CN114810427A - High-energy green liquid propeller ignition device and method for exciting plasma by microwave - Google Patents
High-energy green liquid propeller ignition device and method for exciting plasma by microwave Download PDFInfo
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- CN114810427A CN114810427A CN202210345653.8A CN202210345653A CN114810427A CN 114810427 A CN114810427 A CN 114810427A CN 202210345653 A CN202210345653 A CN 202210345653A CN 114810427 A CN114810427 A CN 114810427A
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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
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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
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Abstract
A high-energy green liquid thruster ignition device and method for microwave excitation of plasma belong to the technical field of space propulsion. The invention adopts a mode of microwave excitation plasma, generates microwave with specific frequency in a resonant cavity by using a microwave power supply module to jet propellant entering the thruster, excites carrier gas to generate plasma, and realizes ignition of high-energy green liquid propellant through high-temperature plasma. The method does not need a catalyst, has the advantages of high ignition energy, reliable ignition, stable combustion, high combustion rate, high thermal efficiency and the like, and can greatly prolong the service life of the liquid thruster.
Description
Technical Field
The invention relates to an ignition device and method for a liquid thruster, and belongs to the technical field of space propulsion.
Background
The "green propellant" developed in recent years mainly includes: azide-based, hydroxylamine nitrate (HAN) -based, Ammonium Dinitramide (ADN), and nitrazidine-based liquid monopropellants. The ADN-based liquid propellant (mainly composed of ADN, alcohols and water) has the advantages of high processing safety, high specific impact, high storage density and the like, and is one of the ideal green propellants at present. The ADN-based and HAN-based liquid propellant is a novel high-performance, green, nontoxic and storable propellant, and represents a brand new research direction and development trend of space chemistry propulsion technology.
ADN-based and HAN-based liquid engines applied to satellites at present adopt a preheating catalysis mode to realize ignition of liquid propellant. The working process of the liquid engine is divided into the following stages: 1) preheating a catalytic bed; 2) spraying a propellant; 3) catalytic decomposition of the propellant; 4) high temperature combustion of the fuel in the combustion chamber; 5) the high-temperature and high-pressure fuel gas is sprayed out to generate thrust. The catalytic decomposition characteristic of the propellant not only determines the ignition starting performance of the engine, but also generates important performance on fuel combustion and the thrust characteristic of the engine.
The current ground test of ADN base and HAN base liquid engines finds that: the ignition of the propellant achieved by the catalytic mode has the problem that the ignition characteristic is significantly influenced by the performance of the catalyst and the preheating temperature. ECAPS corporation found by ground ignition testing on ADN-based liquid thrusters: ignition delay tends to increase as the preheat temperature decreases from greater than 300 c to 200 c. Below 200 c, ignition can still succeed, but the engine ignition delay is further increased to 0.6 s. Test results show that the catalyst performance and the preheating temperature have obvious influence on the ignition characteristics; the engine may suffer from difficulties in starting up at low temperatures, sintering of the catalytic particles (resulting in reduced catalyst activity and blockage of the catalytic bed), significant fluctuations in combustion pressure, etc.
In summary, many basic researches and experimental tests find that factors such as the structure of the catalyst bed, the performance of the catalyst, and the preheating temperature of the catalyst bed have important influence on the decomposition process of the ADN-based and HAN-based liquid propellants. The preheating catalysis mode needs to make large-area contact between ADN-based and HAN-based liquid propellants and catalytic particles to improve the catalytic reaction performance, but causes the catalytic particles to directly bear the action of surrounding high-temperature and high-pressure fuel gas.
At the present stage, both ADN-based engines and HAN-based engines are realized by adopting a catalytic combustion method, high-temperature fuel gas is in direct contact with a catalyst, the temperature in a combustion chamber of the high-energy formula engine can reach more than 1600 ℃, and the catalyst can not stably work under the temperature condition for a long time, so that the problems of reduction of the service life, sintering of the catalyst and the like exist, and the unstable work of the engine is caused. Therefore, the high-energy green liquid engine ignition method for exciting the plasma by microwaves is provided, and the direct ignition of the liquid propellant is realized.
The plasma ignition combustion of liquid drops is realized by exciting ion ionization and ADN and HAN thermal decomposition reaction in the propellant through microwave irradiation of ADN-based and HAN-based liquid propellant spray fields.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the high-energy green liquid thrusting agent comprises ADN/HAN base liquid propellant, and solves the problems of difficult low-temperature starting of an engine, ablation and activity reduction of catalytic particles, incapability of igniting a high-energy catalyst for multiple times and short service life.
The technical scheme of the invention is as follows: an energetic green liquid thruster ignition device for microwave excitation of plasma, comprising: the device comprises an upper computer, a microwave power supply, a magnetron, a circulator, an automatic tuner, a flowmeter, an air storage tank, a flow rate meter, a propellant supply device, a double-channel filling device, a cooling water discharge device, a cooling water storage tank, a load, a rack, a resonant cavity, a tungsten needle and a tungsten needle control device;
the microwave power supply is connected with the upper computer through a transmission line, and the power and the output time transmitted by the microwave power supply are controlled by the upper computer; the microwave power supply supplies power to the magnetron, the circulator and the automatic tuner, and provides power output for the magnetron; microwave energy generated by a magnetron is firstly sent to an input port I of a three-port circulator, then a signal is directionally transmitted to an output port II of the circulator, power sent from the magnetron is transmitted to an automatic tuner, reflected power from a microwave power supply is sent to a load for consumption, and the load is used for protecting the microwave power supply and the magnetron; the gas storage tank and the propellant supply device are respectively used for storing working substance gas and propellant, and are respectively connected with the double-channel filling device through hoses with the outer diameter of 12 mm; the flow meters are arranged at the outlets of the cooling water supply device and the gas storage tank, the flow rate meter is arranged at the outlet of the propellant supply device, the input quantities of the working medium gas and the cooling water are respectively controlled by the flow meters, and the input quantity of the propellant is controlled by the flow rate meter; the double-channel filling device is fixed on the rack, and the working medium gas and the propellant are filled into the resonant cavity through the double-channel filling device; the cooling water discharge device and the cooling water supply device form a cooling system for supplying cooling water to the microwave power supply, the magnetron, the circulator, the automatic tuner and the resonant cavity.
The microwave power supply monitors the working temperature of the magnetron and the change of the power output parameter in real time.
The propellant supply unit stores ADN-based or HAN-based liquid propellant.
The double-channel filling device respectively fills the working medium gas and the propellant through double channels, a propellant supply fluid channel and a carrier gas fluid channel of the double-channel filling device are coaxially arranged, lateral channels are symmetrically arranged on two sides of the carrier gas fluid channel, the working medium gas and the propellant introduced into the lateral channels are introduced into the resonant combustion chamber at the same time, the working medium gas is uniformly distributed in the resonant cavity through the channels on the two sides of the double-channel filling device, the liquid propellant is introduced into the propellant supply fluid channel in the middle, and the upper rack plays a fixing role and is tightly combined with the resonant cavity.
The tungsten needle and the tungsten needle control device are arranged inside the resonant cavity; the microwave resonates in the resonant cavity and ionizes the working medium gas, so that a microwave plasma torch is formed and the propellant is ignited.
The ignition method of the high-energy green liquid propeller for exciting the plasma by the microwave comprises the following steps of:
step 1: the cooling water supply device is turned on.
Step 2: and when the cooling water circularly flows out of the device, a microwave power switch is turned on, and the microwave power is controlled by using an upper computer, wherein the microwave power switch comprises the settings of parameters such as input power, pulse, maximum voltage, minimum voltage and the like.
And step 3: the flow output of the gas storage tank is controlled by a flowmeter, and nitrogen is introduced into the resonant cavity until stable airflow exists above the resonant cavity.
And 4, step 4: and opening a switch of the tungsten needle control device, moving the tungsten needle up to the center of the resonant cavity, and closing the tungsten needle control device when discharge and flare occur in the center of the resonant cavity.
And 5: and opening a switch of the propellant supply device, adjusting the flow range to be 25ml/min to 45ml/min, and when yellow-green jet flame above the resonant cavity is observed, successfully igniting.
Step 6: the switch controlling the gas tank and the propellant supply device is closed.
And 7: and turning off the microwave power supply and the upper computer.
And 8: the cooling water supply device switch is turned off.
Compared with the prior art, the invention has the beneficial effects that:
(1) according to the invention, catalyst particles are not required to be filled, so that the problems of difficulty in low-temperature starting of the engine, ablation of the catalytic particles, reduction of activity and the like commonly existing in a high-energy green liquid engine adopting a preheating catalysis mode are solved.
(2) The invention can ignite liquid drops which accord with the ignition condition in the microwave irradiation range, realizes space multipoint ignition, and improves the starting ignition reliability and response speed.
(3) The invention can control parameters such as microwave power, frequency, spraying and the like, and can increase the flexibility of ignition control.
(4) The invention can inject microwave energy into the high-energy green propellant through the plasma transformation of the carrier gas, and can improve the specific impulse of the thruster.
(5) The invention can realize the free movement of the tungsten needle in the resonant cavity, not only can avoid the interference of the tungsten needle to the combustion process of the propellant in the resonant cavity, but also can realize the reutilization of the probe.
Drawings
FIG. 1 is a block diagram of the present invention;
FIG. 2 is a schematic diagram of an internal arrangement of a resonant cavity according to the present invention;
fig. 3 is a schematic view of a dual-channel filling device according to the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the embodiments of the present invention will be described in detail with reference to the accompanying drawings.
The working principle of the device can be described as follows: a resonance is generated in the resonant cavity by microwaves of a specific frequency (2.45GHz), and the rectangular waveguide transmits the microwaves to the resonant cavity. Working medium gas (such as helium, nitrogen and the like) flowing through the resonant cavity absorbs microwave electromagnetic energy, and then excitation, dissociation and ionization are carried out to generate a large amount of microwave plasma, and a plasma torch is formed to ignite fuel. When the electromagnetic radiation interacts with the plasma in a specific microwave frequency band (e.g., 2.45GHz, 3GHz), the plasma is not coupled with the electromagnetic radiation as a single electron as in the case of the plasma generated by other methods, but rather as a dielectric medium to couple with the electromagnetic energy. The process of microwave plasma generation is the process of breakdown of a working medium, electrons in gas accelerate due to absorption of electromagnetic energy and generate energy loss and exchange processes with nearby gas molecules in an inelastic collision mode, the gas molecules further undergo excitation, dissociation and ionization processes to generate a large amount of free electrons and ions, and at the moment, an external electromagnetic field is influenced, and plasma ionization parameters are changed. The number of electrons can be reduced gradually by diffusion, attachment or self-absorption effects, and when the new number of electrons is equal to or greater than the lost number, the working medium gas can be punctured. Because the magnetic field in the resonant cavity generates Lorentz force on the moving electrons, the electrons obtain certain energy, and the high-energy electrons ionize the surrounding gas to form plasma.
As shown in fig. 1 to 3, in the present embodiment, the ignition device of the present invention includes an upper computer 1, a microwave power supply 2, a magnetron 3, a circulator 4, an auto tuner 5, a flow meter 6, a gas tank 7, a flow rate meter 8, an ADN-based propellant supply device 9, a two-way filling device 10, a cooling water discharge system 11, a cooling water supply device 12, a load 13, a stage 14, a resonant cavity 15, a tungsten needle 16, and a tungsten needle control device 17.
An upper computer 1: and the control of basic parameters including output power, maximum output efficiency, output time and the like is responsible.
And (3) a microwave power supply 2: 1) supplying power energy to the magnetron 3; 2) and monitoring the change of parameters such as the working temperature, the power output and the like of the magnetron in real time.
Magnetron 3: the magnetron 3 is an electric vacuum device for generating microwave energy. Essentially a diode placed in a constant magnetic field. Under the control of the constant magnetic field and the constant electric field which are vertical to each other, electrons in the tube interact with the high-frequency electromagnetic field to convert energy obtained from the constant electric field into microwave energy, thereby achieving the purpose of generating the microwave energy.
The circulator 4: the circulator 4 is a multiport device in which microwaves can only travel in one direction, being isolated in the opposite direction. The invention uses a three-port circulator which is used for connecting a cooling water circulation system, microwave is generated by a microwave source and then is input from a port I, output from a port II, and the port III absorbs the microwave reflected by a load end, thereby protecting a microwave generation system.
Automatic tuner 5: the auto-tuner is used to match the impedance of the circuit to maximize the power transferred to the resonator.
The gas tank 7: for storing any one of nitrogen/helium/argon/air.
Propellant supply device 9: is responsible for storing ADN propellants or HAN-based liquid propellants.
Double-channel filling device 10: a filling device is provided, the design of double channels enables working medium gas and ADN-based propellant to be filled respectively, and the uniform distribution of the working medium gas and the matching of the working medium gas and the ADN-based propellant are ensured.
Cooling water discharge system 11 and cooling water supply device 12: the cooling water supply and discharge of the whole device are carried out, so that the device is cooled in operation.
And (3) loading 13: the impedance matching of the circulator 4 works to protect the circulator 4.
The stage 14: the double-channel filling device is fixed.
Resonant cavity 15: the cavity 15 comprises a cavity, a tungsten pin 16 and a fixture 17. In the device, microwave generates resonance, working medium gas is ionized to form a microwave plasma torch, and the ADN-based propellant is ignited.
A tungsten needle 16: a probe having high conductivity is capable of breaking down an electric field to form a plasma.
Tungsten needle control device 17: the push-pull electromagnet for fixing the tungsten needle can realize the up-and-down movement of the tungsten needle by using a switch.
The microwave power supply 2 is connected with the upper computer 1 through a transmission line, and the power and the output time transmitted by the microwave power supply 2 are controlled through the upper computer 1; the microwave power supply 2 supplies power to the magnetron 3, the circulator 4 and the automatic tuner 5, and the microwave power supply 2 provides power output for the magnetron 3; microwave energy generated by a magnetron 3 is firstly sent to an input port I of a three-port circulator 4, then a signal is directionally transmitted to an output port II of the circulator 4, power sent from the magnetron 3 is transferred to an automatic tuner 5, reflected power from a microwave power supply is sent to a load 13 to be consumed, and the load 13 plays a role of protecting the microwave power supply 2 and the magnetron 3; the gas storage tank 7 and the propellant supply device 9 are respectively used for storing working substance gas and propellant, and the gas storage tank 7 and the propellant supply device 9 are respectively connected with the double-channel filling device 10 through hoses with the outer diameter of 12 mm; the flowmeter 6 is arranged at the outlets of the cooling water supply device 12 and the gas storage tank 7, the flow meter 8 is arranged at the outlet of the propellant supply device 9, the input quantities of the working medium gas and the cooling water are respectively controlled through the flowmeter 6, and the input quantity of the propellant is controlled through the flow meter 8; the double-channel filling device 10 is fixed on the rack 14, and working medium gas and propellant are filled into the resonant cavity 15 through the double-channel filling device 10; the cooling water discharge device 11 and the cooling water supply device 12 constitute a cooling system for supplying cooling water to the microwave power supply 2, the magnetron 3, the circulator 4, the automatic tuner 5, and the resonant cavity 15.
The microwave power supply 2 monitors the working temperature of the magnetron 3 and the change of the power output parameter in real time.
The propellant supplier 9 stores ADN-based or HAN-based liquid propellant.
The double-channel filling device 10 respectively fills the working medium gas and the propellant through double channels, a propellant supply fluid channel and a carrier gas fluid channel of the double-channel filling device 10 are coaxially arranged, lateral channels 101 are symmetrically arranged on two sides of the carrier gas fluid channel, the working medium gas and the propellant introduced into the lateral channels 101 are introduced into the resonant combustion chamber at the same time, the working medium gas is uniformly distributed in the resonant cavity 15 through the channels on two sides of the double-channel filling device 10, the liquid propellant is introduced into the propellant supply fluid channel 102 in the middle, and the rack 14 on the upper side plays a role in fixing and is tightly combined with the resonant cavity 15.
The tungsten needle 16 and the tungsten needle control device 17 are arranged inside the resonant cavity 15; the microwaves resonate in the resonant cavity 15 and ionize the working gas, thereby forming a microwave plasma torch, igniting the propellant.
The ignition method of the high-energy green liquid propeller for exciting the plasma by the microwave comprises the following steps of:
step 1: the cooling water supply device 12 is turned on.
Step 2: and when the cooling water circularly flows out in the device, a switch of the microwave power supply 2 is turned on, and the microwave power supply 2 is controlled by using the upper computer 1, wherein the setting of parameters such as input power, pulse, maximum voltage, minimum voltage and the like is included.
And step 3: the flow output of the gas storage tank 7 is controlled by the flow meter 6, and nitrogen is introduced into the resonant cavity 15 until stable gas flow exists above the resonant cavity 15.
And 4, step 4: and opening a switch of the tungsten needle control device 17, moving the tungsten needle up to the center of the resonant cavity 15, and closing the tungsten needle control device 17 when discharge and fire light occur in the center of the resonant cavity 15.
And 5: the propellant supply device 9 is switched on, the flow rate is adjusted to be between 25ml/min and 45ml/min, and when yellow-green jet flame above the resonant cavity 15 is observed, the ignition is successful.
Step 6: the switches controlling the gas tank 7 and the propellant feed 9 are closed.
And 7: and turning off the microwave power supply 2 and the upper computer 1.
And 8: the cooling water supply device 12 is turned off.
A unique coupling device is designed, namely the tungsten needle can move freely. When the magnetron 3 is started, the tungsten needle 16 is arranged in the middle of the resonant cavity, namely the place with the highest electromagnetic energy calculated by theory; and when the ignition is finished and the plasma flame is stable, the switch is controlled to realize that the tungsten needle moves to the lower side of the combustion chamber. The design aim is to avoid the problems that the tungsten needle is positioned in the resonant combustion chamber and is burnt by plasma flame for a long time to generate deformation abrasion and the like.
Microwave energy, which is the microwave energy that is delivered to maximize the output of power, leaving the autotuner 5 enters the cavity 15. The microwave continues to propagate until it is reflected at the trailing end and a standing wave is created within the cavity 15. A coupling device is specially designed at the joint of a resonant cavity 15 and a double-channel filling device 14, the coupling device mainly comprises a tungsten needle 16 and a tungsten needle control device 17, and a resultant electric field at the tip of the plasma torch can be amplified and breakdown is triggered.
In order to sustain the generation of the microwave discharge, the microwave needs to be turned on all the time, thereby efficiently transferring energy to the plasma. Therefore, flow rate meters and flowmeters require the adjustment of monopropellants and working fluid gases over a wide range of flow rates to observe optimum operating conditions.
When the microwave reaches the plasma moment, a flow meter 6 for controlling the working medium gas is opened (nitrogen is released from a nitrogen tank 7), the working medium gas finally generates plasma flame through the series of ionization processes, then single-component propellant is introduced through a propellant supply device 9 according to a certain flow rate of 25-45 ml/min (controlled by a flow rate meter 8), the propellant can be ignited by the plasma flame generated by the working medium gas, and the test of microwave ignition in the space engine is proved to be feasible. In the subsequent experiment, the flow meter 6 is continuously controlled to close the working medium gas channel, and whether the high-energy green single-component propellant can be successfully ignited under the condition of no combustion supporting of the working medium gas is observed.
In addition, when the microwave power exceeds 500W, the temperature of the devices such as the microwave power supply 2 and the magnetron 3 is too high, and an additional cooling mode is required to protect the whole device from being overheated and to normally operate, so that a cooling system is added, and the cooling system consists of a cooling water supply system and a cooling water discharge system. The cooling supply system is implemented by the following parts: cooling water starts from a single water pump and flows through the microwave power supply 2, the magnetron 3, the resonant cavity 15 and other devices; and finally, cooling water flows out from a cooling water discharging device 11 at the tail end of the resonant cavity device, so that the purpose of timely cooling is realized. The main reason for adding helium is that the high-energy green liquid propellant is difficult to directly ignite, in order to realize successful ignition of the high-energy green monopropellant propellant, the combustion supporting effect of inert gases such as helium is needed, and since the plasma flame generated by helium can reach thousands of degrees, the ignition point of the high-energy green propellant is easily reached, helium is selected as the combustion supporting gas.
The invention designs a set of drainage cooling system. Aiming at the condition that a microwave power supply, a magnetron, a waveguide component and the like are overheated in the microwave excitation plasma combustion process, the real-time water supply of a cooling water supply device is utilized to provide water cooling for all devices to achieve the purpose of cooling. A microwave power supply is used as a water inlet, and the microwave power supply sequentially passes through a magnetron, a waveguide tube and a resonant cavity, and the middle of the microwave power supply is connected with a specially designed cooling water pipeline. And finally flows out from a water outlet at the tail end of the resonant cavity.
The feed microwave frequency should match the resonant cavity 15 frequency: according to the expression of resonant frequency f of resonant cavity
Obtaining integral structural parameters of the resonant cavity by using the microwave frequency (2.45GHz) and determining the radius or the length of the resonant cavity;
wherein μ and ∈ are magnetic conductivity and electric conductivity of a gas medium in the resonant cavity 15, R is a cavity radius of the resonant cavity 15, and l is a cavity height of the resonant cavity 15.
The following description is given of a typical microwave ignition embodiment:
as shown in fig. 1, after the entire apparatus is connected, the cooling apparatus is started to check whether the apparatus can operate normally. Introducing helium gas to manufacture the gas condition required by the microwave ignition device. And controlling a microwave power supply through the upper computer, adjusting the input power to 800W, and detecting the microwave occurrence condition.
And after the microwave is stabilized at the frequency of 2.45GHz, observing the generation condition of the microwave plasma torch in the resonant cavity. The degree of reaction of the input power with the helium gas delivery flow regulating device can be varied. After a stable plasma torch appears, introducing ADN-based propellant at the speed of 25ml/min, observing the reaction condition, and gradually adjusting the input flow of the propellant after successful ignition to achieve the purpose of stable combustion.
In order to perfectly match helium with the high-energy green propellant, a brand-new filling device is designed, as shown in fig. 2, the whole filling device consists of a left pipeline, a right pipeline and a middle double channel respectively, and is fixed on a rack 14. Helium is introduced into the left side and the right side of the gas-liquid separator, so that the helium is uniformly distributed in the outer channel, and the high-energy green liquid propellant is introduced into the middle inner channel. The stand is tightly combined with the resonant cavity while fixing the filling device. When helium is introduced, microwave breakdown of helium generates plasma flame, the plasma flame is mainly distributed in the outer channel, then high-energy green propellant is introduced, and the peripheral helium plasma flame ignites the high-energy green propellant to achieve the purpose of supporting combustion. The filling method has the advantages that helium and the high-energy green propellant can be isolated, and the feasibility that the high-energy green single-component propellant can be successfully ignited or not under the condition of no helium combustion supporting can be observed in subsequent experiments, namely the high-energy green propellant is directly ionized.
Those skilled in the art will appreciate that the details of the invention not described in detail in the specification are within the skill of those skilled in the art.
Claims (10)
1. An ignition device of a high-energy green liquid propeller for exciting plasmas, which is characterized by comprising: the device comprises an upper computer (1), a microwave power supply (2), a magnetron (3), a circulator (4), an automatic tuner (5), a flowmeter (6), an air storage tank (7), a flow rate meter (8), a propellant supply device (9), a dual-channel filling device (10) and a resonant cavity (15);
the microwave power supply (2) is connected with the upper computer (1) through a transmission line, and the power and the output time transmitted by the microwave power supply (2) are controlled through the upper computer (1); the microwave power supply (2) supplies power to the magnetron (3), the circulator (4) and the automatic tuner (5), and the microwave power supply (2) provides power output for the magnetron (3);
microwave energy generated by the magnetron (3) is firstly transmitted to an input port I of a three-port circulator (4), then a signal is directionally transmitted to an output port II of the circulator (4), and the circulator (4) transfers power transmitted from the magnetron (3) to an automatic tuner (5);
the gas storage tank (7) and the propellant supply device (9) respectively store working substance gas and propellant, and the gas storage tank (7) and the propellant supply device (9) are respectively connected with the double-channel filling device (10) through hoses;
the flow meter (6) is arranged at the outlets of the cooling water supply device (12) and the gas storage tank (7), the flow meter (8) is arranged at the outlet of the propellant supply device (9), the input quantities of the working medium gas and the cooling water are respectively controlled through the flow meter (6), and the input quantity of the propellant is controlled through the flow meter (8);
working medium gas and propellant are filled into the resonant cavity (15) through the double-channel filling device (10).
2. A microwave-excited plasma high-energy green liquid thruster ignition device as claimed in claim 1, characterized in that the microwave power supply (2) monitors the operating temperature of the magnetron (3) in real time, the variation of power output parameters.
3. A microwave-excited plasma high-energy green liquid propellant ignition device as claimed in claim 1, characterised in that the propellant feed (9) stores ADN-based or HAN-based liquid propellants.
4. The high-energy green liquid propeller ignition device of the microwave-excited plasma as claimed in claim 1, wherein the dual-channel filling device (10) respectively fills the working medium gas and the propellant through dual channels, a propellant supply fluid channel and a carrier gas fluid channel of the dual-channel filling device (10) are coaxially arranged, lateral channels (101) are symmetrically arranged on two sides of the carrier gas fluid channel, the working medium gas and the propellant introduced into the lateral channels (101) are introduced into the resonant combustion chamber simultaneously, the working medium gas is uniformly distributed in the resonant cavity (15) through the channels on two sides of the dual-channel filling device (10), and the liquid propellant is introduced into the propellant supply fluid channel (102) in the middle.
5. The high-energy green liquid propeller ignition device for microwave excitation plasma according to claim 1, characterized by further comprising a tungsten needle (16), a tungsten needle control device (17); the tungsten needle (16) and the tungsten needle control device (17) are arranged inside the resonant cavity (15); the microwave generates resonance in the resonant cavity (15) and ionizes working medium gas, so that a microwave plasma torch is formed and the propellant is ignited;
when the magnetron (3) is started, the tungsten needle (16) is arranged in the middle of the resonant cavity, namely the place with the highest electromagnetic energy obtained through theoretical calculation; and when the ignition is finished and the plasma flame is stabilized, the tungsten needle control device (17) realizes that the tungsten needle (16) moves to the lower side of the resonant cavity (15).
6. The high-energy green liquid thruster ignition device for microwave-excited plasma as claimed in claim 5, wherein: feeding microwave frequency responseFrequency matching with the resonant cavity (15): according to the expression of resonant frequency f of resonant cavity
Obtaining the integral structural parameters of the resonant cavity by utilizing the microwave frequency and the radius or the length of the resonant cavity (15);
wherein mu and epsilon are the magnetic conductivity and the electric conductivity of a gas medium in the resonant cavity (15), R is the inner radius of the resonant cavity (15), and l is the height of the resonant cavity (15).
7. The high-energy green liquid thruster ignition device for microwave-excited plasma as claimed in claim 1, wherein: also comprises a cooling water discharge device (11) and a cooling water storage tank (12);
the cooling water discharging device (11) and the cooling water supplying device (12) form a cooling system for supplying cooling water to the microwave power supply (2), the magnetron (3), the circulator (4), the automatic tuner (5) and the resonant cavity (15).
8. The high-energy green liquid thruster ignition device for microwave excitation plasma as claimed in claim 1, wherein: also comprises a bench (14); the double-channel filling device (10) is fixed on the rack (14).
9. The high-energy green liquid thruster ignition device for microwave-excited plasma as claimed in claim 1, wherein: further comprising a load (13); a load (13) is connected to the circulator (4), the reflected power from the microwave power supply (2) is fed to the load (13) for consumption, and the load (13) is used for protecting the microwave power supply (2) and the magnetron (3).
10. The ignition method of the high-energy green liquid propeller ignition device for microwave excitation plasma according to any one of claims 1 to 9, characterized by comprising the following steps:
turning on a cooling water supply device (12) switch;
when cooling water circularly flows out of the ignition device, a switch of the microwave power supply (2) is turned on, and the microwave power supply (2) is controlled by using the upper computer (1), wherein the setting of parameters of input power, pulse, maximum voltage and minimum voltage is included;
controlling the flow output of the gas storage tank (7) by using a flowmeter (6), and introducing inert gas into the resonant cavity (15) until stable gas flow exists above the resonant cavity (15);
opening a switch of the tungsten needle control device (17), controlling the tungsten needle (16) to move upwards to the center of the resonant cavity (15), and closing the tungsten needle control device (17) when discharge and fire light occur in the center of the resonant cavity (15);
opening a switch of a propellant supply device (9), adjusting the flow range to be 25ml/min to 45ml/min, and when yellow-green jet flow flame is observed above the resonant cavity (15), successfully igniting;
closing a switch for controlling the air storage tank (7) and the propellant supply device (9);
turning off the microwave power supply (2) and the upper computer (1);
the cooling water supply device (12) is turned off.
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