CN114776482A - Liquid rocket engine propulsion system utilizing resonance ignition - Google Patents
Liquid rocket engine propulsion system utilizing resonance ignition Download PDFInfo
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- CN114776482A CN114776482A CN202210554433.6A CN202210554433A CN114776482A CN 114776482 A CN114776482 A CN 114776482A CN 202210554433 A CN202210554433 A CN 202210554433A CN 114776482 A CN114776482 A CN 114776482A
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- 239000007788 liquid Substances 0.000 title claims abstract description 27
- GQPLMRYTRLFLPF-UHFFFAOYSA-N Nitrous Oxide Chemical compound [O-][N+]#N GQPLMRYTRLFLPF-UHFFFAOYSA-N 0.000 claims abstract description 137
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims abstract description 99
- 239000003350 kerosene Substances 0.000 claims abstract description 74
- 239000001272 nitrous oxide Substances 0.000 claims abstract description 68
- 239000007789 gas Substances 0.000 claims abstract description 48
- 229910052757 nitrogen Inorganic materials 0.000 claims abstract description 46
- 239000000446 fuel Substances 0.000 claims abstract description 43
- 238000001816 cooling Methods 0.000 claims abstract description 33
- 238000002485 combustion reaction Methods 0.000 claims abstract description 19
- 238000010438 heat treatment Methods 0.000 claims abstract description 9
- 229910001873 dinitrogen Inorganic materials 0.000 claims description 7
- 238000012544 monitoring process Methods 0.000 claims description 6
- 238000010304 firing Methods 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 6
- 230000001172 regenerating effect Effects 0.000 description 6
- 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
- 239000000110 cooling liquid Substances 0.000 description 4
- 238000010891 electric arc Methods 0.000 description 4
- 238000002679 ablation Methods 0.000 description 3
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 230000018109 developmental process Effects 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
- 238000003421 catalytic decomposition reaction 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
- 239000007800 oxidant agent Substances 0.000 description 2
- 230000001590 oxidative effect Effects 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 239000003054 catalyst Substances 0.000 description 1
- 235000019994 cava Nutrition 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
- 238000010586 diagram Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000000034 method 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
- 238000010791 quenching Methods 0.000 description 1
- 230000008929 regeneration Effects 0.000 description 1
- 238000011069 regeneration method Methods 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
- 238000004804 winding Methods 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
- F02K9/95—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
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- 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, which comprises: the inlet of the engine is communicated with the outlet of the nitrogen storage tank through a pipeline, the kerosene injector of the engine is communicated with the kerosene storage tank through a fuel pipeline, an inner containing groove, a nitrous oxide storage tank and a cooling jacket are spirally arranged around the outer wall of a combustion chamber of the engine in a circle, the inner containing groove, the nitrous oxide storage tank and the cooling jacket are of a hollow columnar structure, are sleeved on the periphery of the combustion chamber of the engine, and are communicated with the outlet of the nitrogen storage tank through an ignition pipeline, so that the nitrogen is subjected to a resonant heating phenomenon, and is heated to a firing temperature so as to ignite the engine; compared with the traditional ignition mode, the gas resonance igniter is used for ignition, the ignition temperature is high enough, the structure is simple, third gas is not required to be introduced, the overall mass of the system is reduced, and multiple times of ignition starting can be easily realized.
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 is often required to carry out attitude control and adjustment when working in the space, and in order to achieve the purpose, an attitude control engine needs to be carried on the satellite, and a liquid two-component attitude and orbit control engine is an important engine.
The traditional liquid bipropellant attitude and orbit control engine usually uses hydrazine propellant as a power source, however, with the enhancement of environmental awareness of people, toxic hydrazine propellant is no longer suitable to be used as 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); has higher specific impulse when being used as the oxidant of a two-component engine. Based on the advantages, the two-component propulsion system adopting nitrous oxide as the oxidant has the advantages that the traditional propulsion system does not have, such as: no toxicity and pollution, high specific impulse, simple supply system, simple use condition and the like.
The ignition scheme of the nitrous oxide engine commonly used at the present stage generally comprises three ignition modes, namely electric ignition, catalytic decomposition ignition and torch ignition, and the three ignition modes have certain defects. When an electric ignition mode is used, the temperature of an electric arc generated by an electric igniter is low, the electric arc is not enough to directly ignite nitrous oxide and kerosene mixed gas, even if the electric arc is ignited, the electric arc is easy to quench, if a high-energy electric spark plug is used, a set of high-quality electric ignition system and a high-power supply are needed, 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 that nitrous oxide gas is firstly decomposed into nitrogen and oxygen through a catalytic bed, and fuel is ignited by using generated high-temperature mixed gas, so that a main propellant flow is ignited, the catalytic bed needs to be preheated to a certain temperature for normal work, and the catalyst is gradually inactivated after multiple work, so that the catalytic capacity is greatly reduced, therefore, the catalytic ignition mode is not favorable for starting the engine for multiple times, and the ignition delay time is longer; the ignition scheme of the torch usually adopts oxygen and hydrogen as ignition gas, nitrogen is firstly used for extruding the oxygen and hydrogen into the ignition torch during ignition, an electric spark plug is used for ignition, and then generated high-temperature fuel gas is used for igniting nitrous oxide and fuel, so that other gases except propellant need to be introduced in the ignition mode, and the supply system is complicated. Therefore, the development of an igniter which has a 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 means that a pneumatic resonance tube in air flow generates high-frequency shock wave oscillation under a certain pneumatic condition, so that a thermal effect of rapid temperature rise is generated at the tail end of the resonance tube. The pneumatic resonance ignition is a reliable ignition mode for starting for many times, a set of special ignition system is not needed to be added, the problems of electrostatic interference and the like in the traditional ignition mode in a high-altitude environment are avoided, and the method has higher 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 ablation cooling, and the nitrous oxide kerosene engine is low in fuel flow and difficult to cool the engine by applying the traditional regenerative cooling scheme, while the ablation cooling scheme can change the internal configuration of the engine after being used for a long time and is not beneficial to the precise control of thrust, so that the research on the cooling scheme which has a good cooling effect and can meet the requirement of multiple-start long-time work is one of the key problems in the development of the nitrous oxide kerosene two-component propulsion system. Because the latent heat of the nitrous oxide is high and the flow in the nitrous oxide engine is high, the nitrous oxide has high application potential as a regeneration cooling mode of cooling liquid.
Disclosure of Invention
The invention aims to provide a liquid rocket engine propulsion system utilizing resonance ignition to solve the problems that the conventional ignition device is complex in structure and needs additional energy input and the conventional nitrous oxide engine is difficult to protect thermally.
The invention adopts the following technical scheme: a liquid rocket engine propulsion system utilizing resonant ignition, comprising:
a nitrogen storage tank for storing nitrogen therein,
a kerosene storage tank for storing kerosene, the inlet of which is communicated with the outlet of the nitrogen storage tank by a pipeline for ensuring the flow speed of the kerosene under the pressure of nitrogen,
the kerosene injector of the engine 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 therein liquid nitrous oxide,
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 containing groove around the inner wall of the cooling jacket, is outwards provided along the axis of the cooling jacket, corresponds to the inner containing groove and forms an containing channel, the containing channel is used for heating a mobile phase in the containing channel by using the heat of the combustion chamber, one end of the containing channel is communicated with an outlet of a nitrous oxide storage tank through a gas pipeline, and the other end of the containing channel is communicated with a nitrous oxide injector of the engine through a pipeline,
and the inlet of the resonance ignition pipe is also communicated with the outlet of the nitrogen storage tank through an ignition pipeline and is used for enabling the nitrogen to generate a resonance heating phenomenon, so that the nitrogen is heated to the ignition temperature and is ignited for the engine.
Furthermore, a piston baffle is arranged in the middle of the kerosene storage tank and can move downwards under the pressure of nitrogen so as to press the kerosene in the kerosene storage tank into a kerosene injector of the engine;
a plurality of sliding fixing strips are uniformly and fixedly connected around the side wall of the kerosene storage box, each sliding fixing strip is vertically arranged,
the border of piston baffle inwards caves in and forms the pit, and each pit is used for the slip fixed strip to stretch into, and then makes piston baffle reciprocate along the slip fixed strip.
Further, a nitrous oxide pressure sensor is arranged on the nitrous oxide storage tank and used for controlling the flow of nitrous oxide gas.
Furthermore, a nitrogen pressure sensor is arranged on the nitrogen storage tank, and a kerosene pressure sensor is arranged on the kerosene 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.
Further, the resonant 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, the upper top and the lower bottom of the connecting pipe are 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.
The beneficial effects of the invention are: compared with the traditional ignition mode, the gas resonance igniter is used for ignition, the ignition temperature is high enough, the structure is simple, third gas is not required to be accessed, the integral quality of the system is reduced, and multiple ignition starting can be easily realized; compared with a water cooling scheme applied to a ground ignition experiment, the regenerative cooling scheme of the invention which uses liquid nitrous oxide as the cooling liquid has lighter weight and better cooling effect, and can greatly prolong the working time compared with a passive cooling scheme, thereby being more beneficial to being carried on an aircraft.
Drawings
FIG. 1 is a schematic diagram of the system of the present invention;
FIG. 2 is a schematic view of the resonant ignition tube 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 tank; 3. an engine; 4. a fuel conduit; 5. an inner containing slot; 6. a nitrous oxide storage tank; 7. a cooling jacket; 8. an outer accommodating groove; 9. a gas conduit; 10. a resonant squib; 11. driving the nozzle; 12. a connecting pipe; 13. a resonant tube; 14. an ignition conduit; 15. a combustion chamber; 16. accommodating the channel.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
The invention discloses a liquid rocket engine propulsion system utilizing resonance ignition, which comprises a nitrogen storage tank 1, a kerosene storage tank 2, a nitrous oxide storage tank 6, a cooling jacket 7 and a resonance ignition pipe 10, as shown in figure 1.
Nitrogen is stored in the nitrogen storage tank 1, kerosene is stored in the kerosene storage tank 2, an inlet of the kerosene storage tank 2 is communicated with an outlet of the nitrogen storage tank 1 through a pipeline, the kerosene storage tank 2 is used for guaranteeing the flow speed of kerosene under the pressure of the nitrogen, a kerosene injector of the engine 3 is communicated with the kerosene storage tank 2 through a fuel pipeline 4, and a containing groove 5 is spirally formed around the outer wall of a 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 cylindrical structure, the cooling jacket 7 is sleeved on the periphery of a combustion chamber 15 of the engine 3, an outer containing groove 8 is spirally formed around the inner wall of the cooling jacket 7 for one circle, the outer containing groove 8 is formed outwards along the axis of the cooling jacket 7, the outer containing groove 8 and the inner containing groove 5 correspond to each other and form an containing channel 16, the containing channel 16 is used for heating the mobile phase in the containing channel 16 by using the heat of the combustion chamber 15, one end of the containing channel 16 is communicated with an outlet of the nitrous oxide storage tank 6 through a gas pipeline 9, and the other end of the containing channel 16 is communicated with a nitrous oxide injector of the engine 3 through a pipeline.
The inlet of the resonance ignition pipe 10 is also communicated with the outlet of the nitrogen storage tank 1 through an ignition pipeline 14, and the resonance ignition pipe 10 is used for enabling the nitrogen to generate a resonance heating phenomenon, so that the nitrogen is heated to an ignition temperature to ignite the engine 3.
A piston baffle is arranged in the middle of the kerosene storage tank 2 and can move downwards under the pressure of nitrogen so as to press kerosene in the kerosene storage tank 2 into a kerosene injector of the engine 3; winding even fixedly connected with a plurality of slip fixed strips of lateral wall a week of kerosene storage tank 2, each the vertical setting of slip fixed strip, the inside sunken recess that forms in border of piston baffle, each the recess is used for the slip fixed strip to stretch into, and then makes piston baffle reciprocate along the slip fixed 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 is required to be in an ignition mode, the small-flow nitrous oxide gas enters the resonant ignition tube 10 to be ignited, and after the temperature is increased, the nitrous oxide pressure sensor controls the flow adjusting device to be in a supply mode, so that nitrous oxide supply is completed.
Be provided with nitrogen gas pressure sensor on the nitrogen gas storage tank 1, be provided with kerosene pressure sensor on the kerosene storage tank 2. The fuel pipeline 4 is provided with a fuel electromagnetic valve, a fuel flow meter and a fuel cavitation venturi, wherein the electromagnetic valve is used for controlling the on-off of a pipeline, the fuel flow meter 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 the 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 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 preset value.
The conventional engine adopts fuel as regenerative cooling liquid in a regenerative cooling mode, and the nitrous oxide engine has high fuel temperature and low fuel flow, so the mode of utilizing the fuel as the regenerative cooling liquid is not suitable for the nitrous oxide engine; because the latent heat of the nitrous oxide is high enough, the property is stable, the heat protection effect is good, and the nitrous oxide engine can replace a passive cooling mode which is commonly used in a nitrous oxide engine 3.
The invention adopts liquid nitrous oxide to absorb heat through a cooling jacket 7 outside an engine 3, the liquid nitrous oxide is changed into gaseous state after heat absorption, then the gaseous nitrous oxide is used for supplying, when the engine 3 is started, the nitrogen extrudes kerosene for supplying, meanwhile, the nitrous oxide is supplied through self-pressurization and then ignited, the nitrogen enters a resonance ignition pipe 10 for resonance to reach the ignition temperature and ignite the kerosene, when the nitrous oxide is supplied, the nitrogen firstly enters a gas pipeline 9 in liquid state, slowly evaporates in the gas pipeline 9, enters an accommodating channel 16 of the cooling jacket 7 in a gas-liquid two-phase flow state, absorbs heat in the cooling jacket 7 and completely evaporates, and the gaseous nitrous oxide enters an nitrous injector of the engine 3 to complete the supply of the engine 3.
When the engine 3 works, nitrogen enters the kerosene storage tank 2 through the pipeline to pressurize the kerosene, when the engine 3 works, the kerosene with higher flow is needed, the kerosene cannot flow naturally only, and the kerosene is extruded by higher pressure, so that the nitrogen is introduced for pressurizing; 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 work of the engine 3; the gas flow meter on the gas pipe 9 controls the flow rate of nitrogen gas, and when the gas pressure sensor detects a change, the nitrogen gas flow area is increased to prevent the nitrogen gas flow rate from decreasing.
When the engine 3 works, the kerosene is extruded by nitrogen and enters the engine 3 through the fuel pipeline 4; the kerosene pressure sensor on the kerosene storage tank 2 detects the pressure in the kerosene storage tank 2, kerosene in the kerosene storage tank 2 can be gradually consumed along with the work of the engine 3, the occupied space can be reduced, further the pressure in the kerosene storage tank 2 is reduced, the kerosene flow is reduced, and when the kerosene pressure sensor detects that the internal pressure in the kerosene storage tank 2 is reduced, the flow of nitrogen is controlled, 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 the specific expression is that when the engine 3 works, liquid kerosene enters the kerosene injector at a preset flow rate, meanwhile gaseous nitrous oxide enters the nitrous oxide injector at a preset flow rate, the kerosene injector atomizes the kerosene and sprays the kerosene into the combustion chamber 15, a mixed flow of atomized kerosene droplets and gaseous nitrous oxide is ignited by high-temperature nitrogen and then is combusted in the combustion chamber 15, and an oxidation-resistant material needs to be coated outside the combustion chamber 15; 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 an ignition tube 14, 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, 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 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. Nitrogen gas is used as driving gas to enter the driving nozzle 11 for acceleration, then shock waves are generated in the resonance tube 13 to heat the gas, and after about 5 seconds, the gas temperature reaches the ignition temperature of nitrous oxide and kerosene.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and should not be taken as limiting the scope of the present invention, which is intended to cover any modifications, equivalents, improvements, etc. within the spirit and scope of the present invention.
Claims (7)
1. A liquid rocket engine propulsion system utilizing resonant ignition, comprising:
a nitrogen storage tank (1) in which nitrogen is stored,
a kerosene tank (2) for storing kerosene, the inlet of which communicates with the outlet of the nitrogen tank (1) via a pipe for ensuring the flow rate of kerosene under the pressure of nitrogen,
a kerosene injector of the engine (3) is communicated with the kerosene storage box (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 in a circle,
a nitrous oxide tank (6) for storing therein liquid nitrous oxide,
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 containing groove (8) around the inner wall of the cooling jacket (7) for one circle, the outer containing groove (8) is outwardly provided along the axis of the cooling jacket (7), the outer containing groove (8) and the inner containing groove (5) correspond to each other and form an containing channel (16), the containing channel (16) is used for heating a mobile phase in the containing channel (16) by using the heat of the combustion chamber (15), one end of the containing channel (16) is communicated with an outlet of the nitrous oxide storage tank (6) through a gas pipeline (9), and the other end of the containing channel is communicated with a nitrous oxide injector of the engine (3) through a pipeline,
and the inlet of the resonance ignition pipe (10) is also communicated with the outlet of the nitrogen storage tank (1) through an ignition pipeline (14) and is used for enabling the nitrogen to generate a resonance heating phenomenon, so that the nitrogen is heated to an ignition temperature and is ignited for the engine (3).
2. A liquid rocket engine propulsion system using resonance ignition according to claim 1, characterized in that the middle of said kerosene storage tank (2) is provided with a piston baffle which can move downwards under the pressure of nitrogen gas to press the kerosene in the kerosene storage tank (2) 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 box (2), 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. A liquid rocket engine propulsion system using resonance ignition according to claim 2, characterized in that said nitrous oxide tank (6) is provided with a nitrous oxide pressure sensor for controlling the flow of nitrous oxide gas.
4. A liquid rocket engine propulsion system using resonance ignition according to claim 3, characterized in that said nitrogen tank (1) is provided with a nitrogen pressure sensor and said kerosene tank (2) is provided with a kerosene pressure sensor.
5. A liquid rocket engine propulsion system using resonance ignition according to any one of claims 1 to 4, wherein said fuel pipeline (4) 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 (4), said fuel cavitation venturi is used for controlling the fuel flow.
6. The liquid rocket engine propulsion system using resonance ignition according to claim 5, characterized in that a gas solenoid valve, a gas flow meter and a gas cavitation venturi are arranged on the gas pipeline (9), the gas solenoid valve is used for controlling the on-off of the pipeline, the gas flow meter is used for monitoring the flow rate of nitrous oxide in the pipeline, and the gas cavitation venturi is used for controlling the flow rate of nitrous oxide.
7. A liquid rocket engine propulsion system using resonant ignition according to claim 6, characterized in that said resonant squib (10) comprises:
a driving nozzle (11), the upper end of which is communicated with the ignition pipeline (14), 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 axis of the connecting pipe (12) coincides with the axis of the driving nozzle (11) and 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 into the connecting pipe, and the lower through hole is used for being communicated with a combustion chamber (15) of the engine through the resonance pipe (13).
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 |
|---|---|
| CN114776482A true CN114776482A (en) | 2022-07-22 |
| CN114776482B CN114776482B (en) | 2023-08-11 |
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