CN111720239A - Liquid rocket power system capable of starting liquid rockets for multiple times with variable-depth pushing - Google Patents
Liquid rocket power system capable of starting liquid rockets for multiple times with variable-depth pushing Download PDFInfo
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- CN111720239A CN111720239A CN201910595291.6A CN201910595291A CN111720239A CN 111720239 A CN111720239 A CN 111720239A CN 201910595291 A CN201910595291 A CN 201910595291A CN 111720239 A CN111720239 A CN 111720239A
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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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
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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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
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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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
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Abstract
The invention relates to a liquid rocket engine, in particular to a depth variable-thrust multiple-starting liquid rocket power system; the technical problems that the performance of the existing lunar landing rocket engine is low, the propellant is toxic, the accessories of a pressurization system are complex, the propellant of the existing lunar landing and ascending aircraft orbit control and attitude control power system with liquid oxygen kerosene as the main propellant is not uniform, the propellant and a high-pressure storage tank thereof need to be additionally equipped, the volume and the mass of the existing lunar landing and ascending aircraft orbit control and attitude control power system are increased, the effective load of the liquid rocket engine is reduced, and the launching cost is increased are solved. A liquid rocket power system with variable-depth push and multiple-starting comprises a liquid rocket engine, a propellant supply system and an aerogen gas generator; the gas-oxygen gas generator is used for combusting liquid oxygen and kerosene provided by the propellant supply system to generate high oxygen-enriched gas and storing the high oxygen-enriched gas; the liquid rocket engine is a liquid rocket engine started for multiple times by depth variable thrust based on liquid oxygen expansion cycle.
Description
Technical Field
The invention relates to a liquid rocket power system, in particular to a depth variable-pushing multiple-starting liquid rocket power system.
Background
In the process of lunar exploration and (manned) lunar landing tasks, in order to realize lunar orbit transfer and lunar soft landing, the engine is required to have the performances of multiple starting, working condition depth adjustment (10% -100%), long-time working (1000s), reliable working and the like.
The American Apollo lunar descent engine adopts a squeezing type system with hydrazine and dinitrogen tetroxide, and the engine of the type has simple structure, high reliability, low performance and toxic propellant.
The former soviet union proposed an "L-3" lunar chamber power system, in the form of an integration of a descent engine and an ascent engine, in which the main engine uses a gasifier cycle of unsymmetrical dimethylhydrazine and dinitrogen tetroxide, which is an open cycle, of moderate performance but relatively complex construction.
The 7500N lunar variable thrust engine proposed by China adopts an extrusion type system of unsymmetrical dimethylhydrazine and dinitrogen tetroxide and adopts a pintle injector to realize variable thrust, and the engine is simple and reliable, but the performance of the engine is inferior to that of a closed circulation system.
The fuel gas generator is also called as a precombustion chamber, is mainly used as a combustion assembly of a pumping liquid rocket engine, is mainly used for generating high-temperature fuel gas to drive a turbine to do work and pressurize a propellant.
The existing attitude control power system of the lunar landing and ascending aircraft adopts propellant which is generally different from main propellant, so that the propellant used for the attitude control power system and a high-pressure storage tank thereof need to be additionally equipped, the volume and the mass of the liquid rocket engine are increased, the effective load of the liquid rocket engine is reduced, and the launching cost is increased.
Disclosure of Invention
The invention provides a liquid rocket power system with depth-variable propelling and multiple starting, aiming at solving the technical problems that the performance of the existing lunar landing rocket engine is low, a propellant is toxic, and the accessories of a pressurizing system are complex, and the propellant of the existing lunar landing and ascending aircraft orbit control and attitude control power system is not uniform, and the propellant and a high-pressure storage tank thereof need to be additionally equipped, so that the volume and the mass of the existing lunar landing and ascending aircraft are increased, the effective load of the liquid rocket engine is reduced, and the launching cost is increased.
The technical solution of the invention is as follows:
a liquid rocket power system with variable-depth push and multiple-start comprises a liquid rocket engine and a propellant supply system; the propellant supply system comprises a liquid oxygen storage tank, a kerosene storage tank, a helium storage tank and a pressure reducing valve bank; an outlet of the liquid oxygen storage tank is provided with an oxygen pre-pressing turbine pump; it is characterized in that:
also comprises a gas oxygen gas generator; the gas-oxygen gas generator is used for combusting liquid oxygen and kerosene provided by the propellant supply system to generate high oxygen-enriched gas and storing the high oxygen-enriched gas;
the liquid rocket engine is a liquid rocket engine started for multiple times by changing depth and pushing based on liquid oxygen expansion cycle, and comprises a thrust chamber, a gas flow regulating device, a turbo pump set, a fuel flow regulating device, a liquid oxygen throttle valve, a first switch valve, a first gas oxygen kerosene torch igniter, a second gas oxygen kerosene torch igniter and a helium gas control unit; the thrust chamber comprises a combustion chamber and a nozzle; a spray pipe cooling interlayer is arranged in the spray pipe;
the turbopump set comprises a main turbine, an oxidant pump, a forced starting turbine and a fuel pump which are coaxially and fixedly connected and mutually isolated in sequence;
the first gas oxygen kerosene torch igniter is arranged above the combustion chamber of the thrust chamber, a first gas oxygen inlet G2 of the first gas oxygen torch igniter is connected with an outlet of the gas oxygen storage box, a kerosene inlet R2 of the first gas oxygen torch igniter is connected with an outlet of the kerosene storage box, and an outlet of the first gas oxygen torch igniter is arranged in the combustion chamber of the thrust chamber;
the second gas oxygen kerosene torch igniter is arranged on the forced starting turbine, a first gas oxygen inlet G3 of the second gas oxygen kerosene torch igniter is connected with an outlet of the gas oxygen storage box, a kerosene inlet R3 of the second gas oxygen kerosene torch igniter is connected with an outlet of the kerosene storage box, and an outlet of the second gas oxygen kerosene torch igniter is connected with an inlet of the forced starting turbine; the outlet of the forced starting turbine is communicated with the outside;
the inlet of the fuel pump is connected with the outlet of the kerosene storage tank, the outlet of the fuel pump is sequentially connected with a fuel flow regulating device and a first switch valve, and the outlet of the first switch valve is connected with a combustion chamber of the thrust chamber;
the inlet of the oxidant pump is connected with the outlet of the liquid oxygen storage tank, the outlet of the oxidant pump is two, one outlet is connected with the oxygen pre-pressing turbine driving inlet of the oxygen pre-pressing turbine pump, the other outlet is connected with the inlet of the spray pipe cooling interlayer after passing through the liquid oxygen throttle valve, the mixture is evaporated into gas oxygen in the spray pipe cooling interlayer and then divided into three paths, one path is connected with the first gas oxygen inlet of the gas oxygen storage tank, and the other two paths respectively enter the combustion chamber of the thrust chamber after passing through the gas flow regulating device and the main turbine;
a second gas-oxygen inlet of the gas-oxygen storage tank is connected with a first outlet of the high oxygen-enriched fuel gas storage tank;
the helium control unit comprises a helium storage tank, a switch, a pressure reducing valve group, two liquid oxygen pipeline controllers (DC1 and DC2) and two kerosene pipeline controllers (DC3 and DC 4);
two air control ports (C1 and C2) of the liquid oxygen throttle valve are respectively connected with two liquid oxygen pipeline controllers (DC1 and DC 2);
and the two pneumatic control ports (C3 and C4) of the first switch valve are respectively connected with two kerosene pipeline controllers (DC3 and DC 4).
Further, the gas-oxygen gas generator comprises a generator, a water removal device, a second switch valve, a high oxygen-enriched gas storage tank, a third switch valve, two groups of multi-stage one-way valve sets and a pressure reducing valve;
a third gas oxygen kerosene torch igniter is arranged on the generator;
a liquid oxygen inlet of the generator is connected with an A port of the liquid oxygen storage box, a kerosene inlet of the generator is connected with a B port of the kerosene storage box, and an outlet of the generator is connected with an inlet of the water removal device; the outlet of the water removal device is connected with the inlet of the second switch valve; the outlet of the second switch valve is connected with the inlet of one group of the multi-stage check valve group; the outlet of the multi-stage check valve group is connected with the inlet of the high oxygen-enriched fuel gas storage tank, and the first outlet of the high oxygen-enriched fuel gas storage tank is connected with the gas oxygen storage tank; a second outlet of the high oxygen-enriched fuel gas storage tank is connected with an inlet of the third switch valve; the outlet of the third switch valve is connected with the inlet of the other group of multi-stage check valve sets, and the outlet of the group of multi-stage check valve sets is connected with the inlet of the reducing valve; the outlet of the pressure reducing valve is respectively connected with the gas oxygen inlet G0 of the third gas oxygen kerosene torch igniter and the gas oxygen inlet of the attitude control engine; and a kerosene inlet R0 of the third gas oxygen kerosene torch igniter and a kerosene inlet of the attitude control engine are connected with a port B of the kerosene storage box.
Further, the gas flow regulating device and the fuel flow regulating device are both flow regulators.
Furthermore, the multistage check valve group comprises two groups of check valve groups connected in parallel, and each group of check valve groups connected in parallel comprises two check valves connected in series.
Further, the liquid oxygen throttle valve and the first switch valve are both electric gas valves.
Further, the water removal device is a centrifugal water remover.
Further, the second switch valve is an electric air valve.
Further, the third switch valve is an electric explosion valve.
Further, the thrust chamber nozzle area ratio is 200.
Further, the thrust chamber is provided with a mechanical positioning pin injector.
Compared with the prior art, the invention has the beneficial effects that:
1. the liquid rocket engine is based on the liquid oxygen regeneration cooling expansion circulation principle, the advantages of large flow of gas oxygen and relatively low flow resistance of regeneration cooling are fully utilized, liquid oxygen and kerosene are used as propellants, the liquid oxygen is used for carrying out regeneration cooling on a thrust chamber, the liquid oxygen absorbs heat and evaporates to form gas oxygen at a certain temperature, a turbine in a turbine pump is driven to do work, and the propellant is pressurized; the extrusion type extrusion die does not need to be provided with a precombustion chamber, has a simple structure, and has higher performance than an extrusion type system.
2. The gas oxygen pipeline and the kerosene pipeline are respectively provided with a gas flow regulating device and a fuel flow regulating device, and the thrust chamber is provided with a mechanical positioning pintle injector, wherein the gas flow regulating device can directly guide gas oxygen from the front of the main turbine to the back of the main turbine so as to regulate the power of the main turbine, so that the working condition of the invention can be deeply regulated; the fuel flow adjusting device is used for adjusting the kerosene flow in the working condition depth adjusting project, and ensures that the combustion stability of the thrust chamber is good and the cooling is reliable under low working conditions.
3. The thrust chamber of the invention adopts a gas oxygen kerosene torch igniter, and gas oxygen and kerosene for ignition are both from other devices, so that the invention can realize reliable starting (ignition) for many times, and the starting times are not less than 20 times.
4. The invention adopts a self-filling type gas oxygen storage tank which is used for storing part of gas oxygen obtained after liquid oxygen is evaporated and preparing for multiple ignition.
5. The turbopump adopted in the liquid rocket engine comprises a forced starting turbine, and when the turbopump is started, the second gas oxygen kerosene torch ignition device generates gas to drive the forced starting turbine to start, so that the fast starting can be realized.
6. The propellant is gas oxygen and kerosene, and is non-toxic and environment-friendly.
7. The invention continuously or discontinuously works according to the working requirement, the kerosene and the liquid oxygen are combusted to generate the high oxygen-enriched fuel gas, the generated high oxygen-enriched fuel gas is dewatered and then stored in the oxygen-enriched fuel gas storage tank, high-pressure gas oxygen is provided for the attitude control power system, a propellant and a high-pressure storage tank thereof do not need to be additionally arranged, the effective load of the liquid rocket engine is increased, and the launching cost is reduced.
8. The invention utilizes the gas oxygen in the oxygen-enriched gas storage tank to supply gas oxygen for the gas generator and the gas oxygen kerosene torch igniter of the engine, the pressure of the oxygen-enriched gas storage tank is always kept at 4-6 MPa, and the reliable ignition of each gas oxygen kerosene torch igniter for many times can be ensured.
9. The liquid oxygen and the kerosene of the invention are respectively from the descending liquid oxygen storage tank and the kerosene storage tank, thus realizing the integration of the propellant of the rail and attitude control power system.
Drawings
FIG. 1 is a schematic block diagram of one embodiment of the present invention;
fig. 2 is an upper view of the embodiment broken by the break line 1;
fig. 3 is a middle view of the embodiment broken by the break lines 1, 2;
fig. 4 is a lower view of the embodiment broken by the break line 2;
the reference signs are:
1-thrust chamber, 2-gas oxygen storage tank, 201-first gas oxygen inlet, 202-second gas oxygen inlet, 203-outlet, 3-gas flow regulating device, 4-turbopump set, 405-main turbine, 406-oxidant pump, 407-forced start turbine, 408-fuel pump, 5-fuel flow regulating device, 6-liquid oxygen throttle valve, 7-first switch valve, 8-first gas oxygen kerosene torch igniter, 9-second gas oxygen kerosene torch igniter, 10-ball valve, 11-helium control unit, 1101-helium storage tank, 1102-switch and pressure reducing valve bank, 12-generator, 1201-kerosene inlet, 1202-liquid oxygen inlet, 1203-third gas oxygen kerosene torch igniter, 13-water removing device, 14-a second switch valve, 15-a high oxygen-enriched gas storage tank, 1501-a first outlet, 1502-a second outlet, 16-a third switch valve, 17-a multistage check valve bank, 1701-a check valve, 18-a pressure reducing valve, 19-a liquid oxygen storage tank, 20-a kerosene storage tank, 21-a helium storage tank, 22-a pressure reducing valve bank, 23-an attitude control engine and 24-an oxygen pre-pressing turbine pump.
Detailed Description
The invention is further described with reference to the following figures and specific embodiments.
Referring to fig. 1 and 2, the present power system includes a liquid rocket engine, a propellant supply system, and an oxygen-gas fuel generator; the propellant supply system includes a liquid oxygen tank 19, a kerosene tank 20 and a helium pressurizing unit. The helium pressurizing unit comprises a helium storage tank 21 and a pressure reducing valve group 22. An outlet of the liquid oxygen storage tank is provided with an oxygen pre-pressurizing turbine pump 24; helium in the helium storage tank is decompressed by the decompression valve group 22 and then respectively pressurizes the liquid oxygen storage tank 19 and the kerosene storage tank 20.
The gas oxygen gas generator is used for combusting liquid oxygen and kerosene provided by the propellant supply system to generate and store high oxygen-enriched gas.
Referring to fig. 1 and 3, the liquid rocket engine is a liquid rocket engine started multiple times by changing the depth of a liquid oxygen expansion cycle, and comprises a thrust chamber 1, a gas oxygen storage tank 2, a gas flow regulating device 3, a turbo pump set 4, a fuel flow regulating device 5, a liquid oxygen throttle valve 6, a second switch valve 7, a first gas oxygen kerosene torch igniter 8, a second gas oxygen kerosene torch igniter 9 and a helium gas control unit 11. The thrust chamber 1 comprises a combustion chamber and a spray pipe, a spray pipe cooling interlayer is arranged in the spray pipe, and a first gas oxygen kerosene torch igniter 8 is arranged above the combustion chamber of the thrust chamber 1. The outlet of the gas oxygen storage tank 2 is provided with a ball valve 10.
The turbo-pump group 4 includes a main turbine 405, an oxidizer pump 406, a forced start turbine 407, and a fuel pump 408, which are coaxially attached and isolated from each other in this order.
The inlet of the oxidant pump 406 is connected with the outlet of the liquid oxygen storage tank 19, the outlet of the oxidant pump 406 is two, one outlet is connected with the oxygen pre-pressurizing turbine driving inlet of the oxygen pre-pressurizing turbine pump 24, and the other outlet is connected with the inlet of the liquid oxygen throttle valve 6; the outlet of the liquid oxygen throttle valve 6 is connected with a spray pipe cooling interlayer of the thrust chamber 1; the outlet of the thrust chamber 1 is respectively connected with the first gas-oxygen inlet 201 of the gas-oxygen storage tank 2, the inlet of the gas flow regulating device 3 and the inlet of the turbo pump set 4. The second gas-oxygen inlet 202 of the gas-oxygen storage tank 2 is connected with the high oxygen-enriched gas storage tank 15, and the outlet of the gas-oxygen storage tank 2 is respectively connected with the first gas-oxygen inlet G2 of the first gas-oxygen kerosene torch igniter 8 and the first gas-oxygen inlet G3 of the second gas-oxygen kerosene torch igniter 9; a kerosene inlet R2 of the first gas oxygen kerosene torch igniter 8 and a kerosene inlet R3 of the second gas oxygen kerosene torch igniter 9 are respectively connected with an outlet of the kerosene storage tank; the outlet of the igniter 8 of the first gas-oxygen kerosene torch is arranged in the combustion chamber of the thrust chamber 1.
The inlet of the fuel pump 408 is connected to the outlet of the kerosene tank 20, the outlet of the fuel pump 408 is connected to the inlet of the fuel flow rate adjusting device 5, the outlet of the fuel flow rate adjusting device 5 is connected to the inlet of the on-off valve 7, and the outlet of the on-off valve 7 is connected to the combustion chamber of the thrust chamber 1.
The inlet of the forced starting turbine 407 is connected with the outlet of the second kerosene torch igniter 9, and the outlet of the forced starting turbine 407 is communicated with the outside.
The helium control unit 11 comprises a helium tank 1101, a switch and pressure reducing valve bank 1102, two liquid oxygen line controllers DC1, DC2, two kerosene line controllers DC3, DC 4. Two air control ports C1 and C2 of the liquid oxygen throttle valve 6 are respectively connected with two liquid oxygen pipeline controllers DC1 and DC 2; two pneumatic control ports C3 and C4 of the switch valve 7 are respectively connected with two kerosene pipeline controllers DC3 and DC 4.
In the embodiment, the gas flow regulating device 3 and the fuel flow regulating device 5 are both flow regulators, the liquid oxygen throttle valve 6 and the switch valve 7 are both electric gas valves, the area ratio of the thrust chamber spray pipe is 200, the spray pipe cooling interlayer is arranged at the part with the area ratio smaller than 12, and the rest parts except the spray pipe cooling interlayer are made of ablation composite materials. This embodiment employs a thrust chamber with a mechanically positioned pintle injector.
Referring to fig. 1 and 2, the gas-oxygen fuel gas generator includes a generator 12, a water removal device 13, a second on-off valve 14, a highly oxygen-rich fuel gas tank 15, a third on-off valve 16, a multi-stage check valve group 17, and a pressure reducing valve 18. The generator 12 is provided with a third gas oxygen kerosene torch igniter 1203.
A liquid oxygen inlet 1202 of the generator 12 is connected with a port A of the liquid oxygen storage box 19, and a kerosene inlet 1201 of the generator 12 is connected with a port B of the kerosene storage box 20; the outlet of the generator 12 is connected with the inlet of the water removal device 13; the outlet of the water removal device 13 is connected with the inlet of a second switch valve 14; the outlet of the second switch valve 14 is connected with the inlet of one group of the multi-stage check valve group 17; the outlet of the multi-stage check valve group 17 is connected with the inlet of the high oxygen-enriched fuel gas storage tank 15, and the first outlet 1501 of the high oxygen-enriched fuel gas storage tank 15 is connected with the gas oxygen storage tank 2; a second outlet 1502 of the high oxygen-enriched fuel gas storage tank 15 is connected with an inlet of a third switch valve 16; the outlet of the third switch valve 16 is connected with the inlet of another group of multi-stage check valve set 17, and the outlet of the group of multi-stage check valve set 17 is connected with the inlet of a reducing valve 18; the outlet of the pressure reducing valve 18 is connected with a gas oxygen inlet G0 of a gas oxygen kerosene torch igniter 1203 and a gas oxygen inlet of an attitude control engine 23; the kerosene inlet R0 of the gas oxygen kerosene torch igniter 1203 and the kerosene inlet of the attitude control engine 23 are connected with the port B of the kerosene storage box 20.
The working principle of the power system is as follows:
referring to fig. 1, 2, 3 and 4, helium in the helium storage tank 21 is depressurized by the pressure reducing valve group 22 and then respectively pressurizes the liquid oxygen storage tank 19 and the kerosene storage tank 20. The second kerosene torch igniter 9 is ignited, and the forced starting turbine 407 is started, so that the turbine 405, the oxidant pump 406 and the fuel pump 408 are driven to start.
The liquid oxygen in the liquid oxygen storage tank 19 is divided into two paths after entering from the inlet of the oxidant pump 406, the first path enters the oxygen pre-pressurizing turbine driving inlet of the oxygen pre-pressurizing turbine pump 24 to drive the oxygen pre-pressurizing turbine and drive the oxygen pre-pressurizing turbine pump 24 to do work, so that the liquid oxygen storage tank 19 is pressurized; the second path enters a spray pipe cooling interlayer of the thrust chamber 1 after passing through a liquid oxygen throttle valve 6 to perform regenerative cooling on the thrust chamber 1, the liquid oxygen absorbs heat and evaporates to form gas oxygen at a certain temperature, and then the gas oxygen is divided into three parts, wherein most of the gas oxygen is used for driving a main turbine 405 to do work, and the rest of the gas oxygen is used for filling a gas oxygen storage tank 2 or enters a combustion chamber of the thrust chamber 1 for combustion after passing through a gas flow regulating device 3. The oxygen used to drive the main turbine 405 to do work also enters the combustion chamber of the thrust chamber 1 for combustion. The main turbine 405 is stopped by forcibly starting the turbine 407 after stabilizing its operation. The gas flow regulator 3 can lead the oxygen from the front of the main turbine 405 to the back of the main turbine 405 directly, thereby regulating the power of the main turbine 405, and the working condition of the engine can be deeply regulated. Kerosene in the kerosene storage tank 20 enters from the inlet of the fuel pump 408, passes through the fuel flow rate adjusting device 5 and the on-off valve 7, enters the combustion chamber of the thrust chamber 1, and is mixed and combusted with oxygen in the combustion chamber of the thrust chamber 1.
The gas-oxygen storage tank 2 supplies gas oxygen for the first gas-oxygen kerosene torch igniter 8 and the second gas-oxygen kerosene torch igniter 9, and the kerosene storage tank 20 supplies kerosene for the first gas-oxygen kerosene torch igniter 8 and the second gas-oxygen kerosene torch igniter 9. The first gas oxygen kerosene torch igniter 8 and the second gas oxygen kerosene torch igniter 9 can realize reliable ignition for a plurality of times, and the starting times are not less than 20 times. The gas oxygen storage tank 2 is used for storing regenerative cooling gas oxygen and storing gas oxygen for multiple ignition.
The helium gas control unit 11 controls the on/off of the liquid oxygen throttle valve 6 and the on/off valve 7.
Kerosene and liquid oxygen enter the generator 12 through a liquid oxygen inlet 1202 and a kerosene inlet 1201 of the generator 12 respectively for combustion to generate high oxygen-enriched fuel gas (the high oxygen-enriched fuel gas comprises O)2、CO2And H2O is high-temperature, high-oxygen-enriched and high-pressure gas with the pressure of 4-6 MPa, and the high-oxygen-enriched gas sequentially passes through a water removal device 13 for water removal and a second switch valve 14 and then enters a high-oxygen-enriched gas storage tank 15. The high oxygen-enriched gas from the high oxygen-enriched gas storage tank 15 is divided into two paths, one path enters the gas oxygen storage tank 2 for storage, and the other path sequentially passes through a second switch valve 16 and a multistage check valve group 17 and then is decompressed to 1-2 MPa through a decompression valve 18 to supply gas oxygen to the attitude control engine 23 and other gas oxygen kerosene torch igniters. G1 is the gas oxygen inlet of other gas oxygen kerosene torch igniter, R1 is the kerosene inlet of other gas oxygen kerosene torch igniter.
The above description is only an embodiment of the present invention, and is not intended to limit the scope of the present invention, and all equivalent structural changes made by using the contents of the present specification and the drawings, or applied directly or indirectly to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. A liquid rocket power system with variable-depth push and multiple-start comprises a liquid rocket engine and a propellant supply system; the propellant supply system comprises a liquid oxygen storage tank (19), a kerosene storage tank (20), a helium storage tank (21) and a pressure reducing valve bank (22); an outlet of the liquid oxygen storage tank is provided with an oxygen pre-pressurizing turbine pump (24);
the method is characterized in that:
also comprises a gas oxygen gas generator; the gas-oxygen gas generator is used for combusting liquid oxygen and kerosene provided by the propellant supply system to generate high oxygen-enriched gas and storing the high oxygen-enriched gas;
the liquid rocket engine is a liquid rocket engine started for multiple times by changing depth and pushing based on liquid oxygen expansion cycle, and comprises a thrust chamber (1), a gas oxygen storage tank (2), a gas flow regulating device (3), a turbopump set (4), a fuel flow regulating device (5), a liquid oxygen throttle valve (6), a first switch valve (7), a first gas oxygen kerosene torch igniter (8), a second gas oxygen kerosene torch igniter (9) and a helium gas control unit (11); the thrust chamber (1) comprises a combustion chamber and a nozzle; a spray pipe cooling interlayer is arranged in the spray pipe;
the turbopump set (4) comprises a main turbine (405), an oxidant pump (406), a forced start turbine (407) and a fuel pump (408) which are coaxially and fixedly connected and isolated from each other in sequence;
the first gas oxygen kerosene torch igniter (8) is arranged above the combustion chamber of the thrust chamber (1), a first gas oxygen inlet G2 is connected with an outlet (203) of the gas oxygen storage box (2), a kerosene inlet R2 is connected with an outlet of the kerosene storage box, and an outlet of the first gas oxygen kerosene torch igniter is arranged in the combustion chamber of the thrust chamber (1);
the second gas oxygen kerosene torch igniter (9) is arranged on the forced starting turbine (407), a first gas oxygen inlet G3 of the second gas oxygen kerosene torch igniter is connected with an outlet (203) of the gas oxygen storage tank (2), a kerosene inlet R3 of the second gas oxygen kerosene torch igniter is connected with an outlet of the kerosene storage tank, and an outlet of the second gas oxygen kerosene torch igniter is connected with an inlet of the forced starting turbine (407); the outlet of the forced starting turbine (407) is communicated with the outside;
the inlet of the fuel pump (408) is connected with the outlet of the kerosene storage tank (20), the outlet of the fuel pump (408) is sequentially connected with a fuel flow regulating device (5) and a first switch valve (7), and the outlet of the first switch valve (7) is connected with the combustion chamber of the thrust chamber (1);
the inlet of the oxidant pump (406) is connected with the outlet of the liquid oxygen storage tank (19), the outlets of the oxidant pump (406) are two, one of the outlets is connected with the oxygen pre-pressurizing turbine driving inlet of the oxygen pre-pressurizing turbine pump (24), the other outlet is connected with the inlet of the spray pipe cooling interlayer after passing through the liquid oxygen throttle valve (6), the outlets are evaporated into oxygen in the spray pipe cooling interlayer and then divided into three paths, one path is connected with the first oxygen inlet (201) of the gas oxygen storage tank (2), and the other two paths respectively enter the combustion chamber of the thrust chamber (1) after passing through the gas flow regulating device (3) and the main turbine (405);
a second gas-oxygen inlet (202) of the gas-oxygen storage tank (2) is connected with a first outlet (1501) of the high oxygen-enriched fuel gas storage tank (15);
the helium control unit (11) comprises a helium storage tank (1101), a switch and pressure reducing valve group (1102), two liquid oxygen pipeline controllers (DC1, DC2) and two kerosene pipeline controllers (DC3, DC 4);
two air control ports (C1 and C2) of the liquid oxygen throttle valve (6) are respectively connected with two liquid oxygen pipeline controllers (DC1 and DC 2);
two pneumatic control ports (C3 and C4) of the first switch valve (7) are respectively connected with two kerosene pipeline controllers (DC3 and DC 4).
2. A variable depth push multiple start liquid rocket power system according to claim 1 wherein:
the gas oxygen gas generator comprises a generator (12), a water removal device (13), a second switch valve (14), a high oxygen-enriched gas storage tank (15), a third switch valve (16), two groups of multi-stage one-way valve sets (17) and a pressure reducing valve (18);
a third gas oxygen kerosene torch igniter (1203) is arranged on the generator (12);
a liquid oxygen inlet (1202) of the generator (12) is connected with an A port of a liquid oxygen storage tank (19), a kerosene inlet (1201) of the generator (12) is connected with a B port of a kerosene storage tank (20), and an outlet of the generator (12) is connected with an inlet of the water removal device (13); the outlet of the water removal device (13) is connected with the inlet of the second switch valve (14); the outlet of the second switch valve (14) is connected with the inlet of one group of the multi-stage check valve group (17); the outlet of the multi-stage check valve group (17) is connected with the inlet of the high oxygen-enriched fuel gas storage tank (15), and the first outlet (1501) of the high oxygen-enriched fuel gas storage tank (15) is connected with the gas oxygen storage tank (2); a second outlet (1502) of the high oxygen-enriched fuel gas storage tank (15) is connected with an inlet of the third switch valve (16); the outlet of the third switch valve (16) is connected with the inlet of another group of multi-stage check valve sets (17), and the outlet of the group of multi-stage check valve sets (17) is connected with the inlet of the reducing valve (18); the outlet of the pressure reducing valve (18) is respectively connected with the oxygen inlet G0 of the third oxygen kerosene torch igniter (1203) and the oxygen inlet of the attitude control engine (23); the kerosene inlet R0 of the third oxygen kerosene torch igniter (1203) and the kerosene inlet of the attitude control engine (23) are connected with the port B of the kerosene storage box (20).
3. A variable depth push multiple start liquid rocket power system according to claim 1 or 2 wherein: the gas flow regulating device (3) and the fuel flow regulating device (5) are both flow regulators.
4. A variable depth push multiple start liquid rocket power system according to claim 3 wherein: the multi-stage check valve group (17) comprises two groups of check valve groups connected in parallel, and each group of check valve groups connected in parallel comprises two check valves (1701) connected in series.
5. The variable depth push multiple start liquid rocket power system according to claim 4, wherein: the liquid oxygen throttle valve (6) and the first switch valve (7) are both electric air valves.
6. A variable depth push multiple start liquid rocket power system according to claim 5 wherein: the water removing device (13) is a centrifugal water remover.
7. The variable depth multiple start liquid rocket power system according to claim 6, wherein: the second switch valve (14) is an electric air valve.
8. The variable depth push multiple start liquid rocket power system according to claim 7, wherein: the third switch valve (16) is an electric explosion valve.
9. The variable depth push multiple start liquid rocket power system according to claim 8, wherein: the thrust chamber nozzle area ratio is 200.
10. A variable depth push multiple start liquid rocket power system according to claim 9 wherein: the thrust chamber (1) is provided with a mechanical positioning pin injector.
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| CN118066038A (en) * | 2024-04-25 | 2024-05-24 | 北京中科宇航技术有限公司 | 110 Ton thrust open cycle pintle liquid oxygen kerosene rocket engine |
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