CN114776478B - Liquid rocket engine double-component propulsion system utilizing resonance ignition - Google Patents
Liquid rocket engine double-component propulsion system utilizing resonance ignition Download PDFInfo
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- CN114776478B CN114776478B CN202210555598.5A CN202210555598A CN114776478B CN 114776478 B CN114776478 B CN 114776478B CN 202210555598 A CN202210555598 A CN 202210555598A CN 114776478 B CN114776478 B CN 114776478B
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- 239000007788 liquid Substances 0.000 title claims abstract description 24
- GQPLMRYTRLFLPF-UHFFFAOYSA-N Nitrous Oxide Chemical compound [O-][N+]#N GQPLMRYTRLFLPF-UHFFFAOYSA-N 0.000 claims abstract description 160
- 239000000446 fuel Substances 0.000 claims abstract description 90
- 239000001272 nitrous oxide Substances 0.000 claims abstract description 80
- 238000010438 heat treatment Methods 0.000 claims abstract description 8
- 239000003380 propellant Substances 0.000 claims description 43
- 238000002485 combustion reaction Methods 0.000 claims description 13
- 239000002828 fuel tank Substances 0.000 claims description 13
- 230000002441 reversible effect Effects 0.000 claims description 13
- 238000012544 monitoring process Methods 0.000 claims description 6
- 238000007711 solidification Methods 0.000 claims description 5
- 230000008023 solidification Effects 0.000 claims description 5
- 230000009471 action Effects 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims description 3
- 238000010168 coupling process Methods 0.000 claims description 3
- 238000005859 coupling reaction Methods 0.000 claims description 3
- 238000004891 communication Methods 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 48
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 9
- 230000001276 controlling effect Effects 0.000 description 9
- 229910052757 nitrogen Inorganic materials 0.000 description 4
- 238000002679 ablation Methods 0.000 description 3
- 230000003197 catalytic effect Effects 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000001125 extrusion Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 239000007800 oxidant agent Substances 0.000 description 3
- 230000001590 oxidative effect Effects 0.000 description 3
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000004449 solid propellant Substances 0.000 description 2
- 241000282414 Homo sapiens Species 0.000 description 1
- 108091092878 Microsatellite Proteins 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 239000012752 auxiliary agent Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000003421 catalytic decomposition reaction Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 229910001873 dinitrogen Inorganic materials 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000011049 filling Methods 0.000 description 1
- 238000005429 filling process Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000003349 gelling agent Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 231100000572 poisoning Toxicity 0.000 description 1
- 230000000607 poisoning effect Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 229920006395 saturated elastomer Polymers 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
- 229910010271 silicon carbide Inorganic materials 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000004094 surface-active agent Substances 0.000 description 1
- 230000010356 wave oscillation Effects 0.000 description 1
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Classifications
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/401—Liquid propellant rocket engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
-
- 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
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
The invention discloses a liquid rocket engine bi-component propulsion system utilizing resonance ignition, which comprises: the device comprises a fuel storage tank, an engine, a nitrous oxide storage tank, a resonance ignition tube, a resonance heating phenomenon of nitrous oxide, a heating device and a control device, wherein a motor is arranged at the outer side of an inlet of the fuel storage tank and used for pushing a piston to move downwards through a coupler so as to extrude fuel in the fuel storage tank; compared with the traditional ignition mode, the invention uses the resonance ignition tube to perform ignition, has the advantages of high ignition temperature, simple structure, no need of accessing third gas, lightening the whole quality of the system and being capable of easily realizing multiple ignition starting.
Description
Technical Field
The invention belongs to the field of liquid rocket engines, and particularly relates to a liquid rocket engine double-component propulsion system utilizing resonance ignition.
Background
The attitude and orbit control system is an important component system of the satellite, and the propulsion system is a power source in the attitude and orbit control system. With the increasing demand of human beings on satellites, the development of a new generation satellite propulsion system with long working time and large thrust is a key point for prolonging the in-orbit duration and increasing the load of the satellites.
The common propellant of the propulsion system comprises a solid propellant and a liquid propellant, wherein the solid propellant has high safety coefficient, but has lower energy content and great difficulty in fuel filling, and the preprogrammed combustion mode of the propellant causes relatively difficult thrust adjustment, so the propellant is less applied to satellites; the liquid propellant has excellent specific impulse, is easy to fill and has adjustable thrust, but the liquid propellant is extremely easy to leak in the storage and filling processes, so that risks such as corrosion, poisoning, explosion and the like are caused, and the hydrazine propellant frequently applied to satellites is more so; another type of propulsion system often used on satellites is a cold gas propulsion system, i.e. the propellant is ejected from the nozzle by thermal catalytic decomposition or directly from the nozzle to obtain thrust, which has the disadvantage of a small specific impact. Therefore, finding a propellant which can achieve the advantages of high specific impulse, safety, capability of adjusting the thrust force for many times and the like is a key problem faced by the development of a propulsion system.
Disclosure of Invention
The invention aims to provide a liquid rocket engine double-component propulsion system utilizing resonance ignition, which solves the problems that in the prior art, the engine propellant adopting reversible curing propellant is difficult to supply and an ignition device is complex.
The invention adopts the following technical scheme: a liquid rocket engine bi-component propulsion system utilizing resonant ignition, comprising:
a fuel storage tank for storing reversible solidification propellant, a piston is arranged in the fuel storage tank, a motor is arranged at the outer side of an inlet of the fuel storage tank, the motor is used for pushing the piston to move downwards through a coupling so as to extrude fuel in the fuel storage tank,
an engine having an injector propellant inlet in communication with the fuel tank via a fuel conduit,
a nitrous oxide storage tank for storing nitrous oxide therein, an outlet of which is communicated with an injector nitrous oxide inlet of the engine through a gas pipe,
the inlet of the resonance ignition tube is also communicated with the outlet of the nitrous oxide storage tank through an ignition pipeline and is used for enabling nitrous oxide to generate resonance heating phenomenon, so that the nitrous oxide is heated to an ignition temperature to ignite the engine;
the resonance ignition tube includes:
the upper end of the driving nozzle is communicated with the ignition pipeline, the lower end of the driving nozzle is contracted inwards to form a cone-shaped ring,
a resonator tube whose axis coincides with the axis of the drive nozzle,
the axis of the connecting pipe is coincident with the axis of the driving nozzle, the connecting pipe is of a hollow columnar closed structure, an upper through hole and a lower through hole are respectively formed in the upper top and the lower bottom of the connecting pipe, the upper through hole is used for enabling the lower end of the driving nozzle to extend in, and the lower through hole is used for being communicated with a combustion chamber of an engine through a resonance tube.
Further, a piston baffle is arranged in the middle of the fuel storage tank, is positioned at the lower side of the piston, is coaxially arranged with the piston and is fixedly connected with the piston, and is used for moving downwards under the action of a motor so as to press fuel in the fuel storage tank into an injector propellant inlet of the engine;
a plurality of sliding fixing strips are uniformly and fixedly connected around the periphery of the side wall of the fuel storage tank, each sliding fixing strip is vertically arranged,
the edge of the piston baffle plate is inwards recessed to form concave pits, and each concave pit is used for the sliding fixing strip to extend in, so that the piston baffle plate can move up and down along the sliding fixing strip.
Further, a pressure sensor is arranged on the fuel storage tank, and a pressure sensor is arranged on the nitrous oxide storage tank.
Further, a fuel electromagnetic valve, a fuel flowmeter and a fuel cavitation venturi are arranged on the fuel pipeline, the fuel electromagnetic valve is used for controlling the on-off of the pipeline, the fuel flowmeter is used for monitoring the flow of fuel in the fuel pipeline, and the fuel cavitation venturi is used for controlling the flow of fuel.
Further, a gas solenoid valve, a gas flowmeter and a gas cavitation venturi are arranged on the gas pipeline, the gas solenoid valve is used for controlling on-off of the pipeline, the gas flowmeter is used for monitoring flow of nitrous oxide in the pipeline, and the gas cavitation venturi is used for controlling flow of nitrous oxide.
The beneficial effects of the invention are as follows: compared with the traditional ignition mode, the invention has the advantages that the ignition is performed by using the resonance ignition tube, the ignition temperature is high enough, the structure is simple, the third gas is not needed to be connected, the whole quality of the system is lightened, and the ignition starting for multiple times can be realized easily; the invention uses the piston to squeeze and supply the reversible solidification propellant, reduces the structural mass compared with the traditional nitrogen extrusion mode, reduces the volume of a supply system, reduces the complexity of the system, and realizes the integration of storage, pressurization and transportation and flow regulation of the propellant.
Drawings
FIG. 1 is a schematic diagram of a system of the present invention;
fig. 2 is a schematic structural view of the resonance squib of the present invention.
Wherein: 1. a fuel tank; 2. nitrous oxide storage tanks; 3. a resonance ignition tube; 4. injector propellant inlet; 5. a sparger nitrous oxide inlet; 6. an ignition tube; 7. a fuel pipe; 8. a gas conduit; 9. a combustion chamber; 10. a piston; 11. driving the nozzle; 12. a connecting pipe; 13. a resonance tube; 14. a motor; 15. an engine.
Detailed Description
The invention will be described in detail below with reference to the drawings and the detailed description.
The reversible solidified fuel is a solid form with stable surface 'insensitive' when stored and can be converted into liquid property when pressurized or sheared by gelling agent, energetic particles, surfactant, auxiliary agent and the like, so that the quick atomization and combustion can be realized, and the propellant has excellent performance, is safe and reliable, and is a good choice of fuel in satellite propulsion systems. Nitrous oxide is a normal temperature propellant capable of self-pressurization, the high saturated vapor pressure of the nitrous oxide is generally utilized to extrude the nitrous oxide by about 5.2MPa during application, a supply device does not need to be additionally arranged, the nitrous oxide is good in energy performance, the theoretical specific impact is about 206s, the nitrous oxide also has the advantages of being green and safe, the use temperature is high, and the like, and is an excellent choice of the oxidant in a satellite propulsion system.
The nitrous oxide/reversible curing propellant dual-component propulsion system has the advantages of larger thrust and higher energy efficiency compared with a cold air propulsion system, simpler structure and greener and safer propellants and products compared with a traditional liquid dual-component propulsion system, so the nitrous oxide/reversible curing propellant dual-component propulsion system is an excellent choice of a microsatellite attitude and orbit control system.
The existing nitrous oxide dual-component propulsion system is supplied with fuel in a main mode of being supplied by nitrogen in an extrusion mode, which means that the system needs to additionally carry nitrogen and a high-pressure gas cylinder, so that the additional mass of the propulsion system is greatly increased, the volume of the propulsion system is also increased by the gas cylinder, the volume of task units on a satellite is occupied, and the difficulty of satellite launching and working is increased by the additional mass and volume. In addition to the use of nitrogen gas for extrusion to supply the propellant, the vaporized nitrous oxide gas can be used to simultaneously extrude the liquid nitrous oxide and the fuel, so that a pressurizing device can not be introduced to reduce the weight of the system, however, the system has the problem that the supply system is too complex, and a plurality of pipelines and control elements are required to be introduced for achieving the purpose of extruding the fuel and the nitrous oxide by using the vaporized nitrous oxide gas and stably controlling the flow rate of the propellant, which clearly increases the difficulty in developing a micro-propulsion system. Therefore, developing a fuel supply system with simpler structure and smaller volume and mass is one of the key problems faced by the development of nitrous oxide/reversible curing propellant two-component propulsion systems.
Another problem with nitrous oxide/reversible curable propellant propulsion systems is the ignition problem, and the liquid engine ignition mode commonly used at this stage is the ignition of an electric igniter, i.e. the electric igniter is used to directly ignite the main flow of the propellant after mixing the oxidant with the fuel, which is less applicable to nitrous oxide/reversible curable propellant engines, because the ignition temperature of nitrous oxide and the reversible curable fuel is generally higher than the temperature that can be generated by a conventional electric igniter, which makes it difficult for the electric igniter to directly ignite the main flow of the propellant. In nitrous oxide propulsion systems, a common ignition method is catalytic ignition, i.e. nitrous oxide is first catalytically decomposed into nitrogen and oxygen, and the oxygen and fuel are used for ignition to ignite the main flow of the propellant, and this approach requires a catalytic bed and a high-power battery for heating the catalytic bed, which makes the propulsion system more complex in structure, consumes more energy, and has a longer ignition delay time. In a laboratory, a flare ignition mode is generally used for igniting a nitrous oxide engine, namely, a small oxyhydrogen flare is ignited first, and a main flow of a propellant is ignited by high-temperature fuel gas generated by the flare, so that the ignition mode is not suitable for being used on a satellite, and is another direction for improving the nitrous oxide propulsion system because the ignition mode makes a system too complex, and the ignition system has simpler structure and higher ignition efficiency and can be repeatedly started for many times.
Based on the above, the invention discloses a liquid rocket engine two-component propulsion system utilizing resonance ignition, which comprises a fuel storage tank 1, a nitrous oxide storage tank 2 and a resonance ignition tube 3 as shown in figure 1.
The fuel tank 1 is used for storing reversible solidification propellant, the piston 10 is arranged in the fuel tank 1, the motor 14 is arranged outside the inlet of the fuel tank 1, and the motor 14 is used for pushing the piston 10 to move downwards through the coupling so as to extrude fuel in the fuel tank 1.
The injector propellant inlet 4 of the engine 15 is connected to the fuel tank 1 via a fuel line 7, nitrous oxide is stored in the nitrous oxide tank 2, and the outlet of the nitrous oxide tank 2 is connected to the injector nitrous oxide inlet 5 of the engine 15 via a gas line 8.
The inlet of the resonance ignition tube 3 is also communicated with the outlet of the nitrous oxide storage tank 2 through an ignition pipeline 6, and the resonance ignition tube 3 is used for enabling nitrous oxide to generate resonance heating phenomenon, so that the nitrous oxide is heated to an ignition temperature, and the engine 15 is ignited.
The middle part of the fuel storage tank 1 is provided with a piston baffle plate which is positioned at the lower side of the piston 10, is coaxially arranged with the piston 10 and is fixedly connected with the piston 10, and the piston baffle plate is used for downwards moving under the action of the motor 14 so as to press the fuel in the fuel storage tank 1 into the injector propellant inlet 4 of the engine 15; a plurality of sliding fixing strips are uniformly and fixedly connected around the periphery of the side wall of the fuel storage tank 1, each sliding fixing strip is vertically arranged, the edge of the piston baffle plate is inwards recessed to form a recess, and each recess is used for the sliding fixing strip to extend in, so that the piston baffle plate can move up and down along the sliding fixing strip.
The fuel tank 1 is provided with a fuel pressure sensor, the fuel pipeline 7 is provided with a fuel electromagnetic valve, a fuel flowmeter and a fuel cavitation venturi, the fuel electromagnetic valve is used for controlling the on-off of a pipeline, the fuel flowmeter is used for monitoring the flow of fuel in the fuel pipeline 7, and the fuel cavitation venturi is used for controlling the flow of fuel to be kept at a design value.
The nitrous oxide storage tank 2 is provided with a gas pressure sensor, the gas pipeline 8 is provided with a gas solenoid valve, a gas flowmeter and a gas cavitation venturi, the gas solenoid valve is used for controlling the on-off of a pipeline, the gas flowmeter is used for monitoring the flow of nitrous oxide in the pipeline, and the gas cavitation venturi is used for controlling the flow of nitrous oxide to be kept at a design value.
The gas pressure sensor of the nitrous oxide storage tank 2 firstly controls the gas electromagnetic valve to be in an ignition mode, so that small-flow nitrous oxide gas enters the resonance ignition tube 3 to be ignited, and after the temperature rises, the gas pressure sensor controls the gas electromagnetic valve to be in a supply mode, and nitrous oxide supply is completed.
When the system works, the gas pressure sensor of the nitrous oxide storage tank 2 controls a small amount of nitrous oxide gas to enter the resonance ignition tube 3 through the pressure regulator, the nitrous oxide gas is heated to a preset temperature after a certain time, then the gas pressure sensor changes the requirement, so that the nitrous oxide passing through the pressure regulator meets the fixed pressure drop to finish the supply of the oxidant, meanwhile, the motor 14 drives the coupler with preset power, so that the piston 10 is driven to extrude fuel at a preset speed to finish the supply of the fuel, the fuel enters the injector propellant inlet 4, the nitrous oxide enters the injector nitrous oxide inlet 5, and the ignition is finished in the combustion chamber 9.
When the engine 15 works, the motor 14 drives the coupler to start working, the coupler drives the screw to start rotating, and the screw drives the piston 10 to move downwards to pressurize the fuel storage tank 1; the fuel pressure sensor monitors the pressure in the fuel tank 1, and when the preset working pressure is reached, the fuel pressure sensor sends out an instruction to open the fuel electromagnetic valve of the fuel pipeline 7, then the fuel flow is accurately regulated to a preset value, if the thrust of the engine 15 is to be changed, the fuel pressure sensor needs to send out an instruction to the motor 14, the power of the motor 14 is changed, the flow of the supplied fuel is changed by changing the movement speed of the piston 10, and then the thrust of the engine 15 is changed.
When the engine 15 is operated, gaseous nitrous oxide evaporated in the nitrous oxide tank 2 maintains the pressure in the nitrous oxide tank 2; the gas pressure sensor of the nitrous oxide storage tank 2 controls the gas electromagnetic valve to be in an ignition mode, the nitrous oxide gas with small flow enters the resonance ignition tube 3 to be ignited, and after the temperature rises, the gas pressure sensor of the nitrous oxide storage tank 2 controls the gas electromagnetic valve to be in a supply mode, so that nitrous oxide supply is completed.
When the engine 15 works and the temperature generated by the resonance ignition tube 3 is enough, fuel passes through the fuel pipeline 7, and nitrous oxide enters the combustion chamber 9 in the body of the engine 15 through the gas pipeline 8 for combustion; the reversible solidification propellant is liquid when entering the fuel pipeline 7, nitrous oxide is gas when entering the gas pipeline 8, nitrous oxide enters the combustion chamber 9 through the injector nitrous oxide inlet 5 of the gas-liquid coaxial injector, and the propellant enters the combustion chamber 9 in a liquid form through the injector propellant inlet 4 of the gas-liquid coaxial injector, so that combustion is completed in the combustion chamber 9; the inner surface of the body of the engine 15 is coated with an ablation-resistant material, and the ablation-resistant material is made of silicon carbide, so that the engine 15 has good ablation resistance and oxidation resistance and can be prolonged in service life.
When the engine 15 works, the air valve of the ignition pipeline 6 is opened, and the gaseous nitrous oxide enters the resonance ignition tube 3 to heat the gas by using a resonance heating effect, wherein the resonance heating effect is a thermal effect that the pneumatic resonance tube 13 in the air flow generates high-frequency shock wave oscillation under a certain pneumatic condition, so that sharp temperature rise is generated at the tail end of the resonance tube 13.
As shown in fig. 2, the resonance ignition tube 10 comprises a driving nozzle 11, a connecting tube 12 and a resonance tube 13, wherein the upper end of the driving nozzle 11 is communicated with the ignition tube 6, the lower end of the driving nozzle 11 is contracted inwards to form a cone-shaped ring, the lower end of the driving nozzle 11 stretches into the inner cavity of the connecting tube 12, and the length of the driving nozzle 11 stretching into the connecting tube 12 is 1/3 of the length of the connecting tube 12.
The connecting pipe 12 is of a hollow columnar closed structure, the axis of the connecting pipe 12 coincides with the axis of the driving nozzle 11, an upper through hole and a lower through hole are respectively formed in the upper top and the lower bottom of the connecting pipe 12, the upper through hole is used for enabling the lower end of the driving nozzle 11 to extend in, the lower through hole is used for being communicated with a combustion chamber 15 of an engine through a resonance pipe 13, the axis of the resonance pipe 13 coincides with the axis of the driving nozzle 11, and the diameter of the resonance pipe 13 is identical with the diameter of the lower end of the driving nozzle 11. The gaseous nitrous oxide is heated for about 5 seconds in a resonance way and then reaches the ignition temperature, nitrous oxide and the propellant are simultaneously supplied, and the two propellant flows are mixed and atomized and then ignited by the high-temperature nitrous oxide flow; and closing the air valve after the ignition is finished, and repeating the process if the ignition is required to be started repeatedly after the ignition is finished.
The working process of the invention comprises the following steps: the valve on the ignition pipeline 6 is opened, the fuel electromagnetic valve on the fuel pipeline 7 is closed, the gas electromagnetic valve on the gas pipeline 8 enables the nitrous oxide flow to be small, after a preset time, the fuel electromagnetic valve on the fuel pipeline 7 is opened, the gas electromagnetic valve on the gas pipeline 8 enables the nitrous oxide flow to be large, ignition is completed, then the valve on the ignition pipeline 6 is closed, and the pressure sensor of the nitrous oxide storage tank 2 and the gas electromagnetic valve jointly regulate the pressure in the gas pipeline 8 to be stable dynamically.
The foregoing is only illustrative of the present invention and is not to be construed as limiting thereof, but rather as various modifications, equivalent arrangements, improvements, etc., within the spirit and principles of the present invention.
Claims (5)
1. A liquid rocket engine bi-component propulsion system utilizing resonant ignition, comprising:
a fuel storage tank (1) for storing reversible solidification propellant, a piston (10) is arranged in the fuel storage tank, a motor (14) is arranged outside an inlet of the fuel storage tank, the motor (14) is used for pushing the piston (10) to move downwards through a coupling so as to extrude fuel in the fuel storage tank (1),
an engine (15) with injector propellant inlet (4) communicating with the fuel tank (1) via a fuel conduit (7),
a nitrous oxide storage tank (2) for storing nitrous oxide therein, the outlet of which is in communication with the injector nitrous oxide inlet (5) of the engine (15) via a gas conduit (8),
the inlet of the resonance ignition tube (3) is also communicated with the outlet of the nitrous oxide storage tank (2) through an ignition pipeline (6) and is used for leading nitrous oxide to generate resonance heating phenomenon, so that the nitrous oxide is heated to an ignition temperature and the engine (15) is ignited;
the resonance squib (3) comprises:
a driving nozzle (11) with the upper end communicated with the ignition pipeline (6) and the lower end contracted inwards to form a cone-shaped ring,
a resonator tube (13) whose axis coincides with the axis of the drive nozzle (11),
the connecting pipe (12) is of a hollow columnar closed structure, the axis of the connecting pipe coincides with the axis of the driving nozzle (11), an upper through hole and a lower through hole are respectively formed in the upper top and the lower bottom of the connecting pipe (12), the upper through hole is used for enabling the lower end of the driving nozzle (11) to extend in, and the lower through hole is used for being communicated with a combustion chamber of an engine through a resonance tube (13).
2. A liquid rocket engine two-component propulsion system using resonance ignition according to claim 1, characterized in that the middle part of the fuel tank (1) is provided with a piston baffle which is positioned at the lower side of the piston (10) and is coaxially arranged with the piston (10) and fixedly connected, and is used for downward movement under the action of a motor (14) so as to press the fuel in the fuel tank (1) into the injector propellant inlet (4) of the engine (15);
a plurality of sliding fixing strips are uniformly and fixedly connected around the periphery of the side wall of the fuel storage tank (1), each sliding fixing strip is vertically arranged,
the edges of the piston baffle plate are inwards recessed to form concave pits, and each concave pit is used for the sliding fixing strip to extend in, so that the piston baffle plate can move up and down along the sliding fixing strip.
3. A liquid rocket engine two-component propulsion system using resonant ignition according to claim 2, wherein the fuel tank (1) is provided with a pressure sensor and the nitrous oxide tank (2) is provided with a pressure sensor.
4. A liquid rocket engine two-component propulsion system using resonance ignition according to claim 3, wherein the fuel pipeline (7) is provided with a fuel electromagnetic valve, a fuel flowmeter and a fuel cavitation venturi, the fuel electromagnetic valve is used for controlling the on-off of the pipeline, the fuel flowmeter is used for monitoring the flow of fuel in the fuel pipeline (7), and the fuel cavitation venturi is used for controlling the flow of fuel.
5. A liquid rocket engine bi-component propulsion system utilizing resonance ignition according to any one of claims 1-4, wherein a gas solenoid valve, a gas flowmeter and a gas cavitation venturi are arranged on the gas pipeline (8), the gas solenoid valve is used for controlling on-off of the pipeline, the gas flowmeter is used for monitoring flow of nitrous oxide in the pipeline, and the gas cavitation venturi is used for controlling flow of nitrous oxide.
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| CN202210555598.5A CN114776478B (en) | 2022-05-20 | 2022-05-20 | Liquid rocket engine double-component propulsion system utilizing resonance ignition |
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| CN202210555598.5A CN114776478B (en) | 2022-05-20 | 2022-05-20 | Liquid rocket engine double-component propulsion system utilizing resonance ignition |
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| CN114776478B true CN114776478B (en) | 2023-06-09 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1210601A (en) * | 1967-02-11 | 1970-10-28 | Mtu Muenchen Gmbh | Rocket propulsion system |
| CN101852148A (en) * | 2009-04-01 | 2010-10-06 | 北京航空航天大学 | Oxygen/kerosene ignitor using pneumatic resonance ignition technology |
-
2022
- 2022-05-20 CN CN202210555598.5A patent/CN114776478B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1210601A (en) * | 1967-02-11 | 1970-10-28 | Mtu Muenchen Gmbh | Rocket propulsion system |
| CN101852148A (en) * | 2009-04-01 | 2010-10-06 | 北京航空航天大学 | Oxygen/kerosene ignitor using pneumatic resonance ignition technology |
Non-Patent Citations (1)
| Title |
|---|
| 液体火箭发动机气动谐振点火初步研究;梁国柱,张国舟,程显辰,马彬,张振鹏;推进技术(第04期);14-17 * |
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| CN114776478A (en) | 2022-07-22 |
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