CN114776478A - Liquid rocket engine two-component propulsion system utilizing resonance ignition - Google Patents
Liquid rocket engine two-component propulsion system utilizing resonance ignition Download PDFInfo
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- CN114776478A CN114776478A CN202210555598.5A CN202210555598A CN114776478A CN 114776478 A CN114776478 A CN 114776478A CN 202210555598 A CN202210555598 A CN 202210555598A CN 114776478 A CN114776478 A CN 114776478A
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- 239000007788 liquid Substances 0.000 title claims abstract description 26
- 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 100
- 239000001272 nitrous oxide Substances 0.000 claims abstract description 80
- 239000003380 propellant Substances 0.000 claims abstract description 42
- 238000010438 heat treatment Methods 0.000 claims abstract description 8
- 238000002485 combustion reaction Methods 0.000 claims description 13
- 230000002441 reversible effect Effects 0.000 claims description 9
- 238000012544 monitoring process Methods 0.000 claims description 6
- 230000009471 action Effects 0.000 claims description 3
- 239000002828 fuel tank Substances 0.000 claims 4
- 239000007789 gas Substances 0.000 description 48
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 10
- 238000000034 method Methods 0.000 description 5
- 229910052757 nitrogen Inorganic materials 0.000 description 5
- 238000002679 ablation Methods 0.000 description 3
- 230000003197 catalytic effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 239000007800 oxidant agent Substances 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
- 238000001125 extrusion Methods 0.000 description 2
- 230000001590 oxidative effect Effects 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
- 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
- 230000008859 change Effects 0.000 description 1
- 239000000470 constituent Substances 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
- 238000004880 explosion Methods 0.000 description 1
- 238000011049 filling Methods 0.000 description 1
- 238000005429 filling process Methods 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
- 229920006395 saturated elastomer Polymers 0.000 description 1
- 238000010008 shearing Methods 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
Images
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)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
The invention discloses a liquid rocket engine two-component propulsion system using resonance ignition, comprising: the engine is characterized in that a motor is arranged on the outer side of an inlet of the fuel storage tank, the motor is used for pushing a piston to move downwards through a coupler so as to extrude fuel in the fuel storage tank, an injector propellant inlet of the engine is communicated with the fuel storage tank through a fuel pipeline, an outlet of the nitrous oxide storage tank is communicated with an injector nitrous oxide inlet of the engine through a gas pipeline, and an inlet of the resonant ignition pipe is also communicated with an outlet of the nitrous oxide storage tank through an ignition pipeline so as to enable the nitrous oxide to generate a resonant heating phenomenon, so that the nitrous oxide is heated to an ignition temperature to ignite the engine; compared with the traditional ignition mode, the invention has the advantages that the ignition temperature is high enough, the structure is simple, third gas is not required to be introduced, the integral quality of the system is reduced, and multiple ignition starting can be realized easily.
Description
Technical Field
The invention belongs to the field of liquid rocket engines, and particularly relates to a liquid rocket engine two-component propulsion system utilizing resonance ignition.
Background
The attitude and orbit control system is an important constituent 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 of satellite propulsion system with long working time and high thrust is the key point for prolonging the on-orbit time of the satellites and increasing the loads of the satellites.
The common propellants of the propulsion system comprise a solid propellant and a liquid propellant, the solid propellant has high safety coefficient, but has low energy content and high fuel filling difficulty, and the thrust is relatively difficult to adjust due to a pre-programmed combustion mode, so that 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 easy to leak in the storage and filling processes, so that the dangers of corrosion, poisoning, burning explosion and the like are caused, and the liquid propellant is especially suitable for hydrazine propellants frequently applied to satellites; another type of propulsion system frequently used on satellites is the cold gas propulsion system, i.e. the propellant is sprayed from the nozzle or directly from the nozzle by heating and catalytic decomposition to obtain thrust, which has the disadvantage of smaller specific impulse. Therefore, finding a propellant which can take advantages of specific impulse, safety, capability of adjusting thrust for multiple times and the like into consideration is a key problem for developing a propulsion system.
Disclosure of Invention
The invention aims to provide a liquid rocket engine two-component propulsion system utilizing resonance ignition, which aims to solve the problems of difficult propellant supply and complicated ignition device of an engine adopting a reversible solidified propellant in the prior art.
The invention adopts the following technical scheme: a two-component propulsion system for a liquid rocket engine utilizing resonant ignition, comprising:
the fuel storage tank is used for storing the reversible solidified propellant, a piston is arranged in the fuel storage tank, a motor is arranged outside an inlet of the fuel storage tank, the motor is used for pushing the piston to move downwards through a coupler so as to extrude the fuel in the fuel storage tank out,
the injector propellant inlet of the engine is communicated with a fuel storage tank through a fuel pipeline,
a nitrous oxide storage tank, wherein the nitrous oxide storage tank is used for storing nitrous oxide, the outlet of the nitrous oxide storage tank is communicated with the nitrous oxide inlet of an injector of an engine through a gas pipeline,
the inlet of the resonance ignition pipe is also communicated with the outlet of the nitrous oxide storage tank through an ignition pipeline and is used for enabling the nitrous oxide to generate a resonance heating phenomenon, so that the nitrous oxide is heated to an ignition temperature and is ignited for the engine;
the resonance ignition tube includes:
a driving nozzle, the upper end of which is communicated with the ignition pipeline, the lower end of which shrinks inwards to form a conical ring,
a resonance tube, the axis of which is coincident with the axis of the driving nozzle,
the axis of the connecting pipe coincides with the axis of the driving nozzle and is of a hollow columnar closed structure, an upper top and a lower bottom of the connecting pipe are respectively provided with an upper through hole and a lower through hole, the upper through hole is used for the lower end of the driving nozzle to extend into, and the lower through hole is used for being communicated with a combustion chamber of an engine through the resonance pipe.
Furthermore, a piston baffle is arranged in the middle of the fuel storage tank, is positioned on 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 the motor so as to press the 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 box, each sliding fixing strip is vertically arranged,
the border of piston baffle is inwards sunken to form the pit, and each pit is used for the slip fixed strip to stretch into, and then makes the piston baffle reciprocate along the slip fixed strip.
Further, a pressure sensor is arranged on the fuel storage tank, and a pressure sensor is arranged on the nitrous oxide storage tank.
Furthermore, a fuel electromagnetic valve, a fuel flow meter 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 flow meter is used for monitoring the flow of the fuel in the fuel pipeline, and the fuel cavitation venturi is used for controlling the flow of the fuel.
Furthermore, a gas electromagnetic valve, a gas flowmeter and a gas cavitation venturi are arranged on the gas pipeline, the gas electromagnetic valve is used for controlling the on-off of the 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.
The invention has the beneficial effects that: compared with the traditional ignition mode, the invention has the advantages that the ignition temperature is high enough, the structure is simple, the third gas is not required to be accessed, the integral quality of the system is reduced, and the multi-time ignition starting can be realized easily; the invention uses the piston to extrude and supply the reversible solidified propellant, compared with the traditional nitrogen extrusion mode, the structure quality is reduced, the volume of a supply system is reduced, the complexity of the system is reduced, and the integration of the storage, the pressurization and the conveying of the propellant and the flow regulation is realized.
Drawings
FIG. 1 is a schematic diagram of the system of the present invention;
fig. 2 is a schematic structural view of the resonant squib of the present invention.
Wherein: 1. a fuel storage tank; 2. a nitrous oxide storage tank; 3. a resonant squib; 4. an injector propellant inlet; 5. an injector nitrous oxide inlet; 6. an ignition conduit; 7. a fuel conduit; 8. a gas conduit; 9. a combustion chamber; 10. a piston; 11. driving the nozzle; 12. a connecting pipe; 13. a resonant tube; 14. a motor; 15. an engine.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
The reversible solidified fuel is a liquid fuel gelled by a gelling agent, energetic particles, a surfactant, an auxiliary agent and the like, is in a solid form with stable surface insensitive during storage, is converted into liquid property during pressurization or shearing, can realize rapid atomization and combustion, has excellent performance, is safe and reliable, and is an excellent choice of fuel in a satellite propulsion system. Nitrous oxide is a normal-temperature propellant capable of being pressurized automatically, is generally extruded by using the high saturated vapor pressure of about 5.2MPa without additionally adding a supply device when being applied, has better energy performance and theoretical specific impulse of about 206s, has the advantages of greenness, safety, higher use temperature and the like, and is an excellent choice of an oxidant in a satellite propulsion system.
Compared with a cold air propulsion system, the nitrous oxide/reversible curing propellant two-component propulsion system has higher thrust and higher energy efficiency, has simpler structure and greener and safer propellant and product compared with the traditional liquid two-component propulsion system, so that the nitrous oxide/reversible curing propellant two-component propulsion system is an excellent choice for a microsatellite attitude and orbit control system.
The existing nitrous oxide double-component propulsion system supplies fuel by nitrogen extrusion, 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 increased by the gas cylinder, the volume of a task unit on a satellite is occupied, and the difficulty of launching and working of the satellite is increased by the additional mass and volume. The vaporized nitrous oxide gas may be used to simultaneously extrude liquid nitrous oxide and fuel in addition to the propellant pressurized with nitrogen, so that a pressurizing device may not be introduced, thereby reducing the weight of the system, but such a system has problems in that the supply system is complicated, and many pipes and control elements are required to achieve both the purpose of extruding fuel and nitrous oxide itself with the vaporized nitrous oxide gas and the purpose of stably controlling the flow rate of the propellant, which undoubtedly increases the difficulty of development of the micro-propulsion system. Therefore, the development of a fuel supply system with simpler structure and smaller volume and mass is one of the key problems facing the development of the nitrous oxide/reversible solidified propellant two-component propulsion system.
Another problem with nitrous oxide/reversibly curable propellant propulsion systems is ignition, and a currently common liquid engine ignition method is ignition by an electric igniter, i.e., the electric igniter is used to directly ignite a main stream of propellant after mixing an oxidizer and fuel, which is poor in applicability to nitrous oxide/reversibly curable propellant engines because the ignition temperature of nitrous oxide and reversibly curable fuel is generally higher than that which can be generated by a conventional electric igniter, which makes it difficult for the electric igniter to directly ignite the main stream of propellant. In a nitrous oxide propulsion system, a common ignition method is catalytic ignition, i.e. nitrous oxide is catalytically decomposed into nitrogen and oxygen, and ignition is performed using oxygen and fuel to ignite a main propellant flow, which requires a catalytic bed and a high-power battery for heating the catalytic bed, which makes the structure of the propulsion system more complex, consumes more energy, and has a longer ignition delay time. The ignition method is not suitable for being used on a satellite because the ignition system is too complex, and how to make the ignition system simpler in structure and higher in ignition efficiency and enable repeated starting for many times is another direction for improving the nitrous oxide propulsion system.
Based on the above, the invention discloses a liquid rocket engine two-component propulsion system using resonance ignition, as shown in fig. 1, comprising a fuel storage tank 1, a nitrous oxide storage tank 2 and a resonance ignition pipe 3.
The fuel storage tank 1 is used for storing the reversible solidified propellant, a piston 10 is arranged in the fuel storage tank 1, a motor 14 is arranged outside an inlet of the fuel storage tank 1, and the motor 14 is used for pushing the piston 10 to move downwards through a coupler so as to extrude the fuel in the fuel storage tank 1.
An injector propellant inlet 4 of the engine 15 is communicated with the fuel storage tank 1 through a fuel pipeline 7, the nitrous oxide storage tank 2 is used for storing nitrous oxide, and an outlet of the nitrous oxide storage tank 2 is communicated with an injector nitrous oxide inlet 5 of the engine 15 through a gas pipeline 8.
The inlet of the resonance ignition pipe 3 is also communicated with the outlet of the nitrous oxide storage tank 2 through an ignition pipeline 6, and the resonance ignition pipe 3 is used for enabling the nitrous oxide to generate a resonance heating phenomenon, so that the nitrous oxide is heated to an ignition temperature and is ignited for the engine 15.
A piston baffle is arranged in the middle of the fuel storage tank 1, is positioned on the lower side of the piston 10, is coaxially arranged with the piston 10 and is fixedly connected with the piston, and is used for moving downwards under the action of a motor 14 so as to press the fuel in the fuel storage tank 1 into an injector propellant inlet 4 of an engine 15; around the even fixedly connected with a plurality of slip fixed strips of fuel storage tank 1's lateral wall a week, the vertical setting of each slip fixed strip, the inside sunken recess that forms in border of piston baffle, each recess is used for the slip fixed strip to stretch into, and then makes piston baffle reciprocate along the slip fixed strip.
The fuel storage tank 1 is provided with a fuel pressure sensor, the fuel pipeline 7 is provided with a fuel electromagnetic valve, a fuel flow meter and a fuel cavitation venturi, the fuel electromagnetic valve is used for controlling the on-off of the pipeline, the fuel flow meter 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 the fuel to be kept at a designed value.
The nitrous oxide storage tank 2 is provided with a gas pressure sensor, the gas pipeline 8 is provided with a gas electromagnetic valve, a gas flowmeter and a gas cavitation venturi, the gas electromagnetic valve is used for controlling the on-off of the 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 designed 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 nitrous oxide gas with small flow enters the resonance ignition pipe 3 to be ignited, and after the temperature is increased, 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, a small amount of nitrous oxide gas is controlled by a gas pressure sensor of a nitrous oxide storage tank 2 to enter a resonant ignition tube 3 through a pressure regulator, the nitrous oxide gas is heated to a preset temperature after a certain time, then the gas pressure sensor changes the requirement, the nitrous oxide passing through the pressure regulator meets a fixed pressure drop to complete oxidant supply, meanwhile, a motor 14 drives a coupler at preset power to drive a piston 10 to extrude fuel at a preset speed, fuel supply is completed, the fuel enters an injector propellant inlet 4, the nitrous oxide enters an injector nitrous oxide inlet 5, and ignition is completed in a 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 storage tank 1, when the preset working pressure is reached, the fuel pressure sensor sends an instruction to open a fuel electromagnetic valve of the fuel pipeline 7, then the fuel flow is accurately adjusted to be a preset value, if the thrust of the engine 15 is to be changed, the fuel pressure sensor needs to send an instruction to the motor 14 to change the power of the motor 14, the flow of the supplied fuel is changed by changing the movement speed of the piston 10, and the thrust of the engine 15 is further changed.
When the engine 15 is in operation, the 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 firstly controls the gas electromagnetic valve to be in an ignition mode, the small-flow nitrous oxide gas enters the resonant 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 to complete nitrous oxide supply.
When the temperature generated by the resonance ignition tube 3 is enough when the engine 15 works, fuel passes through the fuel pipeline 7, and nitrous oxide enters a combustion chamber 9 in the body part of the engine 15 through the gas pipeline 8 for combustion; the reversibly solidified propellant is liquid when entering a fuel pipeline 7, the nitrous oxide is gas when entering a gas pipeline 8, the nitrous oxide enters a combustion chamber 9 through a nitrous oxide inlet 5 of an injector of a gas-liquid coaxial injector, the propellant enters the combustion chamber 9 through an injector propellant inlet 4 of the gas-liquid coaxial injector in a liquid form, and combustion is completed in the combustion chamber 9; the inner surface of the body part of the engine 15 is coated with an ablation-resistant material, and the ablation-resistant material is a silicon carbide material which has good ablation-resistant and oxidation-resistant performance and can prolong the service life of the engine 15.
When the engine 15 works, the air valve of the ignition pipeline 6 is opened, gaseous nitrous oxide enters the resonant ignition pipe 3 to heat the gas by utilizing a resonant heating effect, and the resonant heating effect means that the pneumatic resonance pipe 13 in the air flow generates high-frequency shock wave oscillation under a certain pneumatic condition, so that a heat effect of rapid temperature rise is generated at the tail end of the resonance pipe 13.
As shown in fig. 2, the resonance lighting tube 10 includes a driving nozzle 11, a connecting tube 12, and a resonance tube 13, wherein the upper end of the driving nozzle 11 is connected to the lighting pipe 6, the lower end of the driving nozzle 11 is contracted inward to form a conical ring, the lower end of the driving nozzle 11 extends into the inner cavity of the connecting tube 12, and the length of the driving nozzle 11 extending into the connecting tube 12 is 1/3 of the length of the connecting tube 12.
The connecting pipe 12 is a hollow columnar closed structure, the axis of the connecting pipe 12 is coincident with the axis of the driving nozzle 11, the upper top and the lower bottom of the connecting pipe 12 are respectively provided with an upper through hole and a lower through hole, the upper through hole is used for the lower end of the driving nozzle 11 to extend into, the lower through hole is used for being communicated with a combustion chamber 15 of an engine through the resonance pipe 13, the axis of the resonance pipe 13 is coincident with the axis of the driving nozzle 11, and the diameter of the resonance pipe 13 is the same as the diameter of the lower end of the driving nozzle 11. The gaseous nitrous oxide is heated in a resonant mode for about 5 seconds and then reaches the ignition temperature, nitrous oxide and propellant are supplied at the same time, and the two propellant flows are mixed and atomized and then ignited by the high-temperature nitrous oxide flow; and after ignition is finished, closing the air valve, and if the air valve needs to be started repeatedly after shutdown, repeating the process.
The working process of the invention is as follows: 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 flow of the nitrous oxide to be small, after the preset time, the fuel electromagnetic valve on the fuel pipeline 7 is opened, the gas electromagnetic valve on the gas pipeline 8 enables the flow of the nitrous oxide to be large, the 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 adjust the pressure inside the gas pipeline 8 to be stable dynamically.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalent replacements, improvements, etc. within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A twin-element propulsion system for a liquid rocket engine using resonant ignition, comprising:
a fuel storage tank (1) used for storing reversible solidified propellant and provided with a piston (10) inside, and an electric motor (14) outside the inlet of the fuel storage tank, wherein the electric motor (14) is used for pushing the piston (10) to move downwards through a coupler so as to extrude the fuel in the fuel storage tank (1),
an engine (15) whose injector propellant inlet (4) communicates 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 communicated with the nitrous oxide inlet (5) of an injector of an engine (15) through a gas pipeline (8),
the inlet of the resonance ignition pipe (3) is also communicated with the outlet of the nitrous oxide storage tank (2) through an ignition pipeline (6) and is used for enabling the nitrous oxide to generate a resonance heating phenomenon, so that the nitrous oxide is heated to an ignition temperature and is ignited for the engine (15);
the resonant squib (10) comprises:
a driving nozzle (11), the upper end of which is communicated with the ignition pipeline (6), and the lower end of which is contracted inwards to form a conical ring,
a resonator tube (13) having an axis coinciding with the axis of the drive nozzle (11),
the axial line of the connecting pipe (12) is coincident with the axial line of the driving nozzle (11) and is of a hollow columnar closed structure, an upper top and a lower bottom of the connecting pipe (12) are respectively provided with an upper through hole and a lower through hole, the upper through hole is used for the lower end of the driving nozzle (11) to extend into, and the lower through hole is used for being communicated with a combustion chamber (15) of an engine through the resonance pipe (13).
2. A twin propulsion system for a liquid rocket engine with resonant ignition according to claim 1, wherein the fuel tank (1) is provided with a piston baffle in the middle, which is located at the lower side of the piston (10), is coaxially arranged with the piston (10) and is fixedly connected to the piston, and is used for moving downwards under the action of the motor (14) 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 box (1), each sliding fixing strip is vertically arranged,
the edge of the piston baffle is inwards sunken to form concave grooves, and each concave groove is used for the sliding fixing strip to stretch into, so that the piston baffle can move up and down along the sliding fixing strip.
3. Liquid rocket engine two-component propulsion system with resonant ignition, according to claim 2, characterized in that said fuel tank (1) is provided with a pressure sensor and said nitrous oxide tank (2) is provided with a pressure sensor.
4. A two-component propulsion system of a liquid rocket engine using resonance ignition according to claim 3, characterized in that said fuel pipeline (7) is provided with a fuel solenoid valve, a fuel flow meter and a fuel cavitation venturi, said fuel solenoid valve is used for controlling the on-off of the pipeline, said fuel flow meter is used for monitoring the flow of fuel in the fuel pipeline (7), and said fuel cavitation venturi is used for controlling the fuel flow.
5. A liquid rocket engine two-component propulsion system using resonance ignition according to any one of claims 1-4, characterized in that said gas pipeline (8) is provided with a gas solenoid valve, a gas flow meter and a gas cavitation venturi, said gas solenoid valve is used for controlling the on-off of the pipeline, said gas flow meter is used for monitoring the flow rate of nitrous oxide in the pipeline, said gas cavitation venturi is used for controlling the flow rate 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 CN114776478B (en) | 2023-06-09 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117093023A (en) * | 2023-10-20 | 2023-11-21 | 沈阳航天新光集团有限公司 | Flow control device and method based on venturi and electromagnetic valve duty cycle adjustment |
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 |
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| CN117093023A (en) * | 2023-10-20 | 2023-11-21 | 沈阳航天新光集团有限公司 | Flow control device and method based on venturi and electromagnetic valve duty cycle adjustment |
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| CN114776478B (en) | 2023-06-09 |
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