CN109083768B - Supply system suitable for large-scale liquid oxygen methane rocket engine test and rocket - Google Patents
Supply system suitable for large-scale liquid oxygen methane rocket engine test and rocket Download PDFInfo
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- CN109083768B CN109083768B CN201811180265.9A CN201811180265A CN109083768B CN 109083768 B CN109083768 B CN 109083768B CN 201811180265 A CN201811180265 A CN 201811180265A CN 109083768 B CN109083768 B CN 109083768B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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Abstract
The invention discloses a supply system suitable for a large liquid oxygen methane rocket engine test. The repeated construction of an oxidant supply system is avoided, and the cost is reduced; the supply system can simultaneously supply gas methane and liquid methane, a large rocket engine test of methane gas-liquid mixing is carried out, and a combustion performance test of the regenerative cooling engine is carried out at low cost; large rocket engine tests with different methane injection temperatures can be stably and efficiently carried out through the mixer; liquid nitrogen is used in the supply system for low-temperature pipeline precooling, and the method has the advantages of safety and low cost. On the basis, the application also provides a rocket based on the experimental supply system suitable for the large liquid oxygen methane rocket engine.
Description
Technical Field
The invention relates to the field of aerospace, in particular to a test supply system suitable for a large liquid oxygen methane rocket engine and a rocket.
Background
1. The large liquid rocket engine has huge demand in the aerospace field, the liquid rocket engine with large thrust is required for human beings to visit the moon or land mars in the future to serve as a support, and the liquid oxygen/methane liquid rocket engine has the advantages of high specific impulse, low cost, low carbon deposit, no coking during cooling, good environmental protection performance, reusability and the like, and is the focus of attention in the research field of the current reusable carrier rocket and large liquid booster power devices. However, at present, liquid oxygen/methane rocket engines are relatively little developed, and further research is still needed. The existing test system separately carries out liquid oxygen/liquid methane and liquid oxygen/gas methane tests, and the test system has the problems of resource waste, high cost and the like. Therefore, it is desirable to design a test system that can be used to perform liquid oxygen/liquid methane and liquid oxygen/gas methane tests.
2. The advantage and ultimate goal of reusability are to reduce the waste caused by discarding expensive rocket bodies, engines and electrical equipment after the carrier is used once, and to reduce the production and launching costs of the carrier by using the carrier for multiple times to share the cost, which is the key point of future development in the aerospace field. The repeated use of the engine becomes an urgent problem to be solved, and the liquid oxygen/methane has potential strong competitiveness as a propellant for repeated use of the engine in the future. The cooling effect of the engine needs to be fully considered in the process of reusing the engine, and the regenerative cooling is suitable for the liquid oxygen/methane reusable engine. The existing test system is used for carrying out tests on the regenerative cooling working condition, and only an engine with a cooling channel can be used for carrying out a gas-liquid mixing injection test, so that the test cost is increased, and the test system is not suitable for selecting proper cooling channel parameters by carrying out a large amount of methane gas-liquid mixing tests. Therefore, it is desirable to design a liquid oxygen/methane test system that can simultaneously inject both gas methane and liquid methane.
3. In a liquid oxygen/methane regeneration cooling engine test, the optimal methane injection temperature needs to be searched, the purposes of high combustion efficiency and stable combustion are achieved, and the existing test system is low in control precision and easy to introduce impurities when the methane temperature is controlled. Therefore, it is necessary to design a liquid oxygen/methane test system that can perform different methane injection temperature tests.
4. In the test process of the liquid oxygen/methane engine, the methane gas is dangerous in the air, and the concentration of the methane gas needs to be considered in the test environment, so that the test safety is ensured. In the existing test system, a liquid methane precooling pipeline is needed in the precooling process of a pipeline system, and a large amount of methane enters air. And liquid methane and liquid oxygen are relatively costly. Therefore, it is necessary to design a set of pipeline pre-cooling system with high safety and low cost.
Disclosure of Invention
The invention aims to provide a supply system suitable for a large liquid oxygen methane rocket engine test, so as to solve the technical problems in the prior art.
The test supply system suitable for the large liquid oxygen methane rocket engine provided by the invention has the following advantages:
the gas methane and liquid methane tests in the large rocket engine test supply system share one set of liquid oxygen supply system, so that the repeated construction of an oxidant supply system is avoided, and the cost is reduced;
the supply system can simultaneously supply gas methane and liquid methane, a large rocket engine test of methane gas-liquid mixing is carried out, and a combustion performance test of the regenerative cooling engine is carried out at low cost;
large rocket engine tests with different methane injection temperatures can be stably and efficiently carried out through the mixer;
liquid nitrogen is used in the supply system for low-temperature pipeline precooling, and the method has the advantages of safety and low cost.
In addition, the application also provides a rocket, which comprises the supply system suitable for the large liquid oxygen methane rocket engine test.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic structural diagram of a supply system suitable for a large liquid methane oxide rocket engine test according to an embodiment of the present invention.
Reference numerals: a01 — first pressure reducer; a 02-first manual stop valve; a03 — first pressure sensor; a04-second manual stop valve; a05-first pneumatic stop valve; a06 — first filter; a07 — first orifice plate; a08 — first temperature sensor; a09 — second pressure sensor; e01-liquid oxygen storage tank; a10-first solenoid valve; a11-third manual stop valve; a12 — first relief valve; a13-fourth manual stop valve; b04-fifth manual shut-off valve; a14-sixth manual stop valve; a15 — second filter; a29 — third filter; a16-second pneumatic stop valve; a17 — first flow meter; a18 — third pressure sensor; a19 — second temperature sensor; a20 — first venturi; a21 — third temperature sensor; a22 — fourth pressure sensor; a23-seventh manual stop valve; a24-third pneumatic stop valve; a26-fourth pneumatic stop valve; a25 — second orifice plate; a27 — fourth filter; a28-second solenoid valve; e02-liquid nitrogen storage tank; b01-eighth manual shut-off valve; b07 — second relief valve; b08-ninth manual shut-off valve; b09-fifth filter; b02-tenth manual shut-off valve; b03-sixth filter; b05-seventh filter; b04-eleventh manual stop valve; b06-twelfth manual shut-off valve; c01-second pressure reducer; c02-thirteenth manual shutoff valve; c03 — fifth pressure sensor; c04-fourteenth manual shut-off valve; c05-fifth pneumatic stop valve; c06-eighth filter; c07-third orifice plate; c08 — fourth temperature sensor; c09 — sixth pressure sensor; e03-liquid methane tank; c10-third solenoid valve; c11-fifteenth manual shutoff valve; c12-third relief valve; c13-sixteenth manual shut-off valve; c14-a seventeenth manual shut-off valve; c16-ninth filter; c15-tenth filter; c17-sixth pneumatic stop valve; c18 — second flow meter; f01-eighteenth manual stop valve; c19-nineteenth manual shut-off valve; c20-seventh pressure sensor; c21 — fifth temperature sensor; c22 — second venturi; c23 — sixth temperature sensor; c24 — eighth pressure sensor; c25-twentieth manual shutoff valve; c26-seventh pneumatic stop valve; c28-eighth pneumatic stop valve; c27-fourth orifice plate; c29-eleventh filter; c30-fourth solenoid valve; e04-gas methane storage tank; d01-fourth relief valve; d02-twenty-first manual shutoff valve; d04 — twelfth filter; d03-thirteenth filter; d05-ninth pneumatic stop valve; d06-a third pressure reducer; d07-ninth pressure sensor; d08-third flow meter; f07-twenty manual stop valve; d09-twenty-third manual stop valve; d10-tenth pressure sensor; d11-seventh temperature sensor; d12-third venturi; d13 — eighth temperature sensor; d14-eleventh pressure sensor; d15-fifth solenoid valve; d16-tenth pneumatic stop valve; d17-fourteenth filter; d18-sixth solenoid valve; f02 — twelfth pressure sensor; f03 — ninth temperature sensor; f04-mixer; f06 — a thirteenth pressure sensor; f05 — tenth temperature sensor; f08-eleventh pneumatic stop valve; f09 — a fourteenth pressure sensor; f10 — eleventh temperature sensor; f11 — fourth venturi; f12 — twelfth temperature sensor; f13-fifteenth pressure sensor; f14-seventh solenoid valve; f15-twelfth pneumatic stop valve; f16-fifteenth filter; f17-eighth solenoid valve; g01-fourth pressure reducer; g03-sixteenth pressure sensor; g02-fifth pressure reducer; g04-seventeenth pressure sensor.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. 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 invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., 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, but 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 invention. 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 invention, it should 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 meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
The first embodiment is as follows:
FIG. 1 is a schematic structural diagram of a supply system suitable for a large liquid methane oxide rocket engine test according to a first embodiment of the present invention; as shown in fig. 1, in the test supply system suitable for the large liquid oxygen methane rocket engine according to the first embodiment of the present invention, pressurized nitrogen is connected to a first manual stop valve a02, a first pressure sensor a03 and a second manual stop valve a04 through a first pressure reducer a01, the second manual stop valve a04 is connected in sequence to a first manual stop valve a05, a first filter a06, a first orifice plate a07, a first temperature sensor a08, a second pressure sensor a09 and a liquid oxygen storage tank E01, the liquid oxygen storage tank E01 is connected to a first solenoid valve a10, a third manual stop valve a11, a first safety valve a12 and a fourth manual stop valve a13, the fourth manual stop valve a13 is connected in sequence to a cross-way, an eleventh manual stop valve B04, a sixth manual stop valve a14 and a second filter a15 are connected in sequence to a sixth manual stop valve a 695a 56, and a second filter a 82 16 is connected in sequence to a second stop valve a 828653, The system comprises a first flowmeter A17, a third pressure sensor A18, a second temperature sensor A19, a first venturi tube A20, a third temperature sensor A21 and a fourth pressure sensor A22, wherein the fourth pressure sensor A22 is connected with a seventh manual stop valve A23, a third pneumatic stop valve A24 and a fourth pneumatic stop valve A26, a second orifice plate A25 is connected behind the third pneumatic stop valve A24, a tee joint is arranged behind the fourth pneumatic stop valve A26, one end of the tee joint is sequentially connected with a fourth filter A27 and a second electromagnetic valve A28, and the other end of the tee joint is connected with an engine;
the liquid nitrogen storage tank E02 is connected with an eighth manual stop valve B01, a second safety valve B07 and a ninth manual stop valve B08, the back of the ninth manual stop valve B08 is connected with a fifth filter B09, the back of the eighth manual stop valve B01 is divided into four ways, the tenth manual stop valve B02, a sixth filter B03 and a seventh filter B05 are respectively connected, the back of the sixth filter B03 is connected with an eleventh manual stop valve B04, and the back of the seventh filter B05 is connected with a twelfth manual stop valve B06;
the pressurized nitrogen is connected with a thirteenth manual stop valve C02, a fifth pressure sensor C03 and a fourteenth manual stop valve C04 through a second pressure reducer C01, the fourteenth manual stop valve C04 is connected with a fifth pneumatic stop valve C05, an eighth filter C06, a third orifice plate C07, a fourth temperature sensor C08, a sixth pressure sensor C09 and a liquid methane storage tank E03 in sequence, the liquid methane storage tank E03 is connected with a third electromagnetic valve C10, a fifteenth manual stop valve C11, a third safety valve C12 and a sixteenth manual stop valve C13, the sixteenth manual stop valve C13 is connected with a four-way in sequence and is connected with a twelfth manual stop valve B06, a seventeenth manual stop valve C14 and a ninth filter C14 respectively, the seventeenth manual stop valve C14 is connected with a tenth filter C14 in sequence, the ninth filter C14 is connected with a sixth pneumatic stop valve C14 in sequence, and one end of the eighteenth flowmeter 14 is connected with an eighteenth manual stop valve C14, the other end of the hydraulic control valve is connected with a nineteenth manual stop valve C19, a seventh pressure sensor C20, a fifth temperature sensor C21, a second venturi tube C22, a sixth temperature sensor C23 and an eighth pressure sensor C24 are sequentially connected behind the nineteenth manual stop valve C19, the eighth pressure sensor C24 is connected with a twentieth manual stop valve C25, a seventh pneumatic stop valve C26 and an eighth pneumatic stop valve C28, a fourth orifice plate C27 is behind the seventh pneumatic stop valve C26, a tee joint is arranged behind the eighth pneumatic stop valve C28, an eleventh filter C29 and a fourth electromagnetic valve C30 are sequentially connected at one end, and the other end of the hydraulic control valve C19 is connected with the engine;
the gas methane storage tank E04 is connected with a fourth safety valve D01, a twenty-first manual stop valve D02 and a twelfth filter D04, the twenty-first manual stop valve D02 is connected with a thirteenth filter D03, the twelfth filter D04 is connected with a ninth pneumatic stop valve D05, a third pressure reducer D06, a ninth pressure sensor D07 and a third flow meter D08 in sequence, the third flow meter D08 is connected with a twenty-second manual stop valve F07 at one end and a twenty-third manual stop valve D09 at the other end, the twenty-third manual stop valve D09 is connected with a tenth pressure sensor D10, a seventh temperature sensor D11, a third pipe D12, an eighth temperature sensor D13 and an eleventh pressure sensor D14 in sequence, the eleventh pressure sensor D14 is connected with an electromagnetic valve at the back, a fifth pressure sensor D15 and a tenth pneumatic stop valve D16 are respectively connected with the tenth pneumatic stop valve D16, one end of the first electromagnetic valve is connected with a fourteenth filter D17 and a sixth electromagnetic valve D18 in sequence, and the other end of the first electromagnetic valve is connected with an engine;
a twelfth pressure sensor F02, a ninth temperature sensor F03 and a mixer F04 are sequentially connected behind the eighteenth manual stop valve F01, a thirteenth pressure sensor F06, a tenth temperature sensor F05 and a mixer F04 are sequentially connected behind the twenty-second manual stop valve F07, an eleventh pneumatic stop valve F08, a fourteenth pressure sensor F09, an eleventh temperature sensor F10, a fourth venturi tube F11, a twelfth temperature sensor F12 and a fifteenth pressure sensor F13 are sequentially connected behind the mixer F04, a fifteenth pressure sensor F13 is divided into a tee joint behind and is respectively connected with a seventh electromagnetic valve F14 and a twelfth pneumatic stop valve F15, a twelfth pneumatic stop valve F15 is divided into a tee joint behind, one end of the twelfth pneumatic stop valve F15 is sequentially connected with a fifteenth filter F16 and an eighth electromagnetic valve F17, and the other end of the fifteenth pressure sensor F13 is connected with the engine;
the first pneumatic stop valve A05, the second pneumatic stop valve A16, the third pneumatic stop valve A24, the fourth pneumatic stop valve A26, the fifth pneumatic stop valve C05, the sixth pneumatic stop valve C17, the seventh pneumatic stop valve C26, the eighth pneumatic stop valve C28, the ninth pneumatic stop valve D05, the tenth pneumatic stop valve D16, the eleventh pneumatic stop valve F08 and the twelfth pneumatic stop valve F15 are connected with the fourth pressure reducer G01 through a sixteenth pressure sensor G03;
the sixth solenoid valve D18, the eighth solenoid valve F17, the fourth solenoid valve C30, and the second solenoid valve a28 are connected to a fifth pressure reducer G02 through a seventeenth pressure sensor G04.
The main working flow of the thrust chamber independent test is that the operation gas pressure of all the pneumatic stop valves is adjusted, namely the gas pressure is adjusted to the design value after the fourth pressure reducer G01 is adjusted, and the pressure required by the driving of each pneumatic stop valve is ensured. Then the fuel and oxidant pressurization system is adjusted to adjust the gas pressure after the first pressure reducer A01 to the design value to provide guarantee for the medium pressure output by the liquid oxygen storage tank E01, and the gas pressure after the second pressure reducer C01 to the design value to provide guarantee for the medium pressure output by the liquid methane storage tank E03. Finally the test blow-off pressure is adjusted to the normal value, i.e. the output pressure of the fifth pressure reducer G02. The system is also provided with a pipeline for filling the liquid oxygen storage tank E01 and the liquid methane storage tank E03 with propellant, and the liquid oxygen storage tank E01 and the liquid methane storage tank E03 are directly filled with the propellant through a tank car. The specific operation flow is as follows:
the fuel and oxidant are charged prior to the nitrogen pressurization operation, primarily by tanker truck charging. And for the oxidant system, opening a fourth manual stop valve A13, opening a sixth manual stop valve A14, filling the liquid oxygen storage tank E01, closing the fourth manual stop valve A13 after the filling is finished, and closing the sixth manual stop valve A14 after the residual liquid in the pipeline is completely deflated, so that the oxidant storage tank is completely filled. And for the fuel system, opening a sixteenth manual stop valve C13, opening a seventeenth manual stop valve C14, filling the liquid methane storage tank E03, closing the sixteenth manual stop valve C13 after the filling is finished, and closing the seventeenth manual stop valve C14 after the residual liquid in the pipeline is deflated. In addition, the twenty-first manual stop valve D02 is directly opened in the filling process of the gas methane storage tank E04, and the twenty-first manual stop valve D02 is closed after the filling is finished, so that the filling is finished for the fuel system. In addition, the filling process of the liquid nitrogen storage tank E02 is directly carried out by opening the ninth manual stop valve B08, and the ninth manual stop valve B08 is closed after the filling process is finished.
In the process of carrying out the thrust room alone test, at first need carry out experimental preparation, confirm that all manual stop valves of system and pneumatic stop valve are in the closed condition, adjust fourth pressure reducer G01 outlet pressure to the required pressure requirement of pneumatic stop valve, instruct according to sixteenth pressure sensor G03, the required air supply of all pneumatic stop valves up to this moment obtains guaranteeing. The fifth pressure reducer G02 is adjusted to the desired blow-off pressure value as indicated by the seventeenth pressure sensor G04, whereupon the test system has adjusted the blow-off gas. The first pressure reducer a01 is then adjusted to set the output pressure to the desired pressure level, indicated by the first pressure sensor a03, and if the output pressure is adjusted incorrectly, the first manual shut-off valve a02 is opened to bleed pressure, and then the second manual shut-off valve a04 and the first manual shut-off valve a05 are opened, until the oxidizer pressurization system is adjusted. The second pressure reducer C01 is then regulated to the design pressure, indicated by the fifth pressure sensor C03, and if the output pressure is regulated incorrectly, the third manual cut-off valve C02 is opened to bleed air and relieve pressure, and finally the fourteenth manual cut-off valve C04 and the fifth pneumatic cut-off valve C05 are opened, so far that the cryogenic fuel pressurization system is regulated and the nitrogen part is operated. Then the ninth pneumatic stop valve D05 is opened, the third pressure reducer D06 is adjusted to make the output pressure reach the required pressure, and indication is carried out through the ninth pressure sensor D07 until the pressure of the gas methane system is adjusted. The thrust room test preparation phase is completed.
In the individual formal test process of the thrust chamber, firstly, a precooling process is carried out on a pipeline, for an oxidant conveying system, the eighth manual stop valve B01, the eleventh manual stop valve B04 and the second pneumatic stop valve A16 are opened, and in the precooling process, the seventh manual stop valve A23 and the third pneumatic stop valve A24 are required to be opened to evacuate gas generated in the precooling process. And after the liquid nitrogen precooling of the whole pipeline is finished, closing the eighth manual stop valve B01, closing the eleventh manual stop valve B04, opening the tenth manual stop valve B02, carrying out the deflation operation of redundant liquid nitrogen, and closing the tenth manual stop valve B02 after the deflation is finished. And (3) closing and opening the fourth manual stop valve A13, after the liquid oxygen precooling pipeline is finished, closing the fourth manual stop valve A13, closing the second pneumatic stop valve A16, closing the seventh manual stop valve A23, closing the third pneumatic stop valve A24, opening the sixth manual stop valve A14, carrying out excess liquid air bleeding operation, and after the air bleeding is finished, closing the sixth manual stop valve A14, so that precooling in the oxidant pipeline is finished. For a low-temperature fuel transportation system, the eighth manual stop valve B01 is opened, the twelfth manual stop valve B06 is opened, the sixth pneumatic stop valve C17 is opened, the twentieth manual stop valve C25 and the seventh pneumatic stop valve C26 are required to be opened in the precooling process, and gas generated in the precooling process is emptied. And after the liquid nitrogen precooling of the whole pipeline is finished, closing the eighth manual stop valve B01, closing the twelfth manual stop valve B06, opening the tenth manual stop valve B02, carrying out the deflation operation of redundant liquid nitrogen, and closing the tenth manual stop valve B02 after the deflation is finished. And closing and opening a sixteenth manual stop valve C13, after the liquid oxygen precooling pipeline is finished, closing a sixteenth manual stop valve C13, closing a sixth pneumatic stop valve C17, closing a twentieth manual stop valve C25, closing a seventh pneumatic stop valve C26, opening a seventeenth manual stop valve C14, carrying out redundant liquid air bleeding operation, and after the air bleeding is finished, closing a seventeenth manual stop valve C14, so far, the precooling in the low-temperature fuel pipeline is finished. In the pre-cooling operation, the liquid in the pipeline needs to be monitored in time according to equipment such as a temperature sensor, a pressure sensor and the like on site. And finishing the preparation work before the thrust chamber test. In the process of the official test, according to the test system used in the actual test, the second pneumatic stop valve a16, the fourth pneumatic stop valve a26, the sixth pneumatic stop valve C17, the eighth pneumatic stop valve C28, the ninth pneumatic stop valve D05, the tenth pneumatic stop valve D16, the eleventh pneumatic stop valve F08 and the twelfth pneumatic stop valve F15 are opened or closed by a time sequence operation, and the operation sequence of the eight valves is controlled by a computer time sequence. After the test is finished, the pipeline system is closed, the fuel and oxidant delivery system is closed firstly, and according to the test system used in the actual test, the second pneumatic stop valve A16, the fourth pneumatic stop valve A26, the sixth pneumatic stop valve C17, the eighth pneumatic stop valve C28, the ninth pneumatic stop valve D05, the tenth pneumatic stop valve D16, the eleventh pneumatic stop valve F08 and the twelfth pneumatic stop valve F15 are closed. The second solenoid valve A28, the fourth solenoid valve C30, the sixth solenoid valve D18 and the eighth solenoid valve F17 are opened to purge the lines and nitrogen from the engine. And opening the third pneumatic stop valve A24, the seventh pneumatic stop valve C26, the fifth electromagnetic valve D15 and the seventh electromagnetic valve F14 to perform air release operation in the pipeline, and closing the third pneumatic stop valve A24, the seventh pneumatic stop valve C26, the fifth electromagnetic valve D15 and the seventh electromagnetic valve F14 after liquid in the pipeline is cleaned. And then closing the nitrogen pressurization system, closing the first pneumatic stop valve A05, opening the first manual stop valve A02, the first electromagnetic valve A10 and the third manual stop valve A11, decompressing the oxygen path pressurization nitrogen pipeline and the tank body, and closing the first manual stop valve A02, the second manual stop valve A04, the first electromagnetic valve A10 and the third manual stop valve A11 after the gas discharge is finished. And closing a fifth pneumatic stop valve C05, opening a thirteenth manual stop valve C02, a third electromagnetic valve C10 and a fifteenth manual stop valve C11, decompressing the fuel tank body and the fuel nitrogen pressurization pipeline, and closing the thirteenth manual stop valve C02, a fourteenth manual stop valve C04, a third electromagnetic valve C10 and a fifteenth manual stop valve C11 after the decompression is finished, so that the pressurization system is closed completely. The supply system for the thrust cell test procedure is operated.
The test supply system suitable for the large liquid oxygen methane rocket engine provided by the invention has the following advantages:
the gas methane and liquid methane tests in the large rocket engine test supply system share one set of liquid oxygen supply system, so that the repeated construction of an oxidant supply system is avoided, and the cost is reduced;
the supply system can simultaneously supply gas methane and liquid methane, a large rocket engine test of methane gas-liquid mixing is carried out, and a combustion performance test of the regenerative cooling engine is carried out at low cost;
large rocket engine tests with different methane injection temperatures can be stably and efficiently carried out through the mixer;
liquid nitrogen is used in the supply system for low-temperature pipeline precooling, and the method has the advantages of safety and low cost.
Specifically, the liquid oxygen storage tank E01 is a high-pressure liquid oxygen storage tank.
Specifically, the liquid methane storage tank E03 is a high pressure liquid methane storage tank.
Specifically, the gas methane storage tank E04 is a high pressure gas methane storage tank.
Specifically, the liquid nitrogen storage tank E02 is a low-pressure liquid nitrogen storage tank.
Specifically, the pressure of the liquid oxygen storage tank E01 is 10 MPa.
Specifically, the pressure of the liquid methane storage tank E03 is 15 MPa.
Specifically, the pressure of the gas methane storage tank E04 is 15 MPa.
Specifically, the pressure of the liquid nitrogen storage tank E02 was 0.8 MPa.
Example two:
the application also provides a rocket, which comprises the supply system suitable for the large liquid oxygen methane rocket engine test.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art 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 invention.
Claims (10)
1. The test supply system is characterized in that pressurized nitrogen is connected with a first manual stop valve (A02), a first pressure sensor (A03) and a second manual stop valve (A04) through a first pressure reducer (A01), the second manual stop valve (A04) is connected with a first pneumatic stop valve (A05), a first filter (A06), a first orifice plate (A07), a first temperature sensor (A08), a second pressure sensor (A09) and a liquid oxygen storage tank (E01) in sequence, the liquid oxygen storage tank (E01) is connected with a first electromagnetic valve (A10), a third manual stop valve (A11), a first safety valve (A12) and a fourth manual stop valve (A13), the fourth manual stop valve (A13) is divided into a four-way and is connected with an eleventh manual stop valve (B04), a sixth manual stop valve (A14) and a second filter (15) respectively, the sixth manual stop valve (A14) is connected with a third filter (A29) in back, the second filter (A15) is connected with a second pneumatic stop valve (A16), a first flow meter (A17), a third pressure sensor (A18), a second temperature sensor (A19), a first venturi tube (A20), a third temperature sensor (A21) and a fourth pressure sensor (A22) in back in sequence, the fourth pressure sensor (A22) is connected with a seventh manual stop valve (A23), a third pneumatic stop valve (A24) and a fourth pneumatic stop valve (A26), the third pneumatic stop valve (A24) is connected with a second orifice plate (A25) in back, the fourth pneumatic stop valve (A26) is divided into a tee joint in back, one end of the fourth pneumatic stop valve is connected with a fourth filter (A27) and a second electromagnetic valve (A28) in sequence, and the other end of the fourth pneumatic stop valve is connected with the engine;
the liquid nitrogen storage tank (E02) is connected with an eighth manual stop valve (B01), a second safety valve (B07) and a ninth manual stop valve (B08), a fifth filter (B09) is connected behind the ninth manual stop valve (B08), a tenth manual stop valve (B02), a sixth filter (B03) and a seventh filter (B05) are respectively connected behind the eighth manual stop valve (B01), an eleventh manual stop valve (B04) is connected behind the sixth filter (B03), and a twelfth manual stop valve (B06) is connected behind the seventh filter (B05);
the pressurized nitrogen is connected with a thirteenth manual stop valve (C02), a fifth pressure sensor (C03) and a fourteenth manual stop valve (C04) through a second pressure reducer (C01), a fifth pneumatic stop valve (C05), an eighth filter (C06), a third orifice plate (C07), a fourth temperature sensor (C08), a sixth pressure sensor (C09) and a liquid methane storage tank (E03) are sequentially connected behind the fourteenth manual stop valve (C04), the liquid methane storage tank (E03) is connected with a third electromagnetic valve (C10), a fifteenth manual stop valve (C11), a third safety valve (C12) and a sixteenth manual stop valve (C13), a sixteenth manual stop valve (C13) is divided into a four-way which is respectively connected with a twelfth manual stop valve (B06), a seventeenth manual stop valve (C14) and a ninth filter (C16), and a seventeenth manual stop valve (C14) is connected with a tenth filter (C15), a sixth pneumatic stop valve (C17) and a second flow meter (C18) are sequentially connected behind the ninth filter (C16), one end of a rear branch tee joint of the second flow meter (C18) is connected with an eighteenth manual stop valve (F01), the other end of the rear branch tee joint of the second flow meter (C18) is connected with a nineteenth manual stop valve (C19), a seventh pressure sensor (C20), a fifth temperature sensor (C21), a second Venturi tube (C22), a sixth temperature sensor (C23) and an eighth pressure sensor (C24) are sequentially connected behind the nineteenth manual stop valve (C19), the eighth pressure sensor (C24) is connected with a twentieth manual stop valve (C25), a seventh pneumatic stop valve (C26) and an eighth pneumatic stop valve (C28), a fourth orifice connecting plate (C27) is arranged behind the seventh pneumatic stop valve (C26), a third branch tee joint of the eighth pneumatic stop valve (C28) is sequentially connected with an eleventh filter (C29) and a fourth electromagnetic valve (C30), the other end is connected with an engine;
the gas methane storage tank (E04) is connected with a fourth safety valve (D01), a twenty-first manual stop valve (D02) and a twelfth filter (D04), the twenty-first manual stop valve (D02) is connected with a thirteenth filter (D03) in sequence, the twelfth filter (D04) is sequentially connected with a ninth pneumatic stop valve (D05), a third pressure reducer (D06), a ninth pressure sensor (D07) and a third flow meter (D08), the third flow meter (D08) is divided into a tee joint in sequence, one end of the third manual stop valve (F07) is connected with one end of the third manual stop valve (D09), the other end of the third manual stop valve (D09) is sequentially connected with a tenth pressure sensor (D10), a seventh temperature sensor (D11), a third Venturi tube (D12), an eighth temperature sensor (D13) and an eleventh pressure sensor (D14), and the eleventh pressure sensor (D14) is divided into a tee joint in sequence, the hydraulic control system is connected with a fifth electromagnetic valve (D15) and a tenth pneumatic stop valve (D16) respectively, the rear part of the tenth pneumatic stop valve (D16) is divided into a tee joint, one end of the tenth pneumatic stop valve is connected with a fourteenth filter (D17) and a sixth electromagnetic valve (D18) in sequence, and the other end of the tenth pneumatic stop valve is connected with an engine;
a twelfth pressure sensor (F02), a ninth temperature sensor (F03) and a mixer (F04) are sequentially connected behind the eighteenth manual stop valve (F01), a thirteenth pressure sensor (F06), a tenth temperature sensor (F05) and a mixer (F04) are sequentially connected behind the twentieth manual stop valve (F07), an eleventh pneumatic stop valve (F08), a fourteenth pressure sensor (F09), an eleventh temperature sensor (F10), a fourth venturi tube (F11), a twelfth temperature sensor (F12) and a fifteenth pressure sensor (F13) are sequentially connected behind the mixer (F04), a seventh electromagnetic valve (F14) and a twelfth pneumatic stop valve (F15) are respectively connected behind the fifteenth pressure sensor (F13), a twelfth pneumatic stop valve (F15) is divided behind the twelfth pneumatic stop valve (F15), a fifteenth filter (F16) and an eighth electromagnetic valve (F17) are sequentially connected at one end of the twelfth pneumatic stop valve (F15), the other end is connected with an engine;
the first pneumatic stop valve (A05), the second pneumatic stop valve (A16), the third pneumatic stop valve (A24), the fourth pneumatic stop valve (A26), the fifth pneumatic stop valve (C05), the sixth pneumatic stop valve (C17), the seventh pneumatic stop valve (C26), the eighth pneumatic stop valve (C28), the ninth pneumatic stop valve (D05), the tenth pneumatic stop valve (D16), the eleventh pneumatic stop valve (F08) and the twelfth pneumatic stop valve (F15) are connected with the fourth pressure reducer (G01) through a sixteenth pressure sensor (G03);
the sixth solenoid valve (D18), the eighth solenoid valve (F17), the fourth solenoid valve (C30), and the second solenoid valve (a28) are connected to a fifth pressure reducer (G02) via a seventeenth pressure sensor (G04).
2. The experimental supply system for large liquid oxygen methane rocket engines according to claim 1, characterized in that the liquid oxygen storage tank (E01) is a high pressure liquid oxygen storage tank.
3. The experimental supply system for large liquid methanone rocket engines according to claim 1, wherein the liquid methane tank (E03) is a high pressure liquid methane tank.
4. The experimental supply system for large liquid methane oxide rocket engines of claim 1, wherein the gas methane storage tank (E04) is a high pressure gas methane storage tank.
5. The experimental supply system for large liquid methanone rocket engines according to claim 1, wherein the liquid nitrogen storage tank (E02) is a low pressure liquid nitrogen storage tank.
6. The experimental supply system for large liquid oxygen methane rocket engines according to claim 2, characterized in that the pressure of the liquid oxygen storage tank (E01) is 10 MPa.
7. The experimental supply system for large liquid methane oxide rocket engines according to claim 3, characterized in that the pressure of the liquid methane storage tank (E03) is 15 MPa.
8. The experimental supply system for large liquid methane oxide rocket engines of claim 4, wherein the pressure of the gas methane storage tank (E04) is 15 MPa.
9. The experimental supply system for large liquid methanone rocket engines according to claim 5, wherein the pressure of the liquid nitrogen storage tank (E02) is 0.8 MPa.
10. A rocket comprising a supply system adapted for testing a large liquid methanone rocket engine as recited in any one of claims 1-9.
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| CN109737829B (en) * | 2019-01-31 | 2024-03-26 | 蓝箭航天空间科技股份有限公司 | Rocket liquid storage tank propellant conveying system and carrier rocket |
| CN109916630A (en) * | 2019-03-27 | 2019-06-21 | 中南大学 | Engine supply system and its removable integration test platform |
| CN110043392B (en) * | 2019-03-29 | 2020-07-21 | 西安航天动力研究所 | Liquid rocket engine starting cold debugging system and method |
| CN111828202A (en) * | 2020-07-20 | 2020-10-27 | 航天科工火箭技术有限公司 | Test bed system of liquid rocket engine |
| CN112360646B (en) * | 2020-09-02 | 2023-06-23 | 航天科工火箭技术有限公司 | Low-temperature rocket engine, turbine pump and bearing cooling structure thereof |
| CN113252720B (en) * | 2021-06-07 | 2022-11-01 | 北京航空航天大学 | Two-phase flow mixing test system adopting liquid nitrogen and nitrogen cooling liquid oxygen |
| CN113586286A (en) * | 2021-07-08 | 2021-11-02 | 北京星途探索科技有限公司 | Liquid oxygen methane propellant supply system |
| CN113446133B (en) * | 2021-08-30 | 2021-11-23 | 西安航天动力研究所 | Ground screening test device and test method for oxygen-enriched methane-rich gas injection unit |
| CN113790110B (en) * | 2021-11-16 | 2022-02-25 | 西安空天引擎科技有限公司 | Integrated liquid flow test system for rocket engine |
| CN114739055B (en) * | 2022-04-11 | 2022-12-06 | 西安交通大学 | Liquid oxygen/liquid methane comprehensive supercooling system and method based on liquid oxygen refrigeration capacity |
| CN115384818B (en) * | 2022-08-25 | 2024-05-17 | 北京航天试验技术研究所 | Mars surface methane propellant in-situ preparation environment simulation device and method |
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| CN103411775A (en) * | 2013-07-22 | 2013-11-27 | 北京航空航天大学 | Fuel supplying system for liquid-propellant rocket engine test |
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