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

Abstract

The present application relates to the field of aerospace technology, in particular to a large-flow fast-response solid-liquid rocket engine ground conveying system. The large-flow and fast-response solid-liquid rocket engine ground transportation system includes a propellant storage unit, a high-pressure supply unit and a low-pressure supply unit; the output ends of the propellant storage unit are respectively communicated with the high-pressure supply unit and the low-pressure supply unit; the high-pressure supply unit and the low-pressure supply unit The output ends of the two are respectively communicated with the combustion chamber through the main road. The high-pressure supply unit and the low-pressure supply unit are in a parallel arrangement. This application cleverly combines the high-pressure supply unit and the low-pressure supply unit. During the test, different supply units can be flexibly switched to meet the requirements of the low-pressure combustion chamber. It can also meet the working condition of high pressure in the combustion chamber, thereby improving the efficiency of the ground transportation system of the solid-liquid rocket engine with large flow and rapid response.

Description

A large-flow and fast-response solid-liquid rocket motor ground conveying system

technical field

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

Background technique

At present, the ground delivery system of the solid-liquid hybrid rocket engine includes a gas circuit and a liquid circuit. Among them, the gas circuit has two functions, one is as a pressurizing circuit, pressurizing the storage tank, so that the storage tank maintains a certain pressure; the other is as a blowing pipe, blowing a large amount of inert nitrogen into the engine to blow out the engine, To ensure the safe extinguishing of the propellant after the ignition test is completed. The liquid path is usually pressurized by the storage tank. After a series of valves, the liquid propellant is sent into the combustion chamber to react with the solid propellant. In order to increase the pressure in the combustion chamber, an electric pump is often added to the liquid path. The low-pressure liquid in the tank is pressurized again to ensure that the liquid propellant enters the high-pressure combustion chamber at a certain flow rate, and then reacts.

However, due to the different pressure conditions of the combustion chamber, the efficiency of the electric pump conveying system is not high when the combustion chamber pressure is low, resulting in the electric pump conveying system unable to meet the low pressure of the combustion chamber.

Therefore, there is an urgent need for a large-flow and fast-response solid-liquid rocket motor ground transportation system to a certain extent to solve the technical problems existing in the prior art.

SUMMARY OF THE INVENTION

The purpose of the present application is to provide a large-flow fast-response solid-liquid rocket engine ground conveying system, so as to solve the technical problem that the electric pump conveying system in the prior art cannot meet the working condition of low combustion chamber pressure to a certain extent.

The application provides a large-flow fast-response solid-liquid rocket engine ground transportation system for propelling propellant to the combustion chamber; the large-flow fast-response solid-liquid rocket engine ground transportation system includes a propellant storage unit, a high-pressure supply unit and a low-pressure supply unit;

The output ends of the propellant storage unit are 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 circuit.

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

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

The first solenoid valve is proximate the propellant storage unit, and the first one-way valve is proximate the combustion chamber.

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

A second solenoid 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.

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

A filter, an electric ball valve, a first hand valve and a flowmeter are arranged in sequence on the propellant supply pipeline; the filter is close to the storage tank, and the flowmeter is close to the high-pressure supply unit or the low-pressure supply unit ;

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

In the above technical solution, further, the main road is provided with a first regulating valve, a third solenoid valve, a third one-way valve and a sixth pressure sensor in sequence;

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 close to the combustion chamber.

In the above technical solution, it further includes a pressurizing unit; the pressurizing unit includes a gas cylinder and a pressurizing pipeline, the input end of the pressurizing pipeline is communicated with the gas cylinder, and the output end is connected to the gas cylinder. the propellant storage unit is connected;

A fourth pressure sensor, a fourth solenoid valve, a first pressure reducer, a second hand valve and a fifth solenoid valve are sequentially arranged on the boosting pipeline;

The fourth pressure sensor is near the gas cylinder and the fifth solenoid valve is near the propellant storage unit.

In the above technical solution, further, a blow-off unit is further included, and the blow-off unit includes a blow-off pipeline;

The input end of the blow-off pipeline is communicated with the pressurization pipeline, and the output end is communicated with the combustion chamber;

A third pressure sensor, a third hand valve, a fifth pressure sensor, a sixth solenoid valve and a fourth one-way valve are sequentially arranged on the blow-off pipeline;

The third pressure sensor is close to the fourth solenoid valve, and the fourth one-way valve is close to the combustion chamber.

In the above technical solution, further, a circulation unit is further included, and the circulation unit includes a circulation pipeline;

One end of the circulation pipeline is communicated with the propellant storage unit, and the other end is communicated with the main circuit;

A fifth one-way valve, a seventh solenoid valve, a second regulating valve and a buffer are sequentially arranged on the circulation pipeline;

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

In the above technical solution, further, an auxiliary unit is further included, and the auxiliary unit includes an auxiliary pipeline;

The auxiliary pipeline is provided with an eighth solenoid valve close to the seventh solenoid valve and a fifth check valve close to the main circuit.

In the above technical solution, a bypass pipeline 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 effects of the present application are:

The application provides a large-flow fast-response solid-liquid rocket engine ground transportation system for propelling propellant to the combustion chamber; the large-flow fast-response solid-liquid rocket engine ground transportation system includes a propellant storage unit, a high-pressure supply unit and a low-pressure supply unit;

The output ends of the propellant storage unit are 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 circuit.

Specifically, the high-voltage supply unit and the low-voltage supply unit in this application are arranged in parallel. The supply unit can satisfy both the low pressure working condition of the combustion chamber and the high pressure working condition of the combustion chamber, thereby improving the efficiency of the ground conveying system of the solid-liquid rocket engine with large flow and rapid response.

Description of drawings

In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the accompanying drawings that need to be used in the description of the specific embodiments or the prior art will be briefly introduced below. The drawings are some embodiments of the present application. For those of ordinary skill in the art, other drawings can also be obtained from these drawings without any creative effort.

1 is a schematic structural diagram of a large-flow fast-response solid-liquid rocket motor ground transportation system provided in Embodiment 1 of the present application;

2 is a schematic structural diagram of a large-flow fast-response solid-liquid rocket motor ground transportation system provided in Embodiment 2 of the present application;

3 is a schematic structural diagram of a large-flow fast-response solid-liquid rocket motor ground transportation system provided in Embodiment 3 of the present application;

FIG. 4 is a schematic structural diagram of a large-flow fast-response solid-liquid rocket motor ground transportation system provided in Embodiment 4 of the present application.

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

Detailed ways

The technical solutions of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present application, but not all of the embodiments.

The components of the embodiments of the present application generally described and shown in the drawings herein may be arranged and designed in a variety of different configurations. Thus, the following detailed description of the embodiments of the application provided in the accompanying drawings is not intended to limit the scope of the application as claimed, but is merely representative of selected embodiments of the application.

Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.

In the description of this application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the accompanying drawings, which is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the indicated device or element must have a specific orientation or a specific orientation. construction and operation, and therefore should not be construed as limitations on this application. Furthermore, the terms "first", "second", and "third" are used for descriptive purposes only and should not be construed to indicate or imply relative importance.

In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it may be a fixed connection or a detachable connection Connection, or integral connection; can be mechanical connection, can also be electrical connection; can be directly connected, can also be indirectly connected through an intermediate medium, can be internal communication between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood in specific situations.

Example 1

The following describes a large-flow fast-response solid-liquid rocket motor ground transportation system according to some embodiments of the present application with reference to FIG. 1 .

In this embodiment, a large-flow fast-response solid-liquid rocket motor ground transportation system is provided for propelling propellant to the combustion chamber 800; the large-flow fast-response solid-liquid rocket engine ground transportation system includes a propellant storage unit, a high-pressure supply unit and low pressure supply unit;

The propellant storage unit is used for storing propellant (propellant refers to liquid oxidant), and its output end can communicate with the high-pressure supply unit and the low-pressure supply unit, respectively; the high-pressure supply unit and the low-pressure supply unit The output ends of the combustion chambers 800 are respectively communicated with the combustion chamber 800 through the main circuit 102; in this application, the high-pressure supply unit and the low-pressure supply unit are arranged in parallel, and the high-pressure supply unit and the low-pressure supply unit are skillfully combined to At the same time, different supply units can be flexibly switched during the test process, which can meet the low-pressure working condition of the combustion chamber 800 and the high-pressure working condition of the combustion chamber 800, thus improving the large flow and rapid response of the ground conveying system of the solid-liquid rocket engine. s efficiency.

Specifically, a first regulating valve 28 , a third solenoid valve 29 , a third one-way valve 30 and a sixth pressure sensor 31 are sequentially arranged on the main circuit 102 ; the first regulating valve 28 is close to the high-pressure supply unit The output end of the low pressure supply unit or the output end of the low pressure supply unit; the sixth pressure sensor 31 is close to the combustion chamber 800 .

Further, the first regulating valve 28 can regulate the flow rate of the liquid oxidant on the main circuit 102 .

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

Further, the third one-way valve 30 is a valve capable of preventing the high-pressure gas in the combustion chamber 800 from being backfilled, and preventing the liquid oxidant in the combustion chamber 800 from entering the high-pressure supply unit and the low-pressure supply unit in reverse.

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

Specifically, the large-flow fast-response solid-liquid rocket engine ground transportation system further includes a bypass pipeline 110; There is a fourth hand valve 32 .

Further, the fourth hand valve 32 can discharge the gas accumulated in the main circuit 102 during the process of filling the main circuit 102 with the liquid oxidant.

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

Further, the first solenoid valve 22 is a control switch of the high-pressure pipeline 101; when the first solenoid valve 22 is opened, the high-pressure pipeline 101 is opened, and the high-pressure pipeline 101 where the electric pump 24 is located is activated, and the electric pump 24 will The propellant is pressurized, sending the high pressure propellant into the combustion chamber 800 .

Further, the 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 the energy input element of the entire high-pressure supply unit. The electric pump 24 can pressurize the low-pressure propellant before the pump into a high-pressure propellant, increase the pressure potential energy of the propellant, so that the propellant has a high pressure, and into the high pressure combustion chamber 800 .

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

Further, the first one-way valve 26 can prevent the propellant of the main circuit 102 from being poured back into the electric pump 24 . When the low pressure supply unit is activated and the high pressure supply unit is deactivated, the propellant in the main circuit 102 may reversely flow into the electric pump 24 , so the first check valve 26 needs to be set to prevent the propellant from entering the electric pump 24 .

To sum up, the high pressure supply unit mainly includes the high pressure pipeline 101 and the first solenoid valve 22 , the first pressure sensor 23 , the electric pump 24 , the second pressure sensor 25 and the first one-way valve 26 arranged on the high pressure pipeline 101 . When the pressure of the combustion chamber 800 is high and the flow rate is large, the high-pressure pipeline 101 is activated, and at this time, the low-pressure pipeline 103 is disabled, and the propellant only passes through the high-pressure pipeline 101 . After being pressurized by the electric pump 24, the propellant will be pushed into the high pressure combustion chamber 800 with a relatively large flow.

Specifically, the low-pressure supply unit includes a low-pressure pipeline 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 solenoid valve 20 and a second check valve 21 are provided; the second solenoid valve 20 is close to the propellant storage unit, and the second check valve 21 is close to the combustion chamber 800 .

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

Further, the second one-way valve 21 can prevent backflow of the propellant.

To sum up, the low-pressure pipeline 103 mainly includes the second solenoid valve 20 and the second one-way valve 21 . The low-pressure pipeline 103 serves as a bypass for the high-pressure pipeline 101 where the electric pump 24 is located, which can work when the combustion chamber 800 is in a low-pressure condition, deactivate the electric pump 24 and the high-pressure pipeline 101 where it is located, and open the second Solenoid valve 20, enabling low pressure line 103.

Specifically, the propellant storage unit includes a tank 14 and a propellant supply pipeline 104 communicated with the tank 14; the propellant supply pipeline 104 is provided with a filter 16, an electric ball valve 17, a first A hand valve 18 and a flow meter 19; the filter 16 is close to the storage tank 14, the flow meter 19 is close to the high pressure supply unit or the low pressure supply unit; the storage tank 14 is provided with a third pressure Sensor 12 and fill bleed valve 15.

Further, the storage tank 14 is a pressure vessel, which can store a certain amount of propellant (liquid oxidant), and can withstand a certain pressure, so that the liquid oxidant can be smoothly squeezed into the high-pressure supply unit or the low-pressure supply unit.

Further, on the one hand, the filling and discharging valve 15 can be used as a liquid oxidant for filling, and the liquid oxidant is filled into the tank 14 through the filling and discharging valve 15, and on the other hand, it can be used as a discharge valve, and on the other hand, it can be used as a discharge valve. 15 drains the remaining liquid oxidant in tank 14.

Further, the filter 16 is used to filter the solid impurities doped in the liquid oxidant, so as to prevent the solid impurities from clogging the propellant supply pipeline 104 and to prevent the solid impurities from entering the combustion chamber 800 .

Further, the electric ball valve 17 has higher reliability and better sealing performance, and can be used as a seal of the tank 14 to block the liquid oxidant in the tank 14 before the test starts, preventing the outflow of the liquid oxidant in the tank 14 .

Further, the first hand valve 18 can be used as a backup switch for the propellant pipeline. When the first solenoid valve 22 or the second solenoid valve 20 fails or the flow of the liquid oxidant in the propellant supply pipeline 104 is abnormal, the first hand valve 18 can be manually closed. Primary valve 18.

Further, the flow meter 19 can monitor the real-time flow rate of the propellant supply pipeline 104 to ensure that the flow rate of the liquid oxidant reaches the target flow rate value.

Embodiment 2

The following describes a large-flow fast-response solid-liquid rocket motor ground transportation system according to some embodiments of the present application with reference to FIG. 2 .

In this embodiment, the large-flow fast-response solid-liquid rocket engine ground transportation system further includes a booster unit; the booster unit includes a gas cylinder 1 and a booster pipeline 105 communicating with the gas cylinder 1, so The input end of the pressurization pipeline 105 is communicated with the gas cylinder 1, and the output end is communicated with the propellant storage unit;

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

Further, the gas cylinder 1 is used to store high-pressure nitrogen, which can be used as a gas source; on the one hand, as a pressurized gas source to pressurize the storage tank 14, so that the storage tank 14 maintains a certain pressure; on the other hand, as a blow-off gas source , blowing a large amount of inert high-pressure nitrogen gas into the combustion chamber 800 to blow out the combustion chamber 800 to ensure the safe extinguishing of the propellant after the ignition test.

Further, the fourth pressure sensor 2 is used to monitor the pressure in the gas cylinder 1. If the pressure of the gas cylinder 1 is too high, it needs to be released from the blow-off pipeline 106 (the blow-off pipeline 106 is described in the third embodiment), If the pressure of the cylinder 1 is too low, the cylinder 1 needs to be inflated.

Further, the fourth solenoid valve 3 is the main valve of the pressurization pipeline 105 , and serves as the main switch of the pressurization pipeline 105 and the blow-off pipeline 106 .

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

Further, the second hand valve 10 is used as a manual switch of the boosting pipeline 105 to control the opening and closing of the tank 14 and is a backup switch. Once the fifth solenoid valve 11 is activated, the second hand valve 10 is activated.

Further, the fifth solenoid valve 11 is an electronically controlled switch of the booster pipeline 105; before the test, the fifth solenoid valve 11 needs to be opened, and the booster pipeline 105 sends high-pressure gas to the tank 14 containing the liquid oxidant, Thereby, the tank 14 is pressurized and then maintained at the target tank 14 pressure, pending the test. It is worth noting that during the test, the fifth solenoid valve 11 in front of the tank 14 also needs to be opened, and the booster pipeline 105 continuously supplies air to the tank 14 containing the liquid oxidant, thereby ensuring that the tank 14 is always It is stabilized within a certain pressure range to prevent the gas space in the tank 14 from increasing due to the massive outflow of the liquid propellant from the tank 14, thereby causing the pressure of the tank 14 to drop significantly.

Further, the third pressure sensor 12 can monitor the pressure of the tank 14; in the process of adjusting the pressure of the tank 14, the second hand valve 10 in front of the tank 14 and the fifth solenoid in front of the tank 14 need to be opened first. valve 11, and then slowly increase the opening of the first pressure reducer 9 of the tank 14, and at the same time visually observe the reading of the third pressure sensor 12 of the tank 14, and continuously adjust until the real-time reading of the third pressure sensor 12 of the tank 14 The reading is consistent with the target tank 14 pressure.

Further, the safety valve 13 is used to ensure that the pressure of the tank 14 does not exceed the limit value. If the pressure of the tank 14 exceeds the limit value, the safety valve 13 is opened, thereby reducing the pressure of the tank 14 and avoiding the operation of the first pressure reducer 9 Mistake and risk of explosion in tank 14 due to overpressure.

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

Embodiment 3

The following describes a large-flow fast-response solid-liquid rocket motor ground transportation system according to some embodiments of the present application with reference to FIG. 3 .

In this embodiment, the large-flow fast-response solid-liquid rocket engine ground transportation system further includes a blow-off unit, and the blow-off unit includes a blow-off pipeline 106; the input end of the blow-off pipeline 106 is connected to the The boosting pipeline 105 is connected, and the output end is connected with the combustion chamber 800; the blow-off pipeline 106 is sequentially provided with a second pressure reducer 4, a third hand valve 5, a fifth pressure sensor 6, a sixth pressure sensor Solenoid valve 7 and fourth one-way valve 8 ; the second pressure reducer 4 is close to the fourth solenoid valve 3 , and the fourth one-way valve 8 is close to the combustion chamber 800 .

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

Further, the third hand valve 5 is used as a manual switch for the blow-off line 106 to control the opening and closing of the blow-off line 106, and is a backup switch, which is activated when the sixth solenoid valve 7 fails.

Further, the second pressure reducer 4 can monitor the pressure of the blow-off line 106 . In the process of adjusting the pressure of the blow-off pipeline 106, firstly, the fourth solenoid valve 3 and the third hand valve 5 need to be opened, and then the opening of the second pressure reducer 4 should be slowly increased, and the reading of the second pressure reducer 4 should be visually checked. , and continuously adjust until the real-time reading of the second pressure reducer 4 is consistent with the target blow-off pressure.

Further, the sixth solenoid valve 7 is used as an electronically controlled switch for the blow-off pipeline 106 during the test. Open in the following cases, the first case is that the test ends normally, open the sixth solenoid valve 7 to blow out the solid-liquid engine, and feed a large amount of nitrogen into the combustion chamber 800 to reduce the temperature of the combustion chamber 800 . The second case is that the test is abnormal. In case of emergency, the sixth solenoid valve 7 is opened, a large amount of inert nitrogen gas is introduced into the combustion chamber 800, the engine is blown out, and the engine is shut down in an emergency.

Further, the fourth one-way valve 8 can prevent the liquid oxidant from flowing back into the blow-off pipeline 106 . It is ensured that the blow-off line 106 can only blow air to the combustion chamber 800 in one direction.

To sum up, the blowing unit ensures the normal supply of blowing gas, so that the entire conveying system has the ability to feed a large amount of inert gas into the combustion chamber 800 at any time, thereby ensuring the safety of the test.

Embodiment 4

The following describes a large-flow fast-response solid-liquid rocket motor ground transportation system according to some embodiments of the present application with reference to FIG. 4 .

In this embodiment, the large-flow fast-response solid-liquid rocket motor ground transportation system further includes a circulation unit, and the circulation unit includes a circulation pipeline 108; one end of the circulation pipeline 108 is communicated with the propellant storage unit, and the other One end communicates with the main circuit 102; the circulation pipeline 108 is provided with a fifth one-way valve 35, a seventh solenoid valve 34, a second regulating valve 33 and a buffer 27 in sequence; the fifth one-way valve 35 Close to the propellant storage unit, the buffer 27 is close to the high pressure supply unit.

Further, the second regulating valve 33 has the same structure and function as the first regulating valve 28; it acts synchronously during the test, that is, it is consistent in real time at the beginning of the test.

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

Further, the fifth one-way valve 35 can prevent the reverse flow of the liquid oxidant, that is, prevent the liquid oxidant fluid from flowing into the circulation line 108 from the tank 14 .

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

To sum up, by configuring the circulation pipeline 108 of the electric pump 24 and the first regulating valve 28 and the two-way regulating valve of the second regulating valve 33, the shortcoming that the electric pump 24 needs to start slowly and stop slowly is avoided, and the electric pump 24 is greatly improved. 24 for the flow responsiveness of a pumped delivery system.

In this embodiment, the large-flow fast-response solid-liquid rocket motor ground transportation system further includes an auxiliary unit, and the auxiliary unit includes an auxiliary pipeline 109; the auxiliary pipeline 109 is provided with a seventh solenoid valve close to the The eighth solenoid valve 36 of 34 and the sixth one-way valve 37 close to the main circuit 102 .

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

Further, the sixth one-way valve 37 prevents the reverse flow of the liquid oxidant, and prevents the liquid oxidant from flowing backward from the main circuit 102 into the auxiliary circuit pipeline.

In summary, by configuring the main circuit 102 and the auxiliary circuit, and both the main circuit 102 and the auxiliary circuit are equipped with regulating valves, it is possible to ensure that either the main circuit 102 and the auxiliary circuit can be opened instantly or simultaneously the main circuit 102 and the auxiliary circuit can be opened. pipeline, so that the regulating valves on the main pipeline 102 and the auxiliary pipeline can be adjusted at the same time. Compared with the traditional single circuit, the flow adjustment range of the double regulating valve pipeline is wider and the real-time response is faster.

In conjunction with the above-mentioned Embodiment 1 to Embodiment 4, the specific working process of the present application is as follows:

Step 100: Preparatory work before the test: It is necessary to pressurize and fill the tank 14, configure the air blowing, and fill the pipeline liquid oxidant.

Step 101: Pressurizing and filling the tank 14 is to add a certain amount of liquid propellant to the tank 14 through the filling and discharging valve, and increase the tank 14 through the first pressure reducer 9 of the pressurizing pipeline 105. Press to the target tank 14 pressure so 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 through the second pressure reducer 4, so 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 solenoid valve 29 with liquid propellant to prevent a part of gas from being stored in the pipeline. Preparations for the filling operation are tank 14 pressurization and valve preparation. Pressurizing the tank 14 is to pressurize the tank 14 to a lower pressure to ensure that the liquid oxidant can be squeezed into the pipeline. Valve preparation is to control the position of the relevant valve in place to ensure that the liquid oxidant can fill each part of the pipeline in turn according to the expected route. The main process is: close the third solenoid valve 29, close the seventh solenoid valve 34 and the eighth solenoid valve 36, open Electric ball valve 17, first-hand valve 18. The filling sequence is low pressure line 103 filling, high pressure line 101 filling and auxiliary line 109 filling.

Step 103 : Filling the low pressure pipeline 103 : closing the first solenoid valve 22 , deactivating the high pressure pipeline 101 , opening the second solenoid valve 20 , and enabling the low pressure pipeline 103 . Afterwards, the fourth hand valve 32 is manually opened until the liquid oxidant flowing into the outside world is not doped with gas.

Step 104 : Filling the high pressure pipeline 101 : closing the second solenoid valve 20 , deactivating the low pressure pipeline 103 , opening the first solenoid valve 22 , and enabling the high pressure pipeline 101 . Afterwards, the fourth hand valve 32 is manually opened until the liquid oxidant flowing into the outside world is not doped with gas.

Step 105: Filling the auxiliary pipeline 109: firstly close the high pressure pipeline 101, open the low pressure pipeline 103, that is, the first solenoid valve 22, and open the second solenoid valve 20; then adjust the opening of the first regulating valve 28 to a smaller opening The second regulating valve 33 is adjusted to a larger opening degree, so as to ensure that the main part of the liquid oxidant flows smoothly into the auxiliary pipeline 109; finally, the eighth solenoid valve 36 and the fourth hand valve 32 are opened until the liquid oxidant flowing into the outside is not mixed with Miscellaneous gases.

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

Step 201: Preparations before the test: ensure that the tank 14 is filled with liquid oxidant, and the pressure of the tank 14 has been pressurized to the target pressure of the tank 14; ensure that the pressure in the blow-off pipeline 106 is adjusted to the target blow-off pressure; ensure that the low-pressure pipe Line 103, high pressure line 101, main line 102, 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 activated, and the entire conveying system is an extrusion type conveying system; 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 state of the boosting pipeline 105 before the test is as follows: the second hand valve 10 is opened, and the fifth solenoid valve 11 is opened. Before the test, the valve status of the blow-off pipeline is as follows: the third hand valve 5 is open, and the sixth solenoid valve 7 is closed. The valve state of the low pressure pipeline 103 before the test is 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 all closed, that is, the first solenoid valve 22 is closed, the seventh solenoid valve 34 is closed, the eighth solenoid valve 36 is closed, and the fourth hand valve 32 is closed.

Step 203: Flow adjustment: manually open the fourth hand valve 32, and gradually increase the opening of the first regulating valve 28 in real time through the real-time reading of the flowmeter 19, until the reading of the flowmeter 19 is consistent with the target flow, close the fourth hand valve 32. Hand valve 32, the flow adjustment is completed.

If the target flow rate of the test is relatively large, 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 can be activated. After passing through the low pressure pipeline 103 , the fluid is divided, and passes through the main pipeline 102 and the auxiliary pipeline 109 at the same time, and finally the flow that flows into the combustion chamber 800 is the sum of the flow of the main pipeline 102 and the flow of the auxiliary pipeline 109 . Open the eighth solenoid valve 36 of the auxiliary circuit, adjust the opening of the first regulating valve 28 to the maximum, and then gradually increase the opening of the second regulating valve 33 until the reading of the flow meter 19 reaches the target flow rate. After that, the openings of the first regulating valve 28 and the second regulating valve 33 are maintained, the fourth hand valve 32 is closed, and the test is awaited.

Step 204: Start the test. The solid-liquid engine ignition time is set from time T0 to time T1 seconds, that is, the ignition time is T0, and the solid-liquid engine is turned off at T1. Before ignition, check the pressure of the tank 14 and the blow-off unit again, and check the status of each valve.

At time T0, the third solenoid valve 29 is opened. Since the opening of the third solenoid valve 29 is in place, the flow rate is rapidly increased to the target flow rate;

The third solenoid valve 29 is closed at time T1, and the flow rapidly drops to zero;

At T1+0.1s, the sixth solenoid valve 7 is opened, and a large amount of inert nitrogen is blown into the combustion chamber 800 to turn off the engine and cool down, so as to ensure the safety of the test.

After the engine is turned off and cooled down, the sixth solenoid valve 7 is closed. At this point, the test is over. 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 large, the pressure of the main circuit 102 is high, and the traditional extrusion conveying system can no longer meet the requirements. An energy input element, namely an electric pump 24, is added to the pipeline 101. At this time, the system mode needs to be switched, the low-pressure pipeline 103 is deactivated, and the high-pressure pipeline 101 is activated, and the system will be changed to a pump-pressure delivery system of the electric pump 24 type.

Step 301: Preparation before the test. Make sure that the tank 14 is filled and the pressure of the tank 14 has been pressurized to the target tank 14 pressure; make sure that the blowing unit pressure is adjusted to the target blowing pressure; make sure that the low-pressure pipeline 103, high-pressure pipeline 101, main circuit 102, auxiliary Line 109 is free of gas and is filled with liquid propellant.

Step 302: Pipeline valve configuration before the test: the flow rate is large, and the pressure of the combustion chamber 800 is high, the high-pressure pipeline 101 containing the electric pump 24 needs to be activated, and the entire conveying system is a pump pressure conveying system. The high-pressure pipeline 101 is opened, the low-pressure pipeline 103 is deactivated, the circulation pipeline 108 is activated, the auxiliary pipeline 109 is activated under super flow conditions, and the auxiliary pipeline 109 is deactivated under normal conditions. That is, the first solenoid valve 22 and the seventh solenoid valve 34 are opened, and the second solenoid valve 20 , the eighth solenoid valve 36 and the fourth hand valve 32 are closed.

Before the test, the valve state of the booster pipeline 105 is as follows: the second hand valve 10 is opened, and the fifth solenoid valve 11 is opened.

Before the test, the valve state of the blow-off pipeline 106 is as follows: the third hand valve 5 is opened, and the sixth solenoid valve 7 is closed.

The valve states of the main circuit 102 before the test are as follows: the electric ball valve 17 is open, the first hand valve 18 is open, the third solenoid valve 29 and the seventh solenoid valve 34 are open, and the second solenoid valve 20 and the eighth solenoid valve 36 are closed.

Step 303: Flow adjustment. Open the high pressure pipeline 101 and the circulation pipeline 108, and gradually adjust the rotational speed of the electric pump 24 and the opening of the second regulating valve 33 until the reading of the second pressure sensor 25 of the electric pump 24 meets the target pressure and the reading of the flowmeter 19 reaches the target flow. That is, the electric ball valve 17, the first hand valve 18, the first solenoid valve 22, and the seventh solenoid valve 34 are opened, and the rest of the valves in the liquid circuit are in a closed state. Turn on the electric pump 24 and gradually increase the speed until the pressure after the electric pump 24 meets the requirements, that is, the reading of the second pressure sensor 25 after the electric pump 24 is greater than the set pressure after the electric pump 24 . Keep the pump speed unchanged, and then gradually increase the opening of the second regulating valve 33 until the flow reaches the set target flow, that is, the reading of the flow meter 19 reaches the set flow value. At this time, since the opening of the second regulating valve 33 increases and the flow rate increases, the pressure behind the electric pump 24 will drop. At this time, it is necessary to increase the rotational speed of the electric pump 24 until the pressure behind the electric pump 24 is greater than the set electric pump 24 back pressure. Next, the rotation speed is not changed, and the opening degree of the second regulating valve 33 is adjusted. By repeatedly adjusting the rotational speed of the electric pump 24 and the opening of the second regulating valve 33 , it is ensured that the flow rate and the pressure after the electric pump 24 meet the requirements. Record the rotational speed of the electric pump 24 that meets the requirements at this time as W1, and the opening of the second regulating valve 33 as K1. Subsequently, the opening degree of the first regulating valve 28 is also adjusted to K1, that is, the structural dimensions and valve opening degrees of the first regulating valve 28 and the second regulating valve 33 are the same.

Step 304: Start the test. The solid-liquid engine ignition time is set from time T0 to time T1 seconds, that is, the ignition time is T0, and the solid-liquid engine is turned off at T1. Before ignition, check the pressure of the tank 14 and the blowing unit again, and check the status of each valve; ensure that the electric pump 24 rotates at W1, and the openings 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 structural dimensions and opening degrees of the first regulating valve 28 and the second regulating valve 33 are the same, when the fluid does not return to the tank 14 through the circulation pipeline 108, but flows to the combustion chamber 800 through the main channel 102, the flowmeter 19 The reading will not change, that is, the flow is still the target flow, the pressure after the electric pump 24 is still greater than the set pressure after the electric pump 24, and both the flow and the pressure after the electric pump 24 meet the requirements. After that, the flow rate of the propellant to the combustion chamber 800 quickly becomes the set target flow rate.

At T1 time, the third solenoid valve 29 is closed, and the seventh solenoid valve 34 is opened, the flow rate of the main circuit 102 rapidly drops to zero, and the flow rate of the circulation pipe 108 is changed to the target flow rate. Afterwards, in order to avoid damage to the electric pump 24, the electric pump 24 gradually reduces the rotational speed and stops slowly. After the electric pump 24 is stopped, the seventh solenoid valve 34 is closed.

At T1+0.1s, the sixth solenoid valve 7 is opened, and a large amount of inert nitrogen is blown into the combustion chamber 800 to turn off the engine and cool down to ensure the safety of the test.

After the engine is turned off and cooled down, the sixth solenoid valve 7 is closed. At this point, the test is over. To sum up, the present application configures the circulation pipeline 108, and the pipeline flow response is fast. On the one hand, the target flow rate can be reached quickly after the opening of the third solenoid valve 29 . On the other hand, after the ignition is over, the flow rate can be quickly reduced to zero, which greatly alleviates the problem of flow tailing. In the present application, in the ignition time period from T0 to T1, the flow rate flowing into the combustion chamber 800 rises rapidly to the target flow rate, and then rapidly decreases to 0, and the flow rate time curve is very stable.

In addition, the present application has a main circuit 102 and an auxiliary pipeline 109, and both circuits are equipped with regulating valves, which can open one channel or two channels instantly, and the valves of the two channels are adjusted at the same time, and the opening degree is unified. Compared with the traditional single circuit, the flow adjustment range of the double regulating valve pipeline is wider and the real-time response is faster.

Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, but not to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: The technical solutions described in the foregoing embodiments can still be modified, or some or all of the technical features thereof can be equivalently replaced; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the technical solutions of the embodiments of the present application. scope.

Claims (6)

1. a large-flow rapid response solid-liquid rocket motor ground conveying system is used for propellant to be propelled to the combustion chamber; it is characterized in that, the large-flow fast response solid-liquid rocket motor ground conveying system comprises a propellant storage unit, a high pressure supply unit and low pressure supply unit; The output ends of the propellant storage unit are 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 circuit; The high-pressure supply unit includes a high-pressure pipeline, one end of the high-pressure pipeline is communicated with the propellant storage unit, and the other end is communicated with the combustion chamber; A first solenoid valve, a first pressure sensor, an electric pump, a second pressure sensor and a first one-way valve are sequentially arranged on the high-pressure pipeline; the first solenoid valve is adjacent to the propellant storage unit, and the first one-way valve is adjacent to the combustion chamber; the low pressure supply unit includes a low pressure pipeline; One end of the low pressure pipeline is communicated with the propellant storage unit, and the other end is communicated with the combustion chamber; A second solenoid 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; It also includes a pressurizing unit; the pressurizing unit includes a gas cylinder and a pressurizing pipeline communicated with the gas cylinder, the input end of the pressurizing pipeline is communicated with the gas cylinder, and the output end is connected with the propulsion The agent storage unit is connected; A fourth pressure sensor, a fourth solenoid valve, a first pressure reducer, a second hand valve and a fifth solenoid valve are sequentially arranged on the boosting pipeline; the fourth pressure sensor is close to the gas cylinder, and the fifth solenoid valve is close to the propellant storage unit; Also includes a blow-off unit, the blow-off unit includes a blow-off pipeline; The input end of the blow-off pipeline is communicated with the pressurization pipeline, and the output end is communicated with the combustion chamber; A third pressure sensor, a third hand valve, a fifth pressure sensor, a sixth solenoid valve and a fourth one-way valve are sequentially arranged on the blow-off pipeline; The third pressure sensor is close to the fourth solenoid valve, and the fourth one-way valve is close to the combustion chamber. 2. The large-flow fast-response solid-liquid rocket motor ground transportation system according to claim 1, wherein the propellant storage unit comprises a storage tank and a propellant supply pipeline communicated with the storage tank; A filter, an electric ball valve, a first hand valve and a flowmeter are arranged in sequence on the propellant supply pipeline; the filter is close to the storage tank, and the flowmeter is close to the high-pressure supply unit or the low-pressure supply unit ; The storage tank is provided with a third pressure sensor and a filling and discharging valve. 3. The large-flow fast-response solid-liquid rocket engine ground transportation system according to claim 1, wherein the main road is sequentially provided with a first regulating valve, a third solenoid valve, a third one-way 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 close to the combustion chamber. 4. The large-flow fast-response solid-liquid rocket motor ground transportation system according to claim 1, further comprising a circulation unit, and the circulation unit comprises a circulation pipeline; One end of the circulation pipeline is communicated with the propellant storage unit, and the other end is communicated with the main circuit; A fifth one-way valve, a seventh solenoid valve, a second regulating valve and a buffer are sequentially arranged on the circulation pipeline; The fifth one-way valve is adjacent to the propellant storage unit, and the buffer is adjacent to the high pressure supply unit. 5. The large-flow fast-response solid-liquid rocket motor ground transportation system according to claim 4, further comprising an auxiliary unit, the auxiliary unit comprising an auxiliary pipeline; The auxiliary pipeline is provided with an eighth solenoid valve close to the seventh solenoid valve and a fifth check valve close to the main circuit. 6. The large-flow fast-response solid-liquid rocket motor ground conveying system according to claim 1, further comprising a bypass pipeline; One end of the bypass pipeline is communicated with the main pipeline, and a fourth hand valve is arranged on the bypass pipeline.

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