline is sequentially provided with a third pressure sensor, a third hand valve, a fifth pressure sensor, a sixth electromagnetic valve and a fourth one-way valve;

the third pressure sensor is close to the fourth solenoid valve, and the fourth check valve is close to the combustion chamber.

In the above technical solution, further, the apparatus further comprises a circulation unit, wherein the circulation unit comprises a circulation pipeline;

one end of the circulating pipeline is communicated with the propellant storage unit, and the other end of the circulating pipeline is communicated with the main pipeline;

a fifth one-way valve, a seventh electromagnetic valve, a second regulating valve and a buffer are sequentially arranged on the circulating pipeline;

the fifth one-way valve is adjacent the propellant storage unit and the buffer is adjacent the high pressure supply unit.

In the above technical solution, further, the system further comprises an auxiliary unit, wherein the auxiliary unit comprises an auxiliary pipeline;

an eighth electromagnetic valve close to the seventh electromagnetic valve and a fifth one-way valve close to the main path are arranged on the auxiliary pipeline.

In the above technical solution, further, a bypass line is further included; one end of the bypass pipeline is communicated with the main pipeline, and a fourth hand valve is arranged on the bypass pipeline.

Compared with the prior art, the beneficial effect of this application is:

the ground conveying system of the large-flow quick-response solid-liquid rocket engine is used for propelling a propellant to a combustion chamber; the large-flow quick-response ground conveying system of the solid-liquid rocket engine comprises a propellant storage unit, a high-pressure supply unit and a low-pressure supply unit;

Specifically, the high-pressure supply unit and the low-pressure supply unit are of a parallel arrangement structure, the high-pressure supply unit and the low-pressure supply unit are ingeniously combined together, different supply units can be flexibly switched in a test process, the low-pressure working condition of a combustion chamber can be met, the high-pressure working condition of the combustion chamber can be met, and therefore the efficiency of the large-flow quick-response solid-liquid rocket engine ground conveying system is improved.

Drawings

In order to more clearly illustrate the detailed description of the present application or the technical solutions in the prior art, the drawings needed to be used in the detailed description of the present application or the prior art description will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative efforts.

FIG. 1 is a schematic structural diagram of a large-flow fast-response ground conveying system of a solid-liquid rocket engine provided in an embodiment of the present application;

FIG. 2 is a schematic structural diagram of a large-flow fast-response ground conveying system of a solid-liquid rocket engine provided in the second embodiment of the present application;

fig. 3 is a schematic structural diagram of a large-flow fast-response solid-liquid rocket engine ground conveying system provided in the third embodiment of the present application;

fig. 4 is a schematic structural diagram of a large-flow fast-response ground conveying system of a solid-liquid rocket engine provided in the fourth embodiment of the present application.

Reference numerals: 1-a gas cylinder; 2-a fourth pressure sensor; 3-a fourth solenoid valve; 4-a second stress-reducer; 5-a third hand valve; 6-a fifth pressure sensor; 7-a sixth solenoid valve; 8-a fourth one-way valve; 9-a first pressure reducer; 10-a second hand valve; 11-a fifth solenoid valve; 12-a third pressure sensor; 13-a safety valve; 14-a storage tank; 15-fill purge valve; 16-a filter; 17-an electric ball valve; 18-a first hand valve; 19-a flow meter; 20-a second solenoid valve; 21-a second one-way valve; 22-a first solenoid valve; 23-a first pressure sensor; 24-an electric pump; 25-a second pressure sensor; 26-a first one-way valve; 27-a buffer; 28-a first regulating valve; 29-a third solenoid valve; 30-a third one-way valve; 31-a sixth pressure sensor; 32-fourth hand valve; 33-a second regulating valve; 34-a seventh solenoid valve; 35-a fifth one-way valve; 36-eighth solenoid valve; 37-a sixth one-way valve; 101-high pressure line; 102-main path; 103-low pressure line; 104-a propellant supply line; 105-a booster circuit; 106-blow off line; 108-circulation line; 109-auxiliary line; 110-a bypass line; 800-combustion chamber.

Detailed Description

The technical solutions of the present application will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are only some embodiments of the present application, but not all embodiments.

The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present application, as presented in the figures, is not intended to limit the scope of the claimed application, but is merely representative of selected embodiments of the application.

All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.

Example one

A mass flow fast response hybrid rocket engine ground delivery system according to some embodiments of the present application is described below with reference to fig. 1.

In this embodiment, a high flow, fast response hybrid rocket engine ground delivery system is provided for propelling a propellant into the combustion chamber 800; the large-flow quick-response solid-liquid rocket engine ground conveying system comprises a propellant storage unit, a high-pressure supply unit and a low-pressure supply unit;

the propellant storage unit is used for storing a propellant (the propellant refers to a liquid oxidizer), and the output end of the propellant storage unit can be respectively communicated with the high-pressure supply unit and the low-pressure supply unit; the output ends of the high-pressure supply unit and the low-pressure supply unit are respectively communicated with the combustion chamber 800 through a main path 102; in the application, the high-pressure supply unit and the low-pressure supply unit are of a parallel arrangement structure, the high-pressure supply unit and the low-pressure supply unit are skillfully combined together, different supply units can be flexibly switched in the test process, the working condition of 800 low pressure in the combustion chamber can be met, and the working condition of 800 high pressure in the combustion chamber can be met, so that the efficiency of the ground conveying system of the large-flow quick-response solid-liquid rocket engine is improved.

Specifically, the main path 102 is provided with a first regulating valve 28, a third electromagnetic valve 29, a third one-way valve 30 and a sixth pressure sensor 31 in sequence; the first regulating valve 28 is close to the output of the high-pressure supply unit or the output of the low-pressure supply unit; the sixth pressure sensor 31 is close to the combustion chamber 800.

Further, the first regulating valve 28 is capable of regulating the flow of liquid oxidant on the main circuit 102.

Further, the third solenoid valve 29 is able to control the opening and closing of the main circuit 102, that is to say the start and end of the ignition.

Further, the third check valve 30 is a valve capable of preventing the high pressure gas in the combustion chamber 800 from flowing backward, and preventing the liquid oxidizer in the combustion chamber 800 from reversely flowing into the high pressure supply unit and the low pressure supply unit.

Further, the first pressure sensor 23 serves as a pressure sensor in front of the combustion chamber 800, and can monitor the real-time pressure in the front of the combustion chamber 800.

Specifically, the large-flow fast-response solid-liquid rocket engine ground conveying system further comprises a bypass pipeline 110; one end of the bypass line 110 is communicated with the main line 102, and the bypass line 110 is provided with a fourth hand valve 32.

Further, fourth hand valve 32 is capable of venting gas trapped in main path 102 during filling of main path 102 with liquid oxidizer.

Specifically, the high-pressure supply unit includes a high-pressure line 101; one end of the high-pressure pipeline 101 is communicated with the propellant storage unit, and the other end of the high-pressure pipeline is communicated with the combustion chamber 800; the high-pressure pipeline 101 is sequentially provided with a first electromagnetic valve 22, a first pressure sensor 23, an electric pump 24, a second pressure sensor 25 and a first one-way valve 26; wherein the first solenoid valve 22 is located adjacent to the propellant storage unit and the first one-way valve 26 is located adjacent to the combustion chamber 800.

Further, the first electromagnetic valve 22 is a control switch of the high-pressure pipeline 101; when the first electromagnetic valve 22 is opened and the high-pressure pipeline 101 is opened, the high-pressure pipeline 101 where the electric pump 24 is located is started, the electric pump 24 is used for pressurizing the propellant, and the high-pressure propellant is sent to the combustion chamber 800.

Further, a first pressure sensor 23 is used to monitor the real time pressure of the propellant before the electric pump 24.

Further, the electric pump 24 is an energy input element of the entire high pressure supply unit, and the electric pump 24 can pressurize the low pressure propellant before the pump to the high pressure propellant, increasing the pressure potential energy of the propellant, thereby making the propellant have a high pressure and enter the combustion chamber 800 at the high pressure.

Further, a second pressure sensor 25 monitors the real-time pressure of the propellant after the electric pump 24.

Further, the first one-way valve 26 can prevent the propellant of the main circuit 102 from flowing backward into the electric pump 24. When the low pressure supply unit is activated and the high pressure supply unit is deactivated, there is a possibility of reverse flow of propellant from main circuit 102 into electric pump 24, and therefore it is necessary to provide first one-way valve 26 to prevent propellant from entering electric pump 24.

In summary, the high-pressure supply unit mainly includes a high-pressure pipeline 101, and a first electromagnetic valve 22, a first pressure sensor 23, an electric pump 24, a second pressure sensor 25, and a first check valve 26 that are disposed on the high-pressure pipeline 101. When the combustion chamber 800 is at a higher pressure and a higher flow rate, the high pressure line 101 is activated, the low pressure line 103 is deactivated, and propellant passes only through the high pressure line 101. After work pressurization by the electric pump 24, the propellant will be pushed into the high pressure combustion chamber 800 at a greater flow rate.

Specifically, the low pressure supply unit includes a low pressure pipe 103; one end of the low-pressure pipeline 103 is communicated with the propellant storage unit, and the other end is communicated with the combustion chamber 800; a second electromagnetic valve 20 and a second one-way valve 21 are sequentially arranged on the low-pressure pipeline 103; the second solenoid valve 20 is located close to the propellant storage unit and the second check valve 21 is located close to the combustion chamber 800.

Further, the second solenoid valve 20 can control the opening and closing of the low pressure line 103.

Further, the second check valve 21 can prevent the propellant from flowing backward.

In summary, the low-pressure line 103 mainly includes the second solenoid valve 20 and the second check valve 21. The low-pressure pipeline 103 is used as a bypass of the high-pressure pipeline 101 where the electric pump 24 is located, and can work when the combustion chamber 800 is in a low-chamber pressure working condition, the electric pump 24 and the high-pressure pipeline 101 where the electric pump is located are stopped, the second electromagnetic valve 20 is opened, and the low-pressure pipeline 103 is started.

In particular, the propellant storage unit comprises a tank 14 and a propellant feed line 104 communicating with the tank 14; the propellant supply pipeline 104 is sequentially provided with a filter 16, an electric ball valve 17, a first hand valve 18 and a flowmeter 19; the filter 16 is close to the tank 14, the flow meter 19 is close to the high pressure supply unit or the low pressure supply unit; the tank 14 is provided with a third pressure sensor 12 and a filling-out valve 15.

Further, the tank 14 is a pressure vessel capable of storing a certain amount of propellant (liquid oxidizer) and withstanding a certain pressure, and can smoothly squeeze the liquid oxidizer into a high-pressure supply unit or a low-pressure supply unit.

Further, the filling-up purge valve 15 can be used as a filling-up of the liquid oxidizing agent for filling up the storage tank 14 through the filling-up purge valve 15, and can be used as a discharge valve for discharging the remaining liquid oxidizing agent in the storage tank 14 through the filling-up purge valve 15.

Further, the filter 16 is used to filter solid contaminants entrained in the liquid oxidizer, prevent solid contaminants from clogging the propellant feed line 104, and prevent solid contaminants from entering the combustion chamber 800.

Further, the electric ball valve 17 has higher reliability and better sealing property, and can block the liquid oxidizing agent in the storage tank 14 before the start of the test to prevent the liquid oxidizing agent in the storage tank 14 from flowing out as a seal of the storage tank 14.

Further, the first hand valve 18 can serve as a backup switch for the propellant circuit, and the first hand valve 18 can be manually closed when either the first solenoid valve 22 or the second solenoid valve 20 fails or the flow of liquid oxidizer in the propellant feed line 104 is abnormal.

Further, the flow meter 19 is able to monitor the real time flow rate of the propellant supply line 104 to ensure that the flow rate of the liquid oxidizer reaches the target flow rate value.

Example two

A mass flow fast response hybrid rocket engine ground delivery system according to some embodiments of the present application is described below with reference to fig. 2.

In this embodiment, the mass flow fast response solid-liquid rocket engine ground conveying system further comprises a pressurization unit; the pressurizing unit comprises a gas cylinder 1 and a pressurizing pipeline 105 communicated with the gas cylinder 1, wherein the input end of the pressurizing pipeline 105 is communicated with the gas cylinder 1, and the output end of the pressurizing pipeline 105 is communicated with the propellant storage unit;

a fourth pressure sensor 2, a fourth electromagnetic valve 3, a first pressure reducer 9, a second hand valve 10 and a fifth electromagnetic valve 11 are sequentially arranged on the pressurization pipeline 105; the fourth pressure sensor 2 is close to the gas cylinder 1, and the fifth electromagnetic valve 11 is close to the propellant storage unit.

Further, the gas cylinder 1 is used for storing high-pressure nitrogen and can be used as a gas source; on one hand, the pressure-boosting air source is used for boosting the pressure of the storage tank 14, so that the storage tank 14 keeps a certain pressure; on the other hand, as a blowing air source, a large amount of inert high-pressure nitrogen is blown into the combustion chamber 800, so that the combustion chamber 800 is blown out, and the safe extinguishing of the propellant after the ignition test is finished is ensured.

Further, the fourth pressure sensor 2 is used to monitor the pressure in the gas cylinder 1, the gas cylinder 1 is at too high a pressure, and needs to be discharged from the blow-off line 106 (the blow-off line 106 is described in the third embodiment), and the gas cylinder 1 needs to be charged when the pressure in the gas cylinder 1 is too low.

Further, the fourth solenoid valve 3 is a master valve of the pressure-increasing line 105 as a master switch of the pressure-increasing line 105 and the blow-off line 106.

Further, the first pressure reducer 9 acts as an adjustable throttling element, capable of reducing the high pressure of the gas cylinder 1 to a pressure available to the tank 14.

Further, the second hand valve 10 is a manual switch for the pressure-increasing line 105, which controls the opening and closing of the tank 14, and is a backup switch, and once the fifth solenoid valve 11 is activated, the second hand valve 10 is activated.

Further, the fifth electromagnetic valve 11 is an electrically controlled switch of the pressure increasing line 105; before the test, the fifth solenoid valve 11 is opened, and the pressurization line 105 supplies high-pressure gas to the tank 14 containing the liquid oxidizer to pressurize the tank 14, and then the target tank 14 pressure is maintained, and the test is awaited. It is worth noting that: in the test process, the fifth electromagnetic valve 11 arranged in front of the storage tank 14 needs to be opened, and the pressurization pipeline 105 continuously supplies air to the storage tank 14 filled with the liquid oxidant, so that the storage tank 14 is always ensured to be stable in a certain pressure range, and the phenomenon that the gas space in the storage tank 14 is increased due to the outflow of a large amount of liquid propellant from the storage tank 14, so that the pressure of the storage tank 14 is greatly reduced is avoided.

Further, the third pressure sensor 12 can be monitoring the tank 14 pressure; in the process of adjusting the pressure of the storage tank 14, the second hand valve 10 arranged in front of the storage tank 14 and the fifth electromagnetic valve 11 arranged in front of the storage tank 14 need to be opened firstly, then the opening degree of the first pressure reducer 9 of the storage tank 14 is slowly increased, and simultaneously the reading of the third pressure sensor 12 of the storage tank 14 is visually observed and continuously adjusted until the real-time reading of the third pressure sensor 12 of the storage tank 14 is consistent with the pressure of the target storage tank 14.

Further, the safety valve 13 is used to ensure that the pressure of the tank 14 does not exceed a limit value, and if the pressure of the tank 14 exceeds the limit value, the safety valve 13 is opened, so as to reduce the pressure of the tank 14, and avoid the risk of explosion caused by error in operating the first pressure reducer 9 and over-high pressure of the tank 14.

To sum up, the pressurizing unit can ensure that the pressure in the storage tank 14 has a certain pressure, and ensure that when a large amount of liquid propellant flows out, the pressure in the storage tank 14 can be stable, so that the liquid propellant is in front of the electric pump 24 from the storage tank 14, or a certain pressure difference exists between the storage tank 14 and the combustion chamber 800, and the pressure difference can smoothly extrude the liquid propellant from the storage tank 14 and ensure a certain flow rate.

EXAMPLE III

A mass flow fast response hybrid rocket engine ground delivery system according to some embodiments of the present application is described below with reference to fig. 3.

In this embodiment, the mass flow fast response hybrid rocket engine ground conveying system further comprises a blowing unit, wherein the blowing unit comprises a blowing pipeline 106; the input end of the blowing-off pipeline 106 is communicated with the pressurization pipeline 105, and the output end of the blowing-off pipeline is communicated with the combustion chamber 800; the blowing pipeline 106 is sequentially provided with a second pressure reducer 4, a third hand valve 5, a fifth pressure sensor 6, a sixth electromagnetic valve 7 and a fourth one-way valve 8; the second pressure reducer 4 is close to the fourth solenoid valve 3, and the fourth check valve 8 is close to the combustion chamber 800.

Further, the second pressure reducer 4 acts as an adjustable throttling element, capable of reducing the high pressure of the gas cylinder 1 to a pressure available for the blow-off line 106.

Further, the third hand valve 5 is used as a manual switch of the blow-off line 106, controls the blow-off line 106 to be opened and closed, and is a standby switch and is activated when the sixth electromagnetic valve 7 fails.

Further, the second pressure reducer 4 is capable of monitoring the pressure of the blow-off line 106. In the process of adjusting the pressure of the blowing pipeline 106, the fourth electromagnetic valve 3 and the third hand valve 5 are firstly required to be opened, then the opening degree of the second pressure reducer 4 is slowly increased, meanwhile, the reading of the second pressure reducer 4 is visually observed, and the adjustment is continuously carried out until the real-time reading of the second pressure reducer 4 is consistent with the target blowing pressure.

Further, the sixth solenoid valve 7 serves as an electrically controlled switch for the blow-off line 106 during the test. And when the test is normally finished in the first condition, the sixth electromagnetic valve 7 is opened to blow off the solid-liquid engine, a large amount of nitrogen is fed into the combustion chamber 800, and the temperature of the combustion chamber 800 is reduced. The second condition is that the test is abnormal, and in case of emergency, the sixth electromagnetic valve 7 is opened, a large amount of inert nitrogen is introduced into the combustion chamber 800, the engine is blown out, and the emergency stop is carried out.

Further, the fourth check valve 8 can prevent the liquid oxidizer from flowing backward into the blow-off line 106. Ensuring that the blow-off line 106 can blow air into the combustion chamber 800 in only one direction.

In summary, the blowing unit ensures the normal supply of the blowing gas, so that the whole conveying system has the capability of sending a large amount of inert gas to the combustion chamber 800 at any time, thereby ensuring the safety of the test.

Example four

A mass flow fast response hybrid rocket engine ground delivery system according to some embodiments of the present application is described below with reference to fig. 4.

In this embodiment, the mass flow fast response solid-liquid rocket engine ground conveying system further comprises a circulation unit, wherein the circulation unit comprises a circulation pipeline 108; one end of the circulation pipeline 108 is communicated with the propellant storage unit, and the other end is communicated with the main pipeline 102; the circulating pipeline 108 is sequentially provided with a fifth one-way valve 35, a seventh electromagnetic valve 34, a second regulating valve 33 and a buffer 27; the fifth one-way valve 35 is located close to the propellant storage unit and the buffer 27 is located close to the high pressure supply unit.

Further, the second regulating valve 33 is identical in structure and function to the first regulating valve 28; the synchronous action in the test process, namely the test is kept consistent in real time when the test is started.

Further, the seventh solenoid valve 34 can control opening and closing of the circulation line 108.

Further, the fifth one-way valve 35 can prevent the reverse flow of liquid oxidizer, i.e., prevent the flow of liquid oxidizer fluid from the tank 14 into the recirculation line 108.

Further, the buffer 27 is used as a pressure vessel tank for buffering the liquid oxidant, so that the pressure in the circulation line 108 is more stable when the seventh solenoid valve 34 is opened instantaneously.

In summary, the circulation pipeline 108 of the electric pump 24, the first regulating valve 28 and the two-way regulating valve of the second regulating valve 33 are configured, so that the disadvantage that the electric pump 24 needs to be started slowly and stopped slowly is overcome, and the flow response capability of the pumping type conveying system of the electric pump 24 is greatly improved.

In this embodiment, the mass flow fast response solid-liquid rocket engine ground conveying system further comprises an auxiliary unit, the auxiliary unit comprises an auxiliary pipeline 109; an eighth solenoid valve 36, close to the seventh solenoid valve 34, and a sixth non-return valve 37, close to the main circuit 102, are provided on the auxiliary line 109.

Further, the eighth solenoid valve 36 can control the opening and closing of the auxiliary line 109.

Further, the sixth check valve 37 prevents the reverse flow of the liquid oxidizer, preventing the reverse flow of the liquid oxidizer from the main path 102 into the auxiliary path line.

In summary, by configuring the main path 102 and the auxiliary path pipeline, and configuring the regulating valves on the main path 102 and the auxiliary path pipeline, it can be ensured that any one of the main path 102 and the auxiliary path pipeline is instantly opened or the main path 102 and the auxiliary path pipeline are simultaneously opened, so that the regulating valves on the main path 102 and the auxiliary path pipeline can be simultaneously adjusted. Compare in traditional one way, the control range of the flow of two governing valve pipelines is wider, and real-time response ability is faster.

With reference to the first to fourth embodiments, the specific working process of the present application is as follows:

step 100: preparation work before the test: the tank 14 needs to be pressurized for filling, purge gas configuration, pipeline liquid oxidant filling.

Step 101: the tank 14 pressurized fill is a fill of a quantity of liquid propellant to the tank 14 through a fill bleed valve and the tank 14 is pressurized to the target tank 14 pressure through the first pressure reducer 9 of the pressurization line 105 such that the real time reading of the third pressure sensor 12 is the target tank 14 pressure.

Step 102: the blow-off gas configuration is to adjust the blow-off pressure to the target blow-off pressure via the second pressure reducer 4 such that the real-time reading of the fifth pressure sensor 6 is the target blow-off pressure.

Specifically, the process of filling the pipeline with liquid oxidant is as follows: the filling process is to fill the pipeline before the third electromagnetic valve 29 with liquid propellant, so as to prevent part of gas from accumulating in the pipeline. The preparations for the filling operation are pressurization of the tank 14 and valve preparation. Pressurizing the tank 14 pressurizes the tank 14 to a lower pressure to ensure that liquid oxidizer can be forced into the line. The valve preparation is to control the position of the relevant valve to be in place, so as to ensure that the liquid oxidant can be filled into each part of the pipeline in turn according to an expected route, and the main process is as follows: the third solenoid valve 29 is closed, the seventh solenoid valve 34 and the eighth solenoid valve 36 are closed, and the electric ball valve 17 and the first hand valve 18 are opened. The sequence of filling is low pressure line 103 filling, high pressure line 101 filling and auxiliary line 109 filling.

Step 103: filling the low-pressure pipeline 103: the first solenoid valve 22 is closed, the high pressure line 101 is deactivated, the second solenoid valve 20 is opened, and the low pressure line 103 is activated. The fourth hand valve 32 is then manually opened until the liquid oxidizer flowing into the environment is not contaminated with gas.

Step 104: filling the high-pressure pipeline 101: the second solenoid valve 20 is closed, the low pressure line 103 is deactivated, the first solenoid valve 22 is opened, and the high pressure line 101 is activated. The fourth hand valve 32 is then manually opened until the liquid oxidizer flowing into the environment is not contaminated with gas.

Step 105: auxiliary line 109 filling: firstly, closing the high-pressure pipeline 101, opening the low-pressure pipeline 103, namely a first electromagnetic valve 22, and opening a second electromagnetic valve 20; then, the opening degree of the first regulating valve 28 is regulated to a smaller opening degree, and the opening degree of the second regulating valve 33 is regulated to a larger opening degree, so that the main part of the liquid oxidant is ensured to smoothly flow into the auxiliary pipeline 109; finally, the eighth solenoid valve 36 and the fourth hand valve 32 are opened until the liquid oxidizer flowing into the outside is not mixed with gas.

Step 200: when the target flow rate of the combustion chamber 800 is small and the combustion chamber 800 pressure is small, the low pressure line 103 is activated and the high pressure line 101 is deactivated.

Step 201: preparation before the test: ensuring that the tank 14 is filled with liquid oxidizer and that the tank 14 pressure has been boosted to the target tank 14 pressure; ensuring that the pressure in the blow-off line 106 is adjusted to the target blow-off pressure; it is ensured that the low-pressure line 103, the high-pressure line 101, the main line 102 and the auxiliary line 109 are free of gas and filled with liquid propellant.

Step 202: when the flow rate is small and the pressure of the combustion chamber 800 is small, only the low-pressure pipeline 103 is started, and the whole conveying system is an extrusion type conveying system; specifically, the low-pressure line 103 is opened, the high-pressure line 101 is deactivated, the auxiliary line 109 and the circulation line 108 are deactivated, that is, the second solenoid valve 20 is opened, the first solenoid valve 22 is closed, and the eighth solenoid valve 36 and the seventh solenoid valve 34 are closed.

More specifically, the valve states of the pressurization line 105 before the test are: the second hand valve 10 is opened and the fifth solenoid valve 11 is opened. The valve state of the blow-off pipeline before the test is that the third hand valve 5 is opened and the sixth electromagnetic valve 7 is closed. The valve states of the low-pressure pipeline 103 before the test are as follows: the electric ball valve 17 is opened, the first hand valve 18 is opened, the second solenoid valve 20 is opened, and the third solenoid valve 29 is closed. The valves of the other paths are closed, namely the first electromagnetic valve 22 is closed, the seventh electromagnetic valve 34 is closed, the eighth electromagnetic valve 36 is closed, and the fourth hand valve 32 is closed.

Step 203: flow adjustment: and manually opening the fourth hand valve 32, gradually increasing the opening of the first regulating valve 28 in real time through the real-time reading of the flow meter 19 until the reading of the flow meter 19 is consistent with the target flow, closing the fourth hand valve 32, and finishing the flow regulation.

If the target flow rate is larger, the opening of the first regulating valve 28 is used to the maximum, and the flow rate still cannot reach the target flow rate, at this time, the auxiliary pipeline 109 may be started. The fluid is divided after passing through the low pressure pipeline 103, and simultaneously passes through the main pipeline 102 and the auxiliary pipeline 109, and finally flows into the combustion chamber 800 at the sum of the flow of the main pipeline 102 and the flow of the auxiliary pipeline 109. The auxiliary path eighth electromagnetic valve 36 is opened to adjust the opening degree of the first regulating valve 28 to the maximum, and then the opening degree of the second regulating valve 33 is gradually increased until the reading of the flowmeter 19 reaches the target flow rate. After that, the opening degrees of the first and

second control valves

28 and 33 are maintained, and the fourth hand valve 32 is closed to wait for the test.

Step 204: the test was started. Setting the ignition time of the solid-liquid engine from T0 to T1 seconds, namely igniting at T0, and closing the solid-liquid engine at T1. Before ignition, the reservoir 14 pressure and blow-off unit pressure are again verified and the valve status checked.

At the time T0, the third electromagnetic valve 29 is opened, and since the opening degree of the third electromagnetic valve 29 is in place, the flow rate is rapidly increased to the target flow rate;

the third electromagnetic valve 29 is closed at the time T1, and the flow rate is rapidly reduced to zero;

at the time of T1+0.1s, the sixth electromagnetic valve 7 is opened, a large amount of inert nitrogen is blown into the combustion chamber 800, the engine is flamed out and cooled, and the safety of the test is guaranteed.

And closing the sixth electromagnetic valve 7 after the engine is flamed out and the temperature is reduced. The test is now complete. Step 300: when the target flow rate is large and the pressure of the combustion chamber 800 is high, the flow control process is as follows: the flow rate is high, the pressure in the main path 102 is high, and the conventional extrusion type conveying system cannot meet the requirement, and an energy input element, namely the electric pump 24, needs to be added into the high-pressure pipeline 101. At this time, the system mode needs to be switched, the low-pressure pipeline 103 is not used, the high-pressure pipeline 101 is used, and the system is changed into a pumping type conveying system of an electric pump 24 type.

Step 301: preparation before testing. Ensuring that the tank 14 pressure has been boosted to the target tank 14 pressure after the tank 14 has been filled; ensuring that the pressure of the blowing unit is adjusted to the target blowing pressure; it is ensured that the low-pressure line 103, the high-pressure line 101, the main line 102 and the auxiliary line 109 are free of gas and filled with liquid propellant.

Step 302: the configuration of a pipeline valve before the test: the flow rate is large, the pressure of the combustion chamber 800 is high, the high-pressure pipeline 101 containing the electric pump 24 needs to be started, and the whole conveying system is a pumping type conveying system. The high-pressure pipeline 101 is started, the low-pressure pipeline 103 is stopped, the circulating pipeline 108 is started, the auxiliary pipeline 109 is started under the working condition of ultra-large flow, and the auxiliary pipeline 109 is stopped under the normal working condition. I.e., open the first solenoid valve 22 and the seventh solenoid valve 34 and close the second solenoid valve 20, the eighth solenoid valve 36 and the fourth hand valve 32.

The valve states of the pressurization line 105 before the test were: the second hand valve 10 is opened and the fifth solenoid valve 11 is opened.

The valve state of the blowing pipeline 106 before the test is that the third hand valve 5 is opened and the sixth electromagnetic valve 7 is closed.

The valve states of main path 102 before the test are: the electric ball valve 17 is opened, the first hand valve 18 is opened, the third electromagnetic valve 29 and the seventh electromagnetic valve 34 are opened, and the second electromagnetic valve 20 and the eighth electromagnetic valve 36 are closed.

Step 303: and (4) flow adjustment. The high-pressure pipeline 101 and the circulating pipeline 108 are opened, the rotating speed of the electric pump 24 and the opening degree of the second regulating valve 33 are gradually adjusted until the reading of the second pressure sensor 25 of the electric pump 24 meets the target pressure, and the reading of the flow meter 19 reaches the target flow rate. Namely, the electric ball valve 17, the first hand valve 18, the first electromagnetic valve 22 and the seventh electromagnetic valve 34 are opened, and the rest valves of the liquid path are all in a closed state. The electric pump 24 is started, and the rotating speed is gradually increased until the rear pressure of the electric pump 24 meets the requirement, namely the reading of the second pressure sensor 25 behind the electric pump 24 is larger than the set rear pressure of the electric pump 24. The pump speed is maintained and then the opening of the second regulating valve 33 is increased step by step until the flow reaches the set target flow, i.e. the flow meter 19 reads a set flow value. At this time, the opening of the second regulating valve 33 is increased, so that the flow rate is increased, and the pressure after the electric pump 24 is decreased, and at this time, the rotation speed of the electric pump 24 needs to be increased until the pressure after the electric pump 24 is higher than the set pressure after the electric pump 24. Subsequently, the opening degree of the second regulator valve 33 is adjusted without changing the rotation speed. By repeatedly adjusting the rotating speed of the electric pump 24 and the opening degree of the second regulating valve 33, the flow and the back pressure of the electric pump 24 are ensured to meet the requirements. The rotation speed of the electric pump 24 that meets the requirements at this time is recorded as W1, and the opening degree of the second regulator valve 33 is recorded as K1. The opening of the first control valve 28 is then likewise adjusted to K1, i.e. the overall dimensions, valve openings, etc. of the first control valve 28 and the second control valve 33 are identical.

Step 304: the test was started. Setting the ignition time of the solid-liquid engine from T0 to T1 seconds, namely igniting at T0, and closing the solid-liquid engine at T1. Before ignition, the pressure in the storage tank 14 and the pressure in the blowing unit are checked again, and the states of all valves are checked; the rotation speed of the electric pump 24 is ensured to be W1, and the opening degrees of the first regulating valve 28 and the second regulating valve 33 are both K1.

At time T0, the third solenoid valve 29 is opened and the seventh solenoid valve 34 is closed. Since the first and

second control valves

28, 33 are identical in terms of their structural dimensions and opening degrees, when the fluid flows to the combustion chamber 800 through the main path 102 instead of returning to the reservoir 14 through the circulation line 108, the reading of the flow meter 19 does not change, i.e., the flow rate is still the target flow rate, the pressure after the electric pump 24 is still greater than the set pressure after the electric pump 24, and both the flow rate and the pressure after the electric pump 24 meet the requirements. Thereafter, the flow rate of the propellant to the combustion chamber 800 quickly becomes the set target flow rate.

At time T1, the third solenoid valve 29 is closed, the seventh solenoid valve 34 is opened, the main path 102 flow rapidly drops to zero, and the circulation line 108 flow is switched to the target flow. Then, to avoid the electric pump 24 from being damaged, the electric pump 24 gradually reduces the rotation speed and stops slowly. After the electric pump 24 is stopped, the seventh electromagnetic valve 34 is closed.

And at the time of T1+0.1s, the sixth electromagnetic valve 7 is opened, a large amount of inert nitrogen is blown into the combustion chamber 800, the engine is flamed out and cooled, and the safety of the test is guaranteed.

And closing the sixth electromagnetic valve 7 after the engine is flamed out and the temperature is reduced. The test is now complete. In summary, the present application configures the circulation line 108 such that the line flow response is fast. On the one hand, the target flow rate can be reached quickly after the third solenoid valve 29 has opened. On the other hand, after ignition is finished, the flow can be rapidly reduced to zero, so that the problem of flow trailing is greatly relieved, namely, the problem that the flow cannot be immediately reset to zero is solved after ignition is finished. In the ignition time period from T0 to T1, the flow rate of the fuel flowing into the combustion chamber 800 is rapidly increased to the target flow rate and then rapidly decreased to 0, and the flow rate time curve is quite stable.

In addition, the main pipeline 102 and the auxiliary pipeline 109 are arranged, the two pipelines are both provided with the regulating valve, one pipeline or two pipelines can be opened instantly, the two pipelines are adjusted simultaneously, and the opening degree is unified. Compare in traditional single pass, the control range of the flow of two governing valve pipelines is wider real-time response ability faster.

Finally, it should be noted that: the above embodiments are only used for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art will understand that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present application.

Claims

1. A large-flow quick-response solid-liquid rocket engine ground conveying system is used for propelling a propellant to a combustion chamber; the ground conveying system of the large-flow quick-response solid-liquid rocket engine is characterized by comprising a propellant storage unit, a high-pressure supply unit and a low-pressure supply unit;

the output ends of the high-pressure supply unit and the low-pressure supply unit are respectively communicated with the combustion chamber through a main path;

the high-pressure supply unit comprises a high-pressure pipeline, one end of the high-pressure pipeline is communicated with the propellant storage unit, and the other end of the high-pressure pipeline is communicated with the combustion chamber;

the high-pressure pipeline is sequentially provided with a first electromagnetic valve, a first pressure sensor, an electric pump, a second pressure sensor and a first one-way valve;

the first solenoid valve is close to the propellant storage unit, and the first one-way valve is close to the combustion chamber;

the low pressure supply unit includes a low pressure line;

one end of the low-pressure pipeline is communicated with the propellant storage unit, and the other end of the low-pressure pipeline is communicated with the combustion chamber;

a second electromagnetic valve and a second one-way valve are sequentially arranged on the low-pressure pipeline; the second solenoid valve is close to the propellant storage unit, and the second one-way valve is close to the combustion chamber;

the device also comprises a pressurization unit; the pressurizing unit comprises a gas cylinder and a pressurizing pipeline communicated with the gas cylinder, wherein the input end of the pressurizing pipeline is communicated with the gas cylinder, and the output end of the pressurizing pipeline is communicated with the propellant storage unit;

the fourth pressure sensor is close to the gas cylinder, and the fifth electromagnetic valve is close to the propellant storage unit;

the blowing unit comprises a blowing pipeline;

the input end of the blowing pipeline is communicated with the pressurizing pipeline, and the output end of the blowing pipeline is communicated with the combustion chamber;

2. The mass flow fast response solid-liquid rocket engine ground delivery system according to claim 1, wherein the propellant storage unit comprises a tank and a propellant feed line in communication with the tank;

3. The mass-flow fast-response solid-liquid rocket engine ground conveying system according to claim 1, wherein a first regulating valve, a third electromagnetic valve, a third one-way valve and a sixth pressure sensor are sequentially arranged on the main path;

4. The mass flow fast response solid-liquid rocket engine ground delivery system according to claim 1, further comprising a circulation unit, said circulation unit comprising a circulation line;

one end of the circulating pipeline is communicated with the propellant storage unit, and the other end of the circulating pipeline is communicated with the main road;

5. The mass flow fast response solid-liquid rocket engine ground delivery system according to claim 4, further comprising an auxiliary unit, said auxiliary unit comprising an auxiliary line;

6. The mass flow fast response solid-liquid rocket engine ground delivery system according to claim 1, further comprising a bypass line;

one end of the bypass pipeline is communicated with the main pipeline, and a fourth hand valve is arranged on the bypass pipeline.