CN112196692A - Electrode combustible thrust continuously adjustable riches fires automatically controlled solid ramjet - Google Patents
Electrode combustible thrust continuously adjustable riches fires automatically controlled solid ramjet Download PDFInfo
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- CN112196692A CN112196692A CN202011094433.XA CN202011094433A CN112196692A CN 112196692 A CN112196692 A CN 112196692A CN 202011094433 A CN202011094433 A CN 202011094433A CN 112196692 A CN112196692 A CN 112196692A
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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
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/18—Composite ram-jet/rocket engines
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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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
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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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
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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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Abstract
The invention discloses a fuel-rich electronic control solid ramjet engine with continuously adjustable electrode combustible thrust, which comprises a power supply system, a fuel gas generator, an air inlet channel, a afterburning chamber and a tail nozzle, wherein the fuel gas generator is connected with the air inlet channel; the fuel gas generator comprises a fuel gas generator shell, a conductive assembly and a fuel gas generator spray pipe, wherein a propellant accommodating cavity capable of accommodating the rich-fuel electric control solid propellant is arranged in the fuel gas generator shell; the conductive assembly comprises a conductive anode, a conductive cathode, a circuit connected with a power supply system, the conductive anode, the rich-combustion electric-control solid propellant and the conductive cathode; and part or all of at least one of the conductive positive electrode and the conductive negative electrode is a combustible electrode. The concept of the electrode combustible fuel-rich electric control solid propellant is applied to the solid ramjet, which is beneficial to solving the problem of great difficulty in the thrust regulation technology of the traditional solid ramjet; compared with the existing electronic control solid engine, the electrode combustible fuel can effectively improve the filling ratio of the engine, effectively reduce the short circuit risk in the propellant combustion process and enhance the controllability of the engine.
Description
Technical Field
The invention relates to the technical field of solid rocket ramjet engines, in particular to a fuel-rich electronic control solid ramjet engine with continuously adjustable electrode combustible thrust.
Background
The solid rocket engine is a missile weapon due to the advantages of simple structure, convenient use, low cost, high reliability and the like, and is widely applied to various missiles, various tactical and strategic missile power systems. The solid rocket ramjet combines the solid rocket engine and the ramjet, utilizes air as an oxidant and solid propellant as fuel, can realize the powered flight of the missile in the whole process, and greatly improves the maneuverability, the range and the rapid penetration capability of the missile. Solid ramjet engines typically employ a regulated flow to control engine thrust. The conventional flow regulation mode of the solid ramjet engine is usually mechanical regulation, the thrust regulation range is narrow, and an actuating part such as a sliding disc valve, a pneumatic needle valve and the like is required. Although the adjusting method is partially applied to actual engineering, the problems of high technical difficulty, low reliability and the like still exist, and the high working performance of the engine in the whole missile flight process cannot be guaranteed.
At present, the research on engines using electrically controlled solid propellant as fuel mainly aims at solid rocket engines, and no published report about solid ramjet engines is found. At present, an electric control solid rocket engine usually adopts a multi-electrode arrangement mode, and the electrode configuration can effectively improve the combustion efficiency of the propellant. However, the multi-electrode configuration increases the structural volumetric mass of the engine, reduces charge-volume fill ratio, and reduces the operating time of the engine. In addition, the multi-electrode configuration increases the risk that the ionic flame generated during propellant combustion is conducted in an electric field environment to cause short circuits, which may cause the engine to fail to operate properly. Meanwhile, in the traditional high-energy propellant of the solid ramjet engine, due to the high content of boron powder or metal powder in the pharmaceutical process, the viscosity of the slurry is too high, the flowability is poor, and the dispersion effect of the solid powder is poor, so that bubbles, cracks and the like are generated in the casting process, and even the casting cannot be performed.
Disclosure of Invention
Aiming at the defects and the requirement background of the prior art, the invention provides the fuel-rich electric control solid ramjet with the electrode combustible thrust continuously adjustable, which combines the latest current situation that the current electric control solid propellant can be continuously adjusted in order to develop a power device of the solid ramjet, firstly applies the concept of the electrode combustible fuel-rich electric control solid propellant to the solid ramjet, and is beneficial to solving the problem of great difficulty in the thrust adjustment technology of the traditional solid ramjet; compared with the existing electronic control solid engine, the electrode combustible fuel can effectively improve the filling ratio of the engine, effectively reduce the short circuit risk in the propellant combustion process and enhance the controllability of the engine.
In order to achieve the aim, the invention provides a fuel-rich electronic control solid ramjet with continuously adjustable electrode combustible thrust, which comprises a power supply system, a fuel gas generator, an air inlet channel, a afterburning chamber and a tail nozzle, wherein the air inlet channel, the afterburning chamber and the tail nozzle are sequentially connected;
the fuel gas generator comprises a fuel gas generator shell and a conductive assembly, a propellant containing cavity capable of containing the rich-fuel electric control solid propellant is arranged in the fuel gas generator shell, a fuel gas generator spray pipe which faces the afterburning chamber and is communicated with the propellant containing cavity is further arranged on the fuel gas generator shell, wherein the fuel gas generator is arranged inside the aircraft, the outlet position of the fuel gas generator spray pipe is later in the outlet of the air inlet channel, namely the outlet of the air inlet channel is communicated with the inlet of the afterburning chamber, and the outlet of the fuel gas generator spray pipe is positioned inside the afterburning chamber and close to the outlet of the air.
The conductive assembly comprises a conductive anode and a conductive cathode, the rich-combustion electric control solid propellant is arranged between the conductive anode and the conductive cathode, and the conductive assembly further comprises a circuit connected with a power supply system, the conductive anode, the rich-combustion electric control solid propellant and the conductive cathode;
and part or all of at least one of the conductive positive electrode and the conductive negative electrode is a combustible electrode.
In one embodiment, the gasifier shell is of a cylindrical configuration, the propellant-receiving chamber is a cylindrical chamber, and the gasifier nozzle is disposed at an aft end of the gasifier shell along an axial direction of the gasifier shell; the combustible electrode is embedded and connected in the fuel-rich electric control solid propellant and comprises an isolation part and an exposed part;
the isolation part comprises a combustible insulating layer for isolating the rich-combustion electric control solid propellant from the side edge of the combustible electrode and preventing the rich-combustion electric control solid propellant from being integrally conducted; the exposed part is positioned at the position of the fuel-rich electric control solid propellant and close to the gas generator spray pipe so as to realize the first ignition of the fuel-rich electric control solid propellant.
In one embodiment, the flammable insulation layer is made of a high-temperature-resistant polymer material, such as one or a mixture of two of polyvinyl chloride, polyvinyl alcohol, phenolic resin, and teflon. The thickness of the combustible insulating layer is between 0.9mm and 0.2 mm. The combustible electrode close to the nozzle end of the gas generator is reserved with 0.1 mm-0.5 mm of non-coated insulating layer as a bare part for realizing the first ignition of the propellant.
In one embodiment, the gas generator further comprises a propellant containing chamber housing, the propellant containing chamber being located within the propellant containing chamber housing, and an insulating layer of heat insulation is provided between the gas generator housing and the propellant containing chamber housing.
In one embodiment, one of the conductive positive electrode and the conductive negative electrode is a combustible electrode; one part of the other one of the conductive positive electrode and the conductive negative electrode is a combustible electrode, and the other part of the other one of the conductive positive electrode and the conductive negative electrode is a propellant containing cavity shell.
In one embodiment, the conductive assembly further comprises a conductive disc, an insulator and a cylindrical base fixedly disposed within the gas generator housing, the cylindrical base and the propellant receiving chamber housing together defining a propellant receiving chamber, the insulator being disposed between the conductive disc and the cylindrical base;
the conductive positive electrode comprises a plurality of positive electrode combustible electrode rods, and the conductive negative electrode comprises a propellant containing cavity shell and a plurality of negative electrode combustible electrode rods; the cylindrical base is provided with first through holes distributed in an annular layered manner; one end of the positive combustible electrode rod is embedded and connected to the single-layer first through hole on the cylindrical base, and the other end of the positive combustible electrode rod is positioned in the fuel-rich electric control solid propellant; the conductive disc is provided with a plurality of second through holes corresponding to the first through holes of the double layers on the cylindrical base, one end of the negative combustible electrode bar is embedded and connected onto the second through holes, the other end of the negative combustible electrode bar penetrates through the insulating piece and the first through holes of the double layers on the cylindrical base and then is positioned in the fuel-rich electric control solid propellant, and the conductive disc and the cylindrical base are both connected onto a circuit; or
The conductive cathode comprises a plurality of cathode combustible electrode rods, and the conductive anode comprises a propellant containing cavity shell and a plurality of anode combustible electrode rods; the cylindrical base is provided with a plurality of first through holes distributed in an annular layered manner; one end of the negative electrode combustible electrode bar is embedded and connected to the single-layer first through hole on the cylindrical base, and the other end of the negative electrode combustible electrode bar is positioned in the fuel-rich electric control solid propellant; be equipped with a plurality of second through-holes that correspond with the first through-hole of double-deck on the cylinder base on the electrically conductive disc, the one end embedding of anodal combustible electrode stick is connected on the second through-hole, and the other end passes and lies in after the first through-hole of double-deck on insulating part, the cylinder base and richly fires inside the automatically controlled solid propellant, electrically conductive disc, cylinder base all connect on the circuit.
In one embodiment, one of the conductive positive electrode and the conductive negative electrode is a combustible electrode, and the other is a propellant containing cavity shell.
In one embodiment, the electrically conductive assembly further comprises an insulator and a fastener fixedly disposed within the gas generator housing, the fastener and the propellant containing chamber housing together defining a propellant containing chamber;
the conductive positive electrode comprises a plurality of positive electrode combustible electrode rods, and the conductive negative electrode is a propellant containing cavity shell; the fixing piece is provided with a plurality of first through holes distributed in a ring-shaped layered manner; one end of the positive electrode combustible electrode bar is embedded and connected to the first through hole, the other end of the positive electrode combustible electrode bar is positioned in the fuel-rich electric control solid propellant, the insulating part is arranged between the propellant containing cavity shell and the positive electrode combustible electrode bar, and the fixing parts are connected to a circuit; or
The conductive cathode comprises a plurality of cathode combustible electrode rods, and the conductive anode is a propellant containing cavity shell; the fixing piece is provided with a plurality of first through holes distributed in a ring-shaped layered manner; the one end embedding of negative pole combustible electrode stick is connected on first through-hole, and the other end is located and is richly fired inside the automatically controlled solid propellant, the insulating part is established and is held between chamber shell and the negative pole combustible electrode stick at the propellant, the mounting is all connected on the circuit.
In one embodiment, the combustible electrode is made of one or a combination of more than two of aluminum, silver, copper and stainless steel, participates in the combustion of the fuel-rich electrically-controlled solid propellant, and after the fuel-rich electrically-controlled solid propellant is combusted and pushed, the combustible electrode is exposed to a high-temperature and high-pressure environment to react with gas-phase products to be combusted into solid-phase particles, and the solid-phase particles are sprayed out of the gas generator nozzle along with the fuel gas.
In one embodiment, the tail pipe is a Laval pipe in a non-combustion mode or a flare pipe in a super-combustion mode.
In one embodiment, the combustible electrode is a cylindrical structure or a truncated cone structure or a foam structure.
In one embodiment, the power supply system is composed of a direct current power supply and a controller for controlling the output of the power supply; when the circuit between the power supply and the fuel gas generator is conducted, the power supply, the conductive anode, the conductive cathode and the rich-fuel electric control solid propellant form a closed loop, and the power supply controller is used for adjusting the magnitude of output voltage in real time so as to change the combustion rate of the rich-fuel electric control solid propellant and further change the magnitude of thrust.
In one embodiment, the rich-burn electrically-controlled solid propellant is composed of an oxidizer, a binder, a metal fuel, a plasticizer and a volume, wherein the oxidizer is one or more of hydroxylamine nitrate, lithium perchlorate, sodium perchlorate, potassium perchlorate and barium perchlorate, and the binder is one or more of polyvinyl alcohol, methyl cellulose, polyethylene oxide or polyvinyl acetate; the metal fuel is one or a combination of more of boron powder, magnesium powder and aluminum powder; the plasticizer is one or more of methyl silicone oil, glycerol and polyethylene glycol; the solvent is one or more of water, ethanol or ethyl acetate. More preferably, the binder is in the form of powder and has a particle size of 150 to 300 mesh. The particle size of the metal fuel is 100 nm-5 μm.
In one embodiment, the combustible electrode in the conductive positive electrode and/or the conductive negative electrode is in the form of a plurality of positive electrode combustible electrode rods/negative electrode combustible electrode rods, and the plurality of combustible electrode rods in the conductive positive electrode or the conductive negative electrode can adopt one specific implementation form of a plurality of coaxially distributed electrodes, a mesh electrode and a foam electrode.
The working principle of the invention is as follows: the fuel-rich electric control solid propellant is electrified through a power supply system and is combusted in the fuel gas generator to generate high-temperature fuel-rich gas, and the fuel-rich gas is sprayed into the afterburning chamber at high speed through a spray pipe of the fuel gas generator. Incoming air in the air inlet channel is sprayed into the afterburning chamber to be mixed with high-temperature rich fuel gas for secondary combustion, and high-temperature high-pressure gas generated by combustion is sprayed out through expansion of the tail spray pipe to generate thrust.
Compared with the prior art, the fuel-rich electronic control solid ramjet with continuously adjustable electrode combustible thrust provided by the invention has the following beneficial effects:
compared with the prior art, the invention has the beneficial effects that:
1. the invention discloses a rich-combustion electronic control solid ramjet engine with continuously adjustable electrode combustible thrust, which replaces a high-energy igniter of a traditional solid ramjet engine, a combustible electrode is directly used as the igniter without carrying an extra igniter, an electric ignition mode is adopted, and the ignition mode is safe and reliable due to the fact that a propellant is relatively intermittent.
2. The invention discloses a fuel-rich electronic control solid ramjet engine with continuously adjustable electrode combustible thrust, wherein a combustible electrode can be made of one or more of high-energy metal materials such as aluminum, silver, copper and stainless steel, and is ablated in a high-temperature and high-pressure environment when a fuel-rich electronic control solid propellant is combusted and pushed so as to participate in a gas-phase combustion reaction. On one hand, the combustible electrode plays a role in igniting and controlling the burning speed, and on the other hand, the electrode is combustible, so that the volume structure quality can be effectively reduced, and the total impact of the engine can be improved.
3. The invention discloses a fuel-rich electronic control solid ramjet engine with continuously adjustable electrode combustible thrust, which can effectively avoid the danger that the engine cannot normally work due to the fact that ionic flame generated by combustion of a fuel-rich electronic control solid propellant is conducted in an electric field environment to cause short circuit by adopting a combustible electrode.
4. The invention discloses a fuel-rich electronic control solid ramjet engine with continuously adjustable electrode combustible thrust, which can increase the content of boron powder or metal in fuel-rich electronic control solid propellant slurry by designing a combustible electrode, thereby improving the specific impulse of the fuel-rich electronic control solid propellant.
5. The invention discloses a fuel-rich electronic control solid ramjet with continuously adjustable electrode combustible thrust, which can realize continuous real-time adjustment of the engine thrust by changing the burning speed of a fuel-rich electronic control solid propellant by adjusting the voltage of two ends of a conductive anode and a conductive cathode, and solves the problems of complicated flow adjusting mechanism and high adjusting technical difficulty of the traditional solid ramjet.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
Fig. 1 is a schematic structural view of a fuel-rich electronically controlled solid ramjet engine with continuously adjustable electrode combustible thrust in embodiment 1 of the invention;
FIG. 2 is a schematic structural diagram of a fuel-rich electrically controlled solid ramjet gas generator with continuously adjustable electrode combustible thrust in embodiment 1 of the present invention;
FIG. 3 is a left side view of a right disc electrode in example 1 of the present invention;
FIG. 4 is a front view of a right disc electrode in example 1 of the present invention;
FIG. 5 is a left side view of the negative disk electrode in example 1 of the present invention;
FIG. 6 is a positive view of a negative disk electrode in example 1 of the present invention;
fig. 7 is a view showing an installation structure of the positive disc electrode, the negative disc electrode, and the ceramic insulator in example 1 of the present invention.
FIG. 8 is a schematic diagram of a circular table combustible electrode in example 2 of the present invention.
FIG. 9 is a left side view of a single truncated cone combustible electrode in example 2 of the invention;
fig. 10 is a front view of a single truncated combustible electrode in example 2 of the invention.
The reference numbers illustrate: 1-gas generator, 2-power supply system, 3-gas inlet channel, 4-afterburning chamber, 5-tail nozzle, 6-gas generator shell, 7-propellant containing cavity, 8-propellant containing cavity shell, 9-combustible electrode, 10-electrode insulating layer, 11-insulating heat-insulating material, 12-gas generator nozzle, 13-positive disk electrode, 14-negative disk electrode, 15-ceramic insulating piece, 16-cylindrical base, 17-conductive disk, 18-wiring column, 19-insulating piece and 20-fixing piece.
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
In the embodiment, the combustible electrode is adopted to control the conductive anode and/or the conductive cathode in the combustion circuit of the rich-combustion electronic control solid propellant, and the combustible electrode is made of one or a combination of more than two of aluminum, silver, copper and stainless steel. In the combustion process of the rich-combustion electric control solid propellant, the combustible electrode participates in the reaction and becomes a part of the combustion of the rich-combustion electric control solid propellant, so that the total impact of the engine is greatly increased, and the structural mass is reduced. Compared with an electric control solid engine in the current research, the design of the combustible electrode not only improves the filling ratio of the engine, enhances the controllability of the rich-combustion electric control solid propellant, reduces the short circuit phenomenon in the electric control combustion process of the rich-combustion electric control solid propellant, but also can control the combustion speed of the rich-combustion electric control solid propellant by changing the applied voltage.
In this embodiment, the combustible electrodes in the conductive positive electrode and/or the conductive negative electrode are all in the form of a plurality of positive electrode combustible electrode rods/negative electrode combustible electrode rods, and the plurality of combustible electrode rods in the conductive positive electrode or the conductive negative electrode can adopt a propeller accommodating cavity in which one of a plurality of electrodes are coaxially distributed, a mesh electrode and a foam electrode is distributed inside the gas generator.
In the embodiment, the fuel gas generator is coaxial with the afterburning chamber, and the volume utilization rate of the charge space in the engine can be fully improved by adopting the structure of the coaxially mounted fuel gas generator, so that more propellants are carried, and the range of the rocket is increased.
The invention has 3 specific implementation cases which are respectively embodiment 1, embodiment 2 and embodiment 3, wherein embodiment 1 is a positive and negative disc combustible electrode structure, embodiment 2 is a circular table combustible electrode structure, and embodiment 3 is a net combustible electrode structure.
Example 1
The present invention is further illustrated by the following examples, but it should not be construed that the scope of the above-described subject matter is limited to the following examples. Various substitutions and alterations can be made without departing from the technical idea of the invention and the scope of the invention is covered by the present invention according to the common technical knowledge and the conventional means in the field.
Referring to fig. 1, the fuel-rich electric control solid ramjet with the staggered combustible electrodes and continuously adjustable thrust in the embodiment 1 is shown. The staggered structure of the plurality of combustible electrodes is mainly used for enabling the current density of the end face of the rich-combustion electric control solid propellant to be more uniform in the electrifying ignition process and enabling combustion to be more uniform. The concrete structure includes:
the device comprises a fuel gas generator 1, a power supply system 2, an air inlet 3, a afterburning chamber 4 and a tail nozzle 5. The gas generator 1 comprises a gas generator housing 6, a propellant containing cavity 7, a propellant containing cavity housing 8, a combustible electrode 9, a combustible insulating layer 10, an insulating and heat insulating layer 11 and a gas generator nozzle 12.
An insulating and heat-insulating layer 11 is filled between the gas generator shell 6 and the propellant containing cavity shell 8, and a solid propellant containing cavity 7 which is rich in combustible solids is arranged between the propellant containing cavity shell 8 and the combustible electrode 9, namely as shown in figure 2.
The gas generator is provided with an electric control solid propellant which is not shown; the rich-combustion electric control solid propellant is composed of 30% of hydroxylamine nitrate, 4% of barium perchlorate, 35% of boron powder (the particle size is 100nm), 8% of water, 3% of glycerol and polyethylene glycol (wherein the components are mixed according to the mass fraction of 1: 1), and 20% of polyvinyl alcohol (the particle size is 150 meshes);
in embodiment 1, the combustible electrode 9 includes a plurality of positive electrode combustible electrode rods and a plurality of negative electrode combustible electrode rods, wherein the positive electrode combustible electrode rods and the negative electrode combustible electrode rods are aluminum electrodes; the propellant containing cavity shell 8 and all the anode combustible electrode rods form a conductive anode, and all the cathode combustible electrode rods form a conductive cathode; the positive electrode combustible electrode bar and the negative electrode combustible electrode bar both adopt a multi-aluminum electrode structure and a double-disc electrode structure, and are divided into a positive disc electrode 13 and a negative disc electrode 14. The positive electrode and the negative electrode are arranged in a staggered mode, so that the end face of the propellant burns uniformly.
The surfaces of the combustible electrodes are all coated with combustible insulating layers 10, and 0.3 mm of the combustible electrode close to the end of a gas generator spray pipe 12 is left without being coated with the combustible insulating layers 10 and is used for realizing initial ignition. Wherein, the combustible insulating layer 10 is made of polyvinyl chloride material and has a thickness of 0.12 mm.
The right circular disc electrode 13 is shown in fig. 3 and comprises a plurality of positive combustible electrode rods and a cylindrical base 16;
as shown in fig. 4, one side of the cylindrical base 16 is provided with a plurality of first through holes distributed in a ring layer shape, and the first through holes are radially arranged from the center to the periphery: 1 first through hole is arranged at the center; the second layer takes the first through hole at the center as the circle center, is 3mm apart from each other, and is provided with 4 first through holes distributed at 90 degrees; the third layer takes the first through hole at the center as the circle center, is 6mm apart from each other, and is distributed with 8 first through holes in 45 degrees; the fourth layer takes the first through hole at the center as the circle center, is 9mm apart from each other, and is distributed with 16 first through holes in a 22.5-degree distribution manner; the plurality of anode combustible electrode rods are fixed on the first layer and the third layer of through holes; the through holes of the second layer and the fourth layer are used for passing through a plurality of negative combustible electrode rods. The other side of the cylindrical base 16 has a cavity for embedding the ceramic insulator 15. More specifically, the side of the cylindrical base 16 is provided with external threads which are matched and connected with the internal threads of the propellant containing cavity shell 8 and connected with the positive pole of the power supply.
The negative disk electrode 14 is shown in fig. 5 and comprises a plurality of negative combustible electrode rods, a conductive disk 17 and a terminal 18. The plurality of negative electrode combustible electrode rods are arranged in a second layer and a fourth layer corresponding to the first through hole of the cylindrical base through the second through hole on the conductive disc 17 as shown in fig. 6, the plurality of negative electrode combustible electrode rods are fixedly connected to one side of the conductive disc 17, the binding post 18 is fixed to the other side of the conductive disc 17, and the binding post 18 is connected with the negative electrode of the power supply.
The ceramic insulator 15 is located between the positive and negative disk electrodes, and is provided with through holes with the number matched with that of the negative disk electrodes for insulation and isolation. As shown in fig. 7, the ceramic insulator 15 is inserted into the cavity of the cylindrical base 16 at one end and connected to the conductive disk 17 at the other end. A plurality of negative combustible electrode rods on the negative disc electrode 14 sequentially pass through the ceramic insulator 15 and the first through holes of the cylindrical base 16 and penetrate into the rich fuel containing cavity and face the gas generator nozzle 12.
The working process of the staggered multiple combustible electrodes and the fuel-rich electronic control solid ramjet with continuously adjustable thrust is as follows: the aluminum electrodes are arranged in a staggered way around the positive and negative electrodes. That is, the polarity of each layer of electrodes is the same, the polarities of the electrodes of the adjacent layers are opposite, the polarity of the electrode of the propellant containing cavity shell is positive, the electrode voltage of the first through hole on the outermost layer of the cylindrical base 16 is negative, the electrode voltage of the first through hole on the secondary outer layer is positive, and so on. The power supply system 2 supplies power to the propellant containing cavity shell 8 and the terminal 18, and the combustible aluminum electrode which is not coated with the combustible insulating layer 10 reacts with the rich-combustion electric control solid propellant to ignite the propellant. In the combustion process, the combustion speed of the combustible insulating layer 10 is higher than that of the propellant and the electrode, so that the combustible electrode and the electric control solid propellant are ensured to be always contacted at the end face. After the propellant is combusted, a plurality of aluminum electrodes react with the propellant gas to form solid particles in the high-temperature high-pressure environment in the gas generator 1, the solid particles are sprayed into the afterburning chamber 4 along with the rich-fuel gas, and the rich-fuel gas and the incoming air of the air inlet channel 3 are mixed in the afterburning chamber 4 for secondary combustion, and are sprayed out through the tail spray pipe 5 and the lava spray pipe. In addition, the voltage of the power supply system 2 can be adjusted to control the burning speed of the rich-burning electric control solid propellant according to the real-time working condition, so that the real-time continuous adjustment of the thrust is realized.
Example 2
The embodiment is a fuel-rich electronic control solid ramjet engine with a plurality of round table electrodes capable of combusting and continuously adjustable thrust. The circular truncated cone electrode mainly aims at longer gas generators, and due to the fact that the combustible electrode is electrified for a long time, the combustible electrode is easy to burn faster than a fuel-rich electric control propellant or melt due to heat accumulation, and the like. The structure of the fuel-rich electrically-controlled ramjet engine is shown in figure 1. With reference to fig. 8, the gas generator 1 has a specific structure including:
a gas generator housing 6, a propellant containing chamber housing 8 and a burnable electrode 9. An insulating and heat-insulating layer 11 is filled between the gas generator shell 6 and the propellant containing cavity shell 8, and a solid propellant containing cavity 7 for containing rich combustion is arranged between the propellant containing cavity shell 8 and the combustible electrode 9.
The gas generator 1 is provided with an unillustrated electrically controlled solid propellant; the rich-combustion electric control solid propellant is composed of 17% of hydroxylamine nitrate, 14% of lithium perchlorate, 33% of boron powder (the particle size is 100nm), 5% of magnesium powder, 8% of water, 3% of methyl silicone oil and polyethylene glycol (wherein the weight percentages are 1: 1), 20% of polyvinyl alcohol and polyethylene oxide (the weight ratio is 5:1, and the particle sizes are 300 meshes).
The propellant containing cavity shell 8 surrounds the propellant containing cavity 7, and the combustible electrode 9 is inserted into the fuel-rich electrically-controlled solid propellant. Specifically, in embodiment 2, the combustible electrode 9 includes a plurality of negative electrode combustible electrode rods, where the negative electrode combustible electrode rods are aluminum electrodes. The propellant containing cavity shell 8 forms a conductive anode, and all the cathode combustible electrode rods form a conductive cathode.
The inner surface of the lower end of the propellant containing cavity shell 8 is provided with internal threads which are connected with the positive electrode of the power supply; the propellant containing cavity shell 8 is fixedly connected with the combustible electrode 9 through an insulating piece 19; the insulating piece 19 is positioned in the propellant containing cavity 7, and two ends of the insulating piece are respectively embedded into the inner wall of the propellant containing cavity shell 8; the insulation piece 19 is provided with through holes with the same number as the combustible electrodes 9, and the combustible electrodes 9 penetrate through the through holes and are inserted into the fuel-rich electric control solid propellant.
A plurality of negative electrode combustible electrode bars in the combustible electrode 9 adopt a structure of a plurality of aluminum electrodes in parallel, one end of each negative electrode combustible electrode bar is connected to the fixing piece, and the other end of each negative electrode combustible electrode bar extends into the rich-fuel containing cavity and faces to the fuel gas generator spray pipe 12; the combustible electrode is shown in fig. 9-10 and comprises a plurality of aluminum electrodes in a circular truncated cone structure and an insulating part 19; the aluminum electrode is a circular truncated cone electrode, namely the diameter of the cathode combustible electrode rod at the end close to the gas generator spray pipe 12 is 1mm smaller than that of the cathode combustible electrode rod at the end close to the fixing piece. Wherein, the fixing member 20 is connected to the negative electrode of the power supply.
The surfaces of the negative electrode combustible electrode rods are all coated with a combustible insulating layer 10, and 0.5mm of non-coated insulating layer is reserved at the electrode close to the end of a gas generator spray pipe 12 and is used for realizing initial ignition. The combustible insulating layer 10 is made of a mixed material of polyvinyl alcohol and polytetrafluoroethylene, and the thickness of the combustible insulating layer is 0.15 mm.
The working process of the fuel-rich electronic control solid ramjet engine with the combustible and continuously adjustable thrust of the plurality of circular truncated cone electrodes is as follows: the power supply system 2 supplies power to the propellant containing cavity shell 8 (positive pole) and the fixing piece 20 (negative pole), and the combustible aluminum electrode which is not coated with the insulating layer reacts with the rich-combustion electric control solid propellant to ignite the propellant. In the combustion process, the combustion speed of the combustible insulating layer 10 is higher than that of the propellant and the electrode, so that the combustible electrode and the electric control solid propellant are ensured to be always contacted at the end face. After the propellant is combusted, a plurality of aluminum electrodes react with the propellant gas to form solid particles in the high-temperature high-pressure environment in the gas generator 1, the solid particles are sprayed into the afterburning chamber 4 along with the rich-fuel gas, and the rich-fuel gas and the incoming air of the air inlet channel 3 are mixed in the afterburning chamber 4 for secondary combustion, and are sprayed out through the tail spray pipe 5 and the lava spray pipe. In addition, the voltage of the power supply system 2 can be adjusted to control the burning speed of the rich-burning electric control solid propellant according to the real-time working condition, so that the real-time continuous adjustment of the thrust is realized.
Example 3
The embodiment is a foam electrode combustible and thrust continuously adjustable fuel-rich electronic control solid ramjet engine. The combustible foam electrode mainly aims at a large-diameter gas generator, on one hand, the combustible foam electrode is uniformly distributed in the propellant, so that the end face of the propellant burns more uniformly, and on the other hand, the combustible foam electrode is easy to ablate and is convenient to react with rich fuel gas. The structure of the fuel-rich electrically-controlled solid ramjet engine is shown in figure 1. The gas generator 1 comprises:
a gas generator housing 6, a propellant containment chamber housing 8 and a combustible aluminum foam electrode. An insulating and heat-insulating layer 11 is filled between the gas generator shell 6 and the propellant containing cavity shell 8, and a cavity 7 for containing the rich-burning solid propellant is arranged between the propellant containing cavity shell 8 and the flammable foamed aluminum electrode.
The gas generator is provided with an electric control solid propellant which is not shown; the rich-combustion electric control solid propellant consists of 30% of lithium perchlorate, 40% of boron powder (the particle size is 100nm), 7% of water, 3% of methyl silicone oil and polyethylene glycol (wherein the methyl silicone oil and the polyethylene glycol are mixed according to the mass ratio of 1: 1), 20% of polyvinyl alcohol and polyethylene oxide (the mass ratio is 5:1, and the particle sizes are all 300 meshes).
The propellant containing cavity shell 8 surrounds the propellant containing cavity 7, and the combustible foamed aluminum electrode is inserted into the rich-combustion electric control solid propellant. The inner surface of the lower end of the propellant containing cavity shell 8 is provided with internal threads which are connected with the positive electrode of the power supply; the propellant containing cavity shell 8 is fixedly connected with the combustible foamed aluminum electrode through a high-temperature resistant insulating part; the high-temperature-resistant insulating piece is positioned in the propellant containing cavity 7, and two ends of the high-temperature-resistant insulating piece are respectively embedded into the inner wall of the propellant containing cavity shell 8; the combustible foamed aluminum electrode is made of aluminum metal, the pore diameter is distributed between 0.5mm and 5mm, one end of the combustible foamed aluminum electrode is fixed on the conductive piece, and the other end of the combustible foamed aluminum electrode penetrates through the high-temperature-resistant insulating piece to penetrate into the rich-fuel containing cavity and face a jet pipe of the fuel gas generator; and the conductive piece is connected with the negative electrode of the power supply.
The surface of the flammable foamed aluminum electrode is uniformly coated with a flammable insulating layer by an immersion method, and the electrode close to the end 12 of the gas generator spray pipe is left with a non-flammable insulating layer of 1mm for realizing the first ignition. Wherein, the combustible insulating layer 10 is made of polytetrafluoroethylene mixed material, and the thickness is controlled between 0.15mm and 0.2 mm.
The working process of the foam electrode combustible and thrust continuously adjustable fuel-rich electronic control solid ramjet engine is as follows: the power supply system 2 supplies power to the propellant containing cavity shell 8 (positive pole) and the conductive piece (negative pole), and the combustible foamed aluminum electrode which is not coated with the insulating layer reacts with the rich-combustion electric control solid propellant to ignite the propellant. In the combustion process, the combustion speed of the combustible insulating layer 10 is higher than that of the propellant and the electrode, so that the combustible electrode and the electric control solid propellant are ensured to be always contacted at the end face. After the propellant is combusted, the combustible foamed aluminum electrode and the propellant gas are reacted to be solid particles in the high-temperature and high-pressure environment in the gas generator 1, the solid particles are sprayed into the afterburning chamber 4 along with the rich-fuel gas, the rich-fuel gas and the inflow air of the air inlet channel 3 are mixed in the afterburning chamber 4 for secondary combustion, and the mixed gas is sprayed out through the expansion spray pipe 5 of the tail spray pipe 5. In addition, the voltage of the power supply system 2 can be adjusted to control the burning speed of the rich-burning electric control solid propellant according to the real-time working condition, so that the real-time continuous adjustment of the thrust is realized.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. A fuel-rich electric control solid ramjet engine with continuously adjustable electrode combustible thrust is characterized by comprising a power supply system, a fuel gas generator, an air inlet channel, a afterburning chamber and a tail nozzle which are sequentially connected;
the fuel gas generator comprises a fuel gas generator shell and a conductive assembly, wherein a propellant containing cavity capable of containing the rich-fuel electric control solid propellant is arranged in the fuel gas generator shell, and a fuel gas generator spray pipe facing the afterburning chamber and communicated with the propellant containing cavity is also arranged on the fuel gas generator shell;
the conductive assembly comprises a conductive anode and a conductive cathode, the rich-combustion electric control solid propellant is arranged between the conductive anode and the conductive cathode, and the conductive assembly further comprises a circuit connected with a power supply system, the conductive anode, the rich-combustion electric control solid propellant and the conductive cathode;
and part or all of at least one of the conductive positive electrode and the conductive negative electrode is a combustible electrode.
2. The electronically controlled solid ramjet engine with continuously adjustable electrode burnable thrust as recited in claim 1, wherein said gas generator housing is cylindrical, said propellant-receiving chamber is cylindrical, and said gas generator nozzle is disposed at an aft end of said gas generator housing along an axial direction of said gas generator housing; the combustible electrode is embedded and connected in the fuel-rich electric control solid propellant and comprises an isolation part and an exposed part;
the isolation part comprises a combustible insulating layer for isolating the rich-combustion electric control solid propellant from the side edge of the combustible electrode and preventing the rich-combustion electric control solid propellant from being integrally conducted; the exposed part is positioned at the position of the fuel-rich electric control solid propellant and close to the gas generator spray pipe so as to realize the first ignition of the fuel-rich electric control solid propellant.
3. The electrically controlled solid ramjet engine with continuously adjustable electrode burnable thrust and rich fuel according to claim 1, wherein the gas generator further comprises a propellant containing chamber housing, the propellant containing chamber being located inside the propellant containing chamber housing, and an insulating layer of heat is provided between the gas generator housing and the propellant containing chamber housing.
4. The fuel-rich electronically-controlled solid ramjet engine with continuously adjustable electrode flammability thrust as claimed in claim 3, wherein one or both of the conductive positive electrode and the conductive negative electrode is a flammable electrode; one part of the other one of the conductive positive electrode and the conductive negative electrode is a combustible electrode, and the other part of the other one of the conductive positive electrode and the conductive negative electrode is a propellant containing cavity shell.
5. The electrically-controlled solid ramjet engine with electrode combustible thrust continuously adjustable and rich in fuel according to claim 4, characterized in that the conductive assembly further comprises a conductive disc, an insulating member and a cylindrical base fixedly arranged inside the housing of the gas generator, the cylindrical base and the housing of the propellant containing cavity together enclose a propellant containing cavity, and the insulating member is arranged between the conductive disc and the cylindrical base;
the conductive positive electrode comprises a plurality of positive electrode combustible electrode rods, and the conductive negative electrode comprises a propellant containing cavity shell and a plurality of negative electrode combustible electrode rods; the cylindrical base is provided with first through holes distributed in an annular layered manner; one end of the positive combustible electrode rod is embedded and connected to the single-layer first through hole on the cylindrical base, and the other end of the positive combustible electrode rod is positioned in the fuel-rich electric control solid propellant; the conductive disc is provided with a plurality of second through holes corresponding to the first through holes of the double layers on the cylindrical base, one end of the negative combustible electrode bar is embedded and connected onto the second through holes, the other end of the negative combustible electrode bar penetrates through the insulating piece and the first through holes of the double layers on the cylindrical base and then is positioned in the fuel-rich electric control solid propellant, and the conductive disc and the cylindrical base are both connected onto a circuit; or
The conductive cathode comprises a plurality of cathode combustible electrode rods, and the conductive anode comprises a propellant containing cavity shell and a plurality of anode combustible electrode rods; the cylindrical base is provided with a plurality of first through holes distributed in an annular layered manner; one end of the negative electrode combustible electrode bar is embedded and connected to the single-layer first through hole on the cylindrical base, and the other end of the negative electrode combustible electrode bar is positioned in the fuel-rich electric control solid propellant; be equipped with a plurality of second through-holes that correspond with the first through-hole of double-deck on the cylinder base on the electrically conductive disc, the one end embedding of anodal combustible electrode stick is connected on the second through-hole, and the other end passes and lies in after the first through-hole of double-deck on insulating part, the cylinder base and richly fires inside the automatically controlled solid propellant, electrically conductive disc, cylinder base all connect on the circuit.
6. The electrically-controlled fuel-rich solid ramjet engine with continuously adjustable electrode combustible thrust according to claim 3, wherein one of the conductive positive electrode and the conductive negative electrode is a combustible electrode and the other is a propellant containing cavity housing.
7. The electrically controlled fuel-rich ramjet engine with continuously adjustable electrode flammability thrust as claimed in claim 6, wherein the electrically conductive assembly further comprises an insulating member and a fixing member fixedly disposed inside the gas generator housing, the fixing member and the propellant containing chamber housing together defining a propellant containing chamber;
the conductive positive electrode comprises a plurality of positive electrode combustible electrode rods, and the conductive negative electrode is a propellant containing cavity shell; the fixing piece is provided with a plurality of first through holes distributed in a ring-shaped layered manner; one end of the positive electrode combustible electrode bar is embedded and connected to the first through hole, the other end of the positive electrode combustible electrode bar is positioned in the fuel-rich electric control solid propellant, the insulating part is arranged between the propellant containing cavity shell and the positive electrode combustible electrode bar, and the fixing parts are connected to a circuit; or
The conductive cathode comprises a plurality of cathode combustible electrode rods, and the conductive anode is a propellant containing cavity shell; the fixing piece is provided with a plurality of first through holes distributed in a ring-shaped layered manner; the one end embedding of negative pole combustible electrode stick is connected on first through-hole, and the other end is located and is richly fired inside the automatically controlled solid propellant, the insulating part is established and is held between chamber shell and the negative pole combustible electrode stick at the propellant, the mounting is all connected on the circuit.
8. The electrically-controlled solid ramjet engine with electrode combustible thrust continuously adjustable according to any one of claims 1 to 7, characterized in that the material of the combustible electrode is one or a combination of two or more of aluminum, silver, copper and stainless steel, the combustible electrode participates in the combustion of the electrically-controlled solid propellant with rich combustion, and after the electrically-controlled solid propellant is combusted and pushed, the combustible electrode is exposed to a high-temperature and high-pressure environment to react with gas phase products to be combusted into solid phase particles, and the solid phase particles are ejected from the gas generator nozzle along with the gas.
9. The fuel-rich electrically-controlled solid ramjet engine with continuously adjustable electrode combustible thrust according to any one of claims 1 to 7, characterized in that the tail pipe is a de-ignition mode laval pipe or a flaring pipe of a super-combustion mode.
10. The fuel-rich electrically-controlled solid ramjet engine with the electrode combustible thrust continuously adjustable according to any one of claims 1 to 7, characterized in that the combustible electrode is of a cylindrical structure, a truncated cone structure or a foam structure.
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