CN114776482B - Liquid rocket engine propulsion system utilizing resonance ignition - Google Patents
Liquid rocket engine propulsion system utilizing resonance ignition Download PDFInfo
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- CN114776482B CN114776482B CN202210554433.6A CN202210554433A CN114776482B CN 114776482 B CN114776482 B CN 114776482B CN 202210554433 A CN202210554433 A CN 202210554433A CN 114776482 B CN114776482 B CN 114776482B
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- kerosene
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- nitrous oxide
- pipeline
- nitrogen
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- 239000007788 liquid Substances 0.000 title claims abstract description 28
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims abstract description 93
- 239000007789 gas Substances 0.000 claims abstract description 51
- 229910052757 nitrogen Inorganic materials 0.000 claims abstract description 42
- 238000001816 cooling Methods 0.000 claims abstract description 33
- GQPLMRYTRLFLPF-UHFFFAOYSA-N Nitrous Oxide Chemical compound [O-][N+]#N GQPLMRYTRLFLPF-UHFFFAOYSA-N 0.000 claims description 142
- 239000001272 nitrous oxide Substances 0.000 claims description 71
- 239000003350 kerosene Substances 0.000 claims description 69
- 239000000446 fuel Substances 0.000 claims description 41
- 238000002485 combustion reaction Methods 0.000 claims description 18
- 238000010438 heat treatment Methods 0.000 claims description 8
- 238000012544 monitoring process Methods 0.000 claims description 6
- 239000010742 number 1 fuel oil Substances 0.000 claims description 3
- 230000001276 controlling effect Effects 0.000 description 10
- 229910001873 dinitrogen Inorganic materials 0.000 description 9
- 230000000694 effects Effects 0.000 description 6
- 239000000110 cooling liquid Substances 0.000 description 5
- 239000003380 propellant Substances 0.000 description 5
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 description 4
- 230000003197 catalytic effect Effects 0.000 description 4
- 230000001172 regenerating effect Effects 0.000 description 4
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 3
- 239000007800 oxidant agent Substances 0.000 description 3
- 239000001301 oxygen Substances 0.000 description 3
- 229910052760 oxygen Inorganic materials 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 239000003054 catalyst Substances 0.000 description 2
- 238000003421 catalytic decomposition reaction Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000010892 electric spark Methods 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 231100000956 nontoxicity Toxicity 0.000 description 2
- 230000001590 oxidative effect Effects 0.000 description 2
- 230000008929 regeneration Effects 0.000 description 2
- 238000011069 regeneration method Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 230000004308 accommodation Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010891 electric arc Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 239000002737 fuel gas Substances 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
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 229920006395 saturated elastomer Polymers 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
- 231100000331 toxic Toxicity 0.000 description 1
- 230000002588 toxic effect Effects 0.000 description 1
- 230000005514 two-phase flow Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 230000010356 wave oscillation Effects 0.000 description 1
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
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
-
- 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
-
- 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
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
The invention discloses a liquid rocket engine propulsion system utilizing resonance ignition, comprising: the inlet of the cooling jacket is communicated with the outlet of the nitrogen storage tank through an ignition pipeline, so that the nitrogen is heated to an ignition temperature, and the engine is ignited; compared with the traditional ignition mode, the gas resonance igniter is high in ignition temperature, simple in structure, free of third gas, capable of reducing the overall quality of the system and capable of easily achieving multiple ignition and starting.
Description
Technical Field
The invention belongs to the field of liquid rocket engines, and particularly relates to a liquid rocket engine propulsion system utilizing resonance ignition.
Background
The satellite often needs to be subjected to attitude control and adjustment when working in the space, and an attitude control engine is required to be carried on the satellite to achieve the purpose, and the liquid double-component attitude control engine is an important engine.
The traditional liquid double-component attitude and orbit control engine usually uses hydrazine propellant as a power source, however, along with the enhancement of environmental awareness of people, toxic hydrazine propellant is not suitable for being used as a propellant, so nitrous oxide enters the sight of researchers. Nitrous oxide has the following advantages: no toxicity and no corrosion; good stability at normal temperature and high saturated vapor pressure (about 5 MPa); the catalyst has higher specific impulse when being used as an oxidant of a two-component engine. Based on the above advantages, a two-component propulsion system employing nitrous oxide as an oxidizer has advantages not possessed by conventional propulsion systems, such as: no toxicity, no pollution, high specific flushing, simple supply system, simple use condition, etc.
The conventional nitrous oxide engine ignition scheme generally has three ignition modes, namely electric ignition, catalytic decomposition ignition and torch ignition, and the three ignition modes have certain defects. When the electric ignition mode is used, the electric arc temperature generated by the electric igniter is low, so that the mixed gas of nitrous oxide and kerosene is not sufficiently ignited directly, even if spark is ignited, the mixed gas is easily quenched, and if a high-energy electric spark plug is used, a set of high-quality electric ignition system and a high-power supply are needed, so that the space and the energy of a satellite are occupied, and the reliability of the satellite is greatly influenced; the catalytic decomposition ignition is generally to decompose nitrous oxide gas into nitrogen and oxygen through a catalytic bed, and ignite fuel by using the generated high-temperature mixed gas, so as to ignite a main flow of the propellant, wherein the catalytic bed needs to be preheated to a certain temperature to perform normal work, and the catalyst is gradually deactivated after multiple works, so that the catalytic capability is greatly reduced, the catalytic ignition mode is unfavorable for multiple starting of an engine, and the ignition delay time is longer; in the torch ignition scheme, gas, oxygen and hydrogen are usually adopted as ignition gas, nitrogen is firstly utilized to extrude the gas, oxygen and hydrogen into an ignition torch during ignition, an electric spark plug is used for ignition, and generated high-temperature fuel gas is utilized to ignite nitrous oxide and fuel, so that other gases except propellant are required to be introduced in the ignition mode, and a supply system is complicated. Therefore, the igniter which has simpler structure, higher ignition efficiency and can be started repeatedly is one of the key problems faced by the development of the nitrous oxide kerosene two-component propulsion system.
The pneumatic resonance ignition is an ignition mode based on a gas resonance heating effect, and the resonance heating effect is a thermal effect that a pneumatic resonance tube in 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. The pneumatic resonance ignition is a reliable multiple-start ignition mode, a special ignition system is not required to be added, the problems of electrostatic interference and the like in a high-altitude environment of the traditional ignition mode are avoided, and the pneumatic resonance ignition system has high application value for a low-thrust nitrous oxide engine with difficult ignition.
The traditional liquid rocket engine cooling mode mainly comprises two modes of regenerative cooling and ablative cooling, and because the fuel flow in the nitrous oxide kerosene engine is smaller, the engine is difficult to be cooled by adopting the traditional regenerative cooling scheme, and the ablative cooling scheme can change the internal configuration of the engine after long-time use, so that the accurate control of thrust is not facilitated, and therefore, the cooling scheme with good research cooling effect and capability of meeting the requirement of multiple-start long-time work is one of the key problems faced by the development of the nitrous oxide kerosene dual-component propulsion system. The nitrous oxide has high latent heat and high flow in the nitrous oxide engine, so that the nitrous oxide has high application potential in a regenerative cooling mode of taking the nitrous oxide as cooling liquid.
Disclosure of Invention
The invention aims to provide a liquid rocket engine propulsion system utilizing resonance ignition, which aims to solve the problems that a conventional ignition device is complex in structure, requires additional energy input and is difficult to thermally protect a conventional nitrous oxide engine.
The invention adopts the following technical scheme: a liquid rocket engine propulsion system utilizing resonant ignition, comprising:
a nitrogen storage tank in which nitrogen is stored,
a kerosene storage tank for storing kerosene therein, an inlet of which is communicated with an outlet of the nitrogen storage tank through a pipe for ensuring a flow rate of kerosene under a pressure of nitrogen,
the engine, the kerosene injector is communicated with the kerosene storage tank through a fuel pipeline, an inner containing groove is spirally arranged around the outer wall of the combustion chamber,
a nitrous oxide storage tank for storing liquid nitrous oxide therein,
the cooling jacket is of a hollow columnar structure, is sleeved on the periphery of a combustion chamber of the engine, is spirally provided with an outer accommodating groove around the inner wall of the cooling jacket, is outwards provided along the axis of the cooling jacket, corresponds to the inner accommodating groove and forms an accommodating channel, the accommodating channel is used for heating the mobile phase in the accommodating channel by utilizing the heat of the combustion chamber, one end of the accommodating channel is communicated with an outlet of a nitrous oxide storage tank through a gas pipeline, the other end of the accommodating channel is communicated with a nitrous oxide injector of the engine through a pipeline,
the inlet of the resonance ignition tube is also communicated with the outlet of the nitrogen storage tank through an ignition pipeline and is used for leading nitrogen to generate resonance heating phenomenon, thereby leading the nitrogen to be heated to the ignition temperature and igniting the engine.
Further, a piston baffle is arranged in the middle of the kerosene storage tank, and the piston baffle can move downwards under the pressure of nitrogen, so that the kerosene in the kerosene storage tank is pressed into a kerosene injector of the engine;
a plurality of sliding fixing strips are uniformly and fixedly connected around the periphery of the side wall of the kerosene 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 nitrous oxide pressure sensor is arranged on the nitrous oxide storage tank, and the nitrous oxide pressure sensor is used for controlling the flow rate of nitrous oxide gas.
Further, a nitrogen pressure sensor is arranged on the nitrogen storage tank, and a coal oil pressure sensor is arranged on the kerosene 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.
Further, the resonance squib 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 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.
The beneficial effects of the invention are as follows: compared with the traditional ignition mode, the gas resonance igniter is high enough in ignition temperature, simple in structure, free of third gas, capable of reducing the overall quality of the system and capable of easily realizing multiple ignition and starting; according to the invention, the liquid nitrous oxide is used as a regenerative cooling scheme of the cooling liquid, so that the liquid nitrous oxide has lighter mass and better cooling effect compared with a water cooling scheme applied to a ground ignition experiment, and the working time can be greatly prolonged compared with a passive cooling scheme, thereby being more beneficial to being carried on an aircraft.
Drawings
FIG. 1 is a schematic diagram of a system of the present invention;
FIG. 2 is a schematic diagram of the structure of the resonant squib of the present invention;
FIG. 3 is a cross-sectional view of a cooling jacket of the present invention;
fig. 4 is a side view of the cooling jacket of the present invention.
Wherein: 1. a nitrogen storage tank; 2. a kerosene storage tank; 3. an engine; 4. a fuel pipe; 5. an inner accommodation groove; 6. nitrous oxide storage tanks; 7. a cooling jacket; 8. an outer accommodating groove; 9. a gas conduit; 10. a resonance ignition tube; 11. driving the nozzle; 12. a connecting pipe; 13. a resonance tube; 14. an ignition tube; 15. a combustion chamber; 16. the receiving channel.
Detailed Description
The invention will be described in detail below with reference to the drawings and the detailed description.
The invention discloses a liquid rocket engine propulsion system utilizing resonance ignition, which is shown in fig. 1 and comprises a nitrogen gas storage tank 1, a kerosene storage tank 2, a nitrous oxide storage tank 6, a cooling jacket 7 and a resonance ignition tube 10.
The nitrogen gas is stored in the nitrogen gas storage tank 1, the kerosene is stored in the kerosene storage tank 2, the inlet of the kerosene storage tank 2 is communicated with the outlet of the nitrogen gas storage tank 1 through a pipeline, the kerosene storage tank 2 is used for guaranteeing the flow rate of kerosene under the pressure of nitrogen gas, the kerosene injector of the engine 3 is communicated with the kerosene storage tank 2 through a fuel pipeline 4, and an inner accommodating groove 5 is spirally formed around the outer wall of the combustion chamber 15 of the engine 3.
As shown in fig. 3 and 4, the nitrous oxide storage tank 6 is used for storing liquid nitrous oxide, the cooling jacket 7 is of a hollow columnar structure, the cooling jacket 7 is sleeved on the periphery of the combustion chamber 15 of the engine 3, an outer accommodating groove 8 is spirally formed around the inner wall of the cooling jacket 7, the outer accommodating groove 8 is outwards formed along the axis of the cooling jacket 7, the outer accommodating groove 8 and the inner accommodating groove 5 correspond to each other, an accommodating channel 16 is formed, the accommodating channel 16 is used for heating the mobile phase in the accommodating channel 16 by utilizing the heat of the combustion chamber 15, one end of the accommodating channel 16 is communicated with the outlet of the nitrous oxide storage tank 6 through a gas pipeline 9, and the other end of the accommodating channel 16 is communicated with the nitrous oxide injector of the engine 3 through a pipeline.
The inlet of the resonance ignition tube 10 is also communicated with the outlet of the nitrogen gas storage tank 1 through an ignition pipeline 14, and the resonance ignition tube 10 is used for enabling nitrogen gas to generate resonance heating phenomenon, so that the nitrogen gas is heated to an ignition temperature, and the engine 3 is ignited.
The middle part of the kerosene storage tank 2 is provided with a piston baffle which can move downwards under the pressure of nitrogen, so that the kerosene in the kerosene storage tank 2 is pressed into a kerosene injector of the engine 3; a plurality of sliding fixing strips are uniformly and fixedly connected around the periphery of the side wall of the kerosene storage tank 2, 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 nitrous oxide storage tank 6 is provided with a nitrous oxide pressure sensor, the nitrous oxide pressure sensor is used for controlling the flow of nitrous oxide gas, when the nitrous oxide gas with small flow is required to be in an ignition mode, the nitrous oxide gas enters the resonance ignition tube 10 for ignition, and after the temperature rises, the nitrous oxide pressure sensor controls the flow regulating device to be in a supply mode, so that nitrous oxide supply is completed.
A nitrogen pressure sensor is arranged on the nitrogen storage tank 1, and a coal oil pressure sensor is arranged on the kerosene storage tank 2. The fuel pipeline 4 is provided with a fuel electromagnetic valve, a fuel flowmeter and a fuel cavitation venturi, wherein the 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 4, and the fuel cavitation venturi is used for controlling the flow of fuel to be kept at a preset value.
The gas pipeline 9 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 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 preset value.
The conventional engine adopts a fuel as a regeneration cooling liquid, and the nitrous oxide engine has high combustion temperature and low fuel flow, so the mode of using the fuel as the regeneration cooling liquid is not suitable for the nitrous oxide engine, and the nitrous oxide engine is cooled in a passive cooling mode in general, and the invention uses liquid nitrous oxide, namely an oxidant, as the cooling liquid for cooling; because the nitrous oxide latent heat is high enough, the property is stable, the heat protection effect is good, and the nitrous oxide engine 3 can be replaced by a passive cooling mode commonly used.
The invention adopts liquid nitrous oxide to absorb heat through a cooling sleeve 7 outside an engine 3, the liquid nitrous oxide becomes a gaseous state after absorbing heat, then gaseous nitrous oxide is used for supplying, nitrogen extrudes kerosene for supplying when the engine 3 is started, nitrous oxide is supplied through self-pressurization and then is ignited, nitrogen enters a resonance ignition tube 10 to resonate, the temperature of ignition is reached and kerosene is ignited, when the nitrous oxide is supplied, the liquid nitrous oxide firstly enters a gas pipeline 9 and slowly evaporates in the gas pipeline 9, and enters a containing channel 16 of the cooling sleeve 7 in a gas-liquid two-phase flow state, absorbs heat in the cooling sleeve 7 and completely evaporates, and the nitrous oxide injector with the gaseous state entering the engine 3 completes the supply of the engine 3.
When the engine 3 works, nitrogen enters the kerosene storage tank 2 through a pipeline to boost the pressure of the kerosene, and when the engine 3 works, the kerosene with higher flow is required, and cannot be realized only by natural flow of the kerosene, and the kerosene is extruded by higher pressure, so that the nitrogen is introduced to boost the pressure; the nitrogen pressure sensor on the nitrogen storage tank 1 detects the pressure change in the nitrogen storage tank 1, so that the kerosene flow is prevented from changing when the pressure in the nitrogen storage tank 1 is reduced along with the operation of the engine 3; the gas flow meter on the gas pipe 9 controls the flow rate of nitrogen, and when the gas pressure sensor detects a change, the nitrogen flow area is increased to prevent the nitrogen flow rate from decreasing.
When the engine 3 works, kerosene is extruded by nitrogen and enters the engine 3 through a fuel pipeline 4; the pressure in the kerosene storage tank 2 is detected by the kerosene pressure sensor on the kerosene storage tank 2, kerosene in the kerosene storage tank 2 is gradually consumed along with the operation of the engine 3, the occupied space is reduced, the pressure in the kerosene storage tank 2 is further reduced, the kerosene flow is reduced, and the nitrogen flow is controlled when the pressure in the kerosene storage tank 2 is detected by the kerosene pressure sensor to be reduced, so that the pressure in the kerosene storage tank 2 is kept stable; the fuel flow meter precisely controls the kerosene flow to a preset value, so that the engine 3 stably works.
The main body of the engine 3 mainly comprises a kerosene injector, a nitrous oxide injector, a combustion chamber 15 and a spray pipe, and is characterized in that when the engine 3 works, liquid kerosene enters the kerosene injector at a preset flow, gaseous nitrous oxide enters the nitrous oxide injector at a preset flow at the same time, the kerosene injector atomizes the kerosene and sprays the kerosene into the combustion chamber 15, the mixed flow of atomized kerosene droplets and gaseous nitrous oxide is combusted in the combustion chamber 15 after being ignited by high-temperature nitrogen, and the outside of the combustion chamber 15 is required to be coated with oxidation resistant materials; the material of the spray pipe is ablation-resistant silicon carbide.
As shown in fig. 2, the resonance ignition 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 communicated with the ignition tube 14, 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 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 hollow columnar airtight 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 extending in the lower end of the driving nozzle 11, the lower through hole is used for communicating with a combustion chamber 15 of an engine through a resonance tube 13, the axis of the resonance tube 13 coincides with the axis of the driving nozzle 11, and the diameter of the resonance tube 13 is the same as the diameter of the lower end of the driving nozzle 11. The nitrogen gas enters the driving nozzle 11 as a driving gas to accelerate, then shock waves are generated in the resonance tube 13 to heat the gas, and the temperature of the gas reaches the ignition temperature of nitrous oxide and kerosene after about 5 seconds.
The foregoing description of the preferred embodiments of the invention is not intended to limit the invention to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and scope of the invention are intended to be included within the scope of the invention.
Claims (6)
1. A liquid rocket engine propulsion system utilizing resonant ignition, comprising:
a nitrogen storage tank (1) in which nitrogen is stored,
a kerosene storage tank (2) for storing kerosene, an inlet of which is communicated with an outlet of the nitrogen storage tank (1) through a pipeline and is used for ensuring the flow rate of the kerosene under the pressure of nitrogen,
an engine (3) with a kerosene injector communicated with a kerosene storage tank (2) through a fuel pipeline (4), an inner containing groove (5) is spirally arranged around the outer wall of a combustion chamber (15) of the engine,
a nitrous oxide tank (6) for storing liquid nitrous oxide therein,
the cooling jacket (7) is of a hollow columnar structure, is sleeved on the periphery of a combustion chamber (15) of the engine (3), is spirally provided with an outer accommodating groove (8) around the periphery of the inner wall of the cooling jacket (7), the outer accommodating groove (8) is outwards provided along the axis of the cooling jacket (7), the outer accommodating groove (8) and the inner accommodating groove (5) correspond to each other and form an accommodating channel (16), the accommodating channel (16) is used for heating the mobile phase in the accommodating channel (16) by utilizing the heat of the combustion chamber (15), one end of the accommodating channel (16) is communicated with the outlet of the nitrous oxide storage tank (6) through a gas pipeline (9), the other end of the accommodating channel is communicated with the nitrous oxide injector of the engine (3) through a pipeline,
the inlet of the resonance ignition tube (10) is also communicated with the outlet of the nitrogen storage tank (1) through an ignition pipeline (14) and is used for leading nitrogen to generate resonance heating phenomenon, so that the nitrogen is heated to an ignition temperature and the engine (3) is ignited;
the resonance squib (10) comprises:
a driving nozzle (11) with the upper end communicated with the ignition pipeline (14) 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 axis of the connecting pipe (12) is coincident with the axis of the driving nozzle (11), 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 (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 (15) of an engine through a resonance tube (13).
2. A liquid rocket engine propulsion system using resonance ignition according to claim 1, characterized in that the middle part of the kerosene storage tank (2) is provided with a piston baffle which can move downwards under the pressure of nitrogen, so that the kerosene in the kerosene storage tank (2) is pressed into the kerosene injector of the engine (3);
a plurality of sliding fixing strips are uniformly and fixedly connected around the periphery of the side wall of the kerosene storage tank (2), 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 propulsion system using resonance ignition according to claim 2, wherein nitrous oxide pressure sensors are provided on the nitrous oxide tank (6) for controlling the flow of nitrous oxide gas.
4. A liquid rocket engine propulsion system using resonance ignition according to claim 3, wherein the nitrogen tank (1) is provided with a nitrogen pressure sensor, and the kerosene tank (2) is provided with a coal oil pressure sensor.
5. A liquid rocket engine propulsion system using resonance ignition according to any one of claims 1-4, wherein the fuel pipeline (4) 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 (4), and the fuel cavitation venturi is used for controlling the flow of fuel.
6. A liquid rocket engine propulsion system using resonance ignition according to claim 5, wherein the gas pipeline (9) 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 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210554433.6A CN114776482B (en) | 2022-05-20 | 2022-05-20 | Liquid rocket engine propulsion system utilizing resonance ignition |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210554433.6A CN114776482B (en) | 2022-05-20 | 2022-05-20 | Liquid rocket engine propulsion system utilizing resonance ignition |
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| Publication Number | Publication Date |
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| CN114776482A CN114776482A (en) | 2022-07-22 |
| CN114776482B true CN114776482B (en) | 2023-08-11 |
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| CN202210554433.6A Active CN114776482B (en) | 2022-05-20 | 2022-05-20 | Liquid rocket engine propulsion system utilizing resonance ignition |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5109669A (en) * | 1989-09-28 | 1992-05-05 | Rockwell International Corporation | Passive self-contained auto ignition system |
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| CN103644044A (en) * | 2013-11-26 | 2014-03-19 | 北京航空航天大学 | Multi-component simulative engine applied to vacuum plume effect experimental research and ignition scheme thereof |
| CN111173647A (en) * | 2020-03-26 | 2020-05-19 | 北京宇航推进科技有限公司 | Two-component nitrous oxide engine |
| CN112177801A (en) * | 2020-08-31 | 2021-01-05 | 西北工业大学 | Hydrogen peroxide/kerosene rocket engine thrust chamber based on third fluid |
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2022
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| US5109669A (en) * | 1989-09-28 | 1992-05-05 | Rockwell International Corporation | Passive self-contained auto ignition 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 |
| CN101699053A (en) * | 2009-10-26 | 2010-04-28 | 北京航空航天大学 | Oxygen-complementing type air-hydrogen/air-oxygen pneumatic resonance heat surface igniter |
| CN103644044A (en) * | 2013-11-26 | 2014-03-19 | 北京航空航天大学 | Multi-component simulative engine applied to vacuum plume effect experimental research and ignition scheme thereof |
| CN111173647A (en) * | 2020-03-26 | 2020-05-19 | 北京宇航推进科技有限公司 | Two-component nitrous oxide engine |
| CN112177801A (en) * | 2020-08-31 | 2021-01-05 | 西北工业大学 | Hydrogen peroxide/kerosene rocket engine thrust chamber based on third fluid |
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| CN114776482A (en) | 2022-07-22 |
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