CN110469426B - Solid rocket engine with continuously adjustable thrust and solid rocket - Google Patents
Solid rocket engine with continuously adjustable thrust and solid rocket Download PDFInfo
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- CN110469426B CN110469426B CN201910778824.4A CN201910778824A CN110469426B CN 110469426 B CN110469426 B CN 110469426B CN 201910778824 A CN201910778824 A CN 201910778824A CN 110469426 B CN110469426 B CN 110469426B
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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
- F02K9/26—Burning control
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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
- F02K9/28—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants having two or more propellant charges with the propulsion gases exhausting through a common nozzle
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Abstract
The invention discloses a solid rocket engine with continuously adjustable thrust and a solid rocket, which comprise a fuel gas generating assembly, a combustion chamber and a tail nozzle which are sequentially connected, wherein the fuel gas generating assembly comprises an oxygen-rich fuel gas generator and an oxygen-poor fuel gas generator; an oxygen-enriched accommodating cavity capable of accommodating an oxygen-enriched electric control solid propellant is arranged in the oxygen-enriched fuel gas generator, and an oxygen-enriched ablation circuit is arranged on the oxygen-enriched fuel gas generator; a lean oxygen accommodating cavity capable of accommodating a lean oxygen electric control solid propellant is arranged in the lean oxygen gas generator, and a lean oxygen ablation circuit is arranged on the lean oxygen gas generator; the oxygen-enriched gas generator is provided with an oxygen-enriched controller capable of controlling the flow of oxygen-enriched gas, and the oxygen-poor gas generator is provided with an oxygen-poor controller capable of controlling the flow of oxygen-poor gas, so that the problems of narrow thrust adjusting range and large technical difficulty of the traditional solid rocket engine and the problems of complex supply and adjusting system of the liquid rocket engine are solved.
Description
Technical Field
The invention relates to the technical field of solid rocket engines, in particular to a solid rocket engine with continuously adjustable thrust and a solid rocket.
Background
The solid rocket engine is a rocket engine taking a solid propellant as fuel. The solid propellant powder injection device mainly comprises a combustion chamber shell, a solid propellant powder charge and a spray pipe. The solid rocket engine has the outstanding characteristics of simple structure, few required parts and no actuating part generally. The characteristics ensure that the solid rocket engine has high reliability and convenient maintenance and operation. Therefore, the solid rocket engine is widely applied to various missiles, and the trend of solidifying the power systems of various tactical and strategic missiles is more and more obvious.
For existing solid or liquid rocket engines, direct flow regulation is typically used to control engine thrust. For a rocket engine using solid fuel, the conventional flow rate regulation method is usually mechanical regulation, the regulation range of the regulation method is narrow, and an actuating part is required to play a role in controlling the flow rate, for example, by a control valve and the like, so as to finally achieve the effect of changing the thrust. For rocket engines using liquid fuel, the flow rate is generally regulated by injection pressure drop, and the regulation and the supply mode thereof are complex, have more parts and relatively lower reliability.
Disclosure of Invention
Aiming at the problems that the fuel flow regulation range of a solid rocket engine is narrow, a part needs to be actuated and the like in the prior art, the invention provides the solid rocket engine with continuously adjustable thrust and the solid rocket, which are beneficial to solving the problems of narrow thrust regulation range and large technical difficulty of the traditional solid rocket engine and the problem of complex supply and regulation system of a liquid rocket engine.
In order to achieve the aim, the invention provides a solid rocket engine with continuously adjustable thrust, which comprises a fuel gas generating assembly, a combustion chamber and a tail nozzle which are connected in sequence, wherein the fuel gas generating assembly comprises an oxygen-rich fuel gas generator and an oxygen-poor fuel gas generator;
an oxygen-enriched accommodating cavity capable of accommodating an oxygen-enriched electric control solid propellant is arranged in the oxygen-enriched fuel gas generator, an oxygen-enriched ablation circuit capable of ablating the oxygen-enriched fuel gas generated by the oxygen-enriched electric control solid propellant is arranged on the oxygen-enriched fuel gas generator, and the oxygen-enriched accommodating cavity is communicated with the combustion chamber through an oxygen-enriched fuel gas channel;
the oxygen-poor fuel gas generator is internally provided with an oxygen-poor accommodating cavity capable of accommodating an oxygen-poor electric control solid propellant, the oxygen-poor fuel gas generator is provided with an oxygen-poor ablation circuit capable of ablating oxygen-poor fuel gas generated by the oxygen-poor electric control solid propellant, and the oxygen-poor accommodating cavity is communicated with the combustion chamber through an oxygen-poor fuel gas channel;
the oxygen-enriched gas generator is provided with an oxygen-enriched controller capable of controlling the flow of oxygen-enriched gas, and the oxygen-poor gas generator is provided with an oxygen-poor controller capable of controlling the flow of oxygen-poor gas.
Further preferably, the oxygen-deficient ablation circuit comprises a first cathode, a first anode and a first power supply respectively electrically connected with the first cathode and the first anode, an oxygen-deficient ablation cavity capable of ablating the oxygen-deficient electrically-controlled solid propellant is arranged between the first cathode and the first anode, and the oxygen-deficient controller is arranged on the first power supply.
Preferably, the oxygen-enriched ablation circuit comprises a second cathode, a second anode and a second power supply which is respectively and electrically connected with the second cathode and the second anode, an oxygen-enriched ablation cavity which can ablate the oxygen-enriched electrically-controlled solid propellant is arranged between the second cathode and the second anode, and the oxygen-enriched controller is arranged on the second power supply.
Further preferably, the lean oxygen gas generator is of a cylindrical structure, and the lean oxygen accommodating cavity is a cylindrical cavity arranged inside the lean oxygen gas generator;
the oxygen-enriched fuel gas generator is of a hollow columnar structure sleeved outside the oxygen-poor fuel gas generator, and the oxygen-enriched accommodating cavity is an annular columnar cavity arranged inside the oxygen-enriched fuel gas generator.
Preferably, one of the first cathode and the first anode is an electrode rod, the other one of the first cathode and the first anode is an annular electrode plate, the electrode rod is inserted into the axial position of the oxygen-deficient electrically-controlled solid propellant, and the annular electrode plate is wrapped on the side wall of the oxygen-deficient electrically-controlled solid propellant;
and the second cathode and the second anode are both annular electrode plates, one annular electrode plate is attached to the wall of the upper inner ring of the oxygen-enriched electric-control solid propellant, and the other annular electrode plate is attached to the wall of the upper outer ring of the oxygen-enriched electric-control solid propellant.
Preferably, the oxygen-enriched fuel gas generator is of a cylindrical structure, and the oxygen-enriched accommodating cavity is a cylindrical cavity arranged in the oxygen-enriched fuel gas generator;
the oxygen-poor fuel gas generator is a hollow columnar structure sleeved outside the oxygen-rich fuel gas generator, and the oxygen-poor accommodating cavity is an annular columnar cavity arranged inside the oxygen-poor fuel gas generator.
Preferably, one of the second cathode and the second anode is an electrode rod, the other one of the second cathode and the second anode is an annular electrode plate, the electrode rod is inserted into the axial position of the oxygen-enriched electrically-controlled solid propellant, and the annular electrode plate is wrapped on the side wall of the oxygen-enriched electrically-controlled solid propellant;
the first cathode and the first anode are both annular electrode plates, one annular electrode plate is attached to the wall of the upper inner ring of the oxygen-deficient electrically-controlled solid propellant, and the other annular electrode plate is attached to the wall of the upper outer ring of the oxygen-deficient electrically-controlled solid propellant.
Further preferably, the tail pipe is of a horn-shaped flaring structure, the combustion chamber is connected with one end, with a smaller caliber, of the tail pipe, and a closing structure is arranged at one end, connected with the tail pipe, of the combustion chamber.
In order to achieve the purpose, the invention also provides a solid rocket with continuously adjustable thrust, which comprises a rocket body, wherein the rocket body is provided with the solid rocket engine with continuously adjustable thrust.
The invention discloses a solid rocket engine with continuously adjustable thrust and a solid rocket, which are different from the traditional solid rocket engine in that a fuel gas generating assembly in the scheme is designed into two independent oxygen-rich fuel gas generators and two independent oxygen-poor fuel gas generators, wherein the oxygen-rich fuel gas generators and the oxygen-poor fuel gas generators are respectively loaded with an oxygen-rich electric control solid propellant and an oxygen-poor electric control solid propellant, and the flow of the fuel generated after the oxygen-rich electric control solid propellant and the oxygen-poor electric control solid propellant are gasified through an oxygen-rich controller and an oxygen-poor controller in real time, so that the real-time continuous adjustment of the thrust of the engine is realized, different flight conditions are met, the flight envelope of the engine is widened, and the problems of narrow thrust adjusting range, large technical difficulty and complex supply and adjusting system of the traditional solid rocket engine are solved.
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 front cross-sectional view of a continuously variable thrust solid rocket engine in an embodiment of the present invention;
FIG. 2 is a side cross-sectional view of a continuously variable thrust solid rocket engine in an embodiment of the present invention;
FIG. 3 is a first block diagram of a first cathode, a first anode, and an oxygen-depleted electrically controlled solid propellant in accordance with an embodiment of the present invention;
FIG. 4 is a diagram of a first installation configuration of a second cathode, a second anode and an oxygen-enriched electrically controlled solid propellant in accordance with an embodiment of the present invention;
FIG. 5 is a diagram of a second cathode, a second anode and a second installation configuration of an oxygen-enriched electrically controlled solid propellant in accordance with an embodiment of the present invention;
fig. 6 is a second installation configuration of the first cathode, the first anode and the oxygen-depleted electrically controlled solid propellant in accordance with an embodiment of the present invention.
The reference numbers illustrate: 1-oxygen-poor electric control solid propellant, 2-oxygen-poor fuel gas generator, 3-oxygen-rich electric control solid propellant, 4-oxygen-rich fuel gas generator, 5-combustion chamber, 6-tail nozzle, 7-oxygen-rich fuel gas channel, 8-oxygen-poor fuel gas channel, 9-first cathode, 10-first anode, 11-second cathode, 12-second anode,
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.
The solid rocket engine with continuously adjustable thrust force as shown in fig. 1-2 comprises a gas generating assembly, a combustion chamber 5 and a tail nozzle 6 which are connected in sequence, wherein the gas generating assembly comprises an oxygen-rich gas generator 4 and an oxygen-poor gas generator 2.
An oxygen-enriched accommodating cavity capable of accommodating the oxygen-enriched electric control solid propellant 3 is arranged in the oxygen-enriched fuel gas generator 4, an oxygen-enriched ablation circuit which is not shown and can ablate the oxygen-enriched fuel gas generated by the oxygen-enriched electric control solid propellant 3 is arranged on the oxygen-enriched fuel gas generator 4, and the oxygen-enriched accommodating cavity is communicated with the combustion chamber 5 through an oxygen-enriched fuel gas channel 7; the oxygen-enriched electrically-controlled solid propellant 3 is formed by compounding and polymerizing fuel and oxidant, the content of the oxidant in the oxygen-enriched electrically-controlled solid propellant 3 is far more than that of the fuel, after the oxygen-enriched ablation circuit is electrified, the fuel and the oxidant in the oxygen-enriched electrically-controlled solid propellant 3 are subjected to combustion reaction under the ablation effect, oxygen-enriched gas is further generated, the oxygen-enriched gas flows into the combustion chamber 5, and most or all of the oxygen-enriched gas is the oxidant because the content of the oxidant is far more than that of the fuel. The oxygen-enriched electrically-controlled solid propellant 3 in the embodiment can be obtained by the electrically-controlled solid propellant preparation method disclosed in patent CN 106905091A.
An oxygen-poor accommodating cavity capable of accommodating the oxygen-poor electric control solid propellant 1 is arranged in the oxygen-poor fuel gas generator 2, an oxygen-poor ablation circuit which is not shown and can ablate the oxygen-poor fuel gas generated by the oxygen-poor electric control solid propellant 1 is arranged on the oxygen-poor fuel gas generator 2, and the oxygen-poor accommodating cavity is communicated with the combustion chamber 5 through an oxygen-poor fuel gas channel 8; the oxygen-deficient solid propellant 1 is formed by compounding and polymerizing fuel and oxidant, the content of the oxidant in the oxygen-deficient solid propellant 1 is far less than that of the fuel, after the oxygen-deficient ablation circuit is electrified, the fuel and the oxidant in the oxygen-deficient solid propellant 1 are subjected to combustion reaction under the ablation action, so that oxygen-deficient gas is generated, the oxygen-deficient gas flows into the combustion chamber 5, and most or all of the oxygen-deficient gas is fuel because the content of the oxidant is far less than that of the fuel. The oxygen-deficient electrically controlled solid propellant 1 in the present embodiment can be obtained by the electrically controlled solid propellant preparation method disclosed in patent CN 106905091A.
An oxygen-rich controller which can control the flow rate of the oxygen-rich gas and is not shown in the figure is arranged on the oxygen-rich gas generator 4, and an oxygen-poor controller which can control the flow rate of the oxygen-poor gas and is not shown in the figure is arranged on the oxygen-poor gas generator 2. The two independent oxygen-enriched fuel gas generators 4 and the two independent oxygen-depleted fuel gas generators 2 are used, the oxygen-enriched fuel gas generators 4 and the two independent oxygen-depleted fuel gas generators 2 are respectively loaded with the oxygen-enriched electric control solid propellant 3 and the oxygen-depleted electric control solid propellant 1, and the flow rates of the fuels on the oxygen-enriched electric control solid propellant 3 and the oxygen-depleted electric control solid propellant 1 are adjusted in real time through the oxygen-enriched controller and the oxygen-depleted controller, so that the real-time continuous adjustment of the thrust of the engine is realized, different flight working conditions are met, the flight envelope of the engine is widened, and the problems of narrow thrust adjustment range, high technical difficulty and complex supply and adjustment system of a liquid rocket engine are solved.
The voltage on the oxygen-enriched ablation circuit and the voltage on the oxygen-deficient ablation circuit are adjusted through the oxygen-enriched controller and the oxygen-deficient controller, the reaction rate of ablation reaction on the oxygen-enriched electric control solid propellant 3 and the oxygen-deficient electric control solid propellant 1 is adjusted, the effect of adjusting the flow of oxygen-enriched gas and oxygen-deficient gas is further achieved, on the premise that the equivalence ratio of the oxygen-enriched gas to the oxygen-deficient gas is kept to be 1, the real-time continuous adjustment of the thrust of the engine can be achieved by changing the flow supply of the oxygen-deficient gas and the oxygen-enriched gas, different flight working conditions are met, and the flight envelope of the engine.
Preferably, the oxygen-poor fuel gas generator 2 is of a cylindrical structure, and the oxygen-poor accommodating cavity is a cylindrical cavity arranged inside the oxygen-poor fuel gas generator 2; the oxygen-rich fuel gas generator 4 is a hollow columnar structure sleeved outside the oxygen-poor fuel gas generator 2, the oxygen-rich accommodating cavity is an annular columnar cavity arranged inside the oxygen-rich fuel gas generator 4, under the structure, the oxygen-poor electric control solid propellant 1 is of a columnar structure, and the oxygen-rich electric control solid propellant 3 is of a hollow columnar structure, which is shown in the figure in the embodiment.
At this time, the oxygen-deficient ablation circuit includes a first power supply, a first cathode 9 and a first anode 10, which are electrically connected, and the oxygen-deficient controller is disposed on the first power supply. One of the first cathode 9 and the first anode 10 is an electrode rod, and the other is an annular electrode plate, the electrode rod is inserted into the axial position of the oxygen-deficient electrically-controlled solid propellant 1, and the annular electrode plate is wrapped on the side wall of the oxygen-deficient electrically-controlled solid propellant 1, as shown in fig. 3; an ablation cavity is formed between the first cathode 9 and the first anode 10, so that the oxygen-deficient electrically-controlled solid propellant 1 with the columnar structure is ablated to generate oxygen-deficient fuel gas; the oxygen-enriched ablation circuit comprises a second power supply, a second cathode 11 and a second anode 12 which are electrically connected, and the oxygen-enriched controller is arranged on the second power supply. Both the second cathode 11 and the second anode 12 are annular electrode plates, one of which is attached to the wall of the inner ring of the oxygen-enriched electrically-controlled solid propellant 3, and the other is attached to the wall of the outer ring of the oxygen-enriched electrically-controlled solid propellant 3, as shown in fig. 4; an ablation cavity is formed between the second cathode 11 and the second anode 12, so that the oxygen-enriched electric control solid propellant 3 with the hollow cylindrical structure is ablated to generate oxygen-enriched fuel gas.
Or:
the oxygen-enriched fuel gas generator 4 is of a columnar structure, and the oxygen-enriched accommodating cavity is a columnar cavity arranged inside the oxygen-enriched fuel gas generator 4; the oxygen-poor fuel gas generator 2 is a hollow columnar structure sleeved outside the oxygen-rich fuel gas generator 4, the oxygen-poor accommodating cavity is an annular columnar cavity arranged inside the oxygen-poor fuel gas generator 2, under the structure, the oxygen-rich electrically-controlled solid propellant 3 is of a columnar structure, and the oxygen-poor electrically-controlled solid propellant 1 is of a hollow columnar structure.
At this time, the oxygen-enriched ablation circuit includes a second power supply, a second cathode 11 and a second anode 12, which are electrically connected, and the oxygen-enriched controller is disposed on the second power supply. One of the second cathode 11 and the second anode 12 is an electrode rod, and the other one is an annular electrode plate, the electrode rod is inserted into the axial position of the oxygen-enriched electrically-controlled solid propellant 3, and the annular electrode plate is wrapped on the side wall of the oxygen-enriched electrically-controlled solid propellant 3, as shown in fig. 5; an ablation cavity is formed between the second cathode 11 and the second anode 12, so that the oxygen-enriched electrically-controlled solid propellant 3 with the columnar structure is ablated to generate oxygen-enriched fuel gas; the oxygen-deficient ablation circuit comprises a first power supply, a first cathode 9 and a first anode 10 which are electrically connected, and an oxygen-deficient controller is arranged on the first power supply. Both the first cathode 9 and the first anode 10 are annular electrode plates, one of which is attached to the wall of the inner ring of the oxygen-deficient electrically-controlled solid propellant 1, and the other is attached to the wall of the outer ring of the oxygen-deficient electrically-controlled solid propellant 1, as shown in fig. 6; an ablation cavity is formed between the first cathode 9 and the first anode 10, so that the oxygen-deficient electrically-controlled solid propellant 1 with a hollow cylindrical structure is ablated, and oxygen-deficient fuel gas is generated.
Further preferably, the tail pipe 6 is a trumpet-shaped flaring structure, the combustion chamber 5 is connected with the tail pipe 6 at one end with a smaller caliber, a closing-up structure is arranged at one end of the combustion chamber 5 connected with the tail pipe 6, and a structure which is closed up first and then flares is adopted, so that the thrust effect generated by gas combustion is more remarkable.
The structure of the oxygen-poor fuel gas generator 2 and the oxygen-rich fuel gas generator 4 which are coaxially arranged can fully improve the volume utilization rate of the internal charging space of the engine, carry more propellants and increase the range of the rocket. Of course, the lean oxygen gas generator 2 and the rich oxygen gas generator 4 need not be installed coaxially, but may be installed at a reasonable location according to the overall layout of the flight. Even if the lean oxygen gas generator 2 is installed separately from the rich oxygen gas generator 4, it can enter the afterburner through two gas inlets.
The specific working process of the solid rocket engine with continuously adjustable thrust in the embodiment is as follows:
firstly, the relationship between the burning rate and the voltage of the oxygen-deficient electrically-controlled solid propellant 1 can be obtained through a plurality of tests:
r1＝f(u1)
in the formula, r1For the electrically controlled combustion of the solid propellant 1 in the absence of oxygen, u1Is the voltage of the oxygen-deficient ablation circuit;
the density rho of the oxygen-deficient electrically-controlled solid propellant 1 can be obtained by measurement1By measuring oxygen depletionThe burning surface area A of the solid propellant 1 can be obtained by controlling the sectional area of the grain1. Thus, the mass flow of the oxygen-depleted electrically controlled solid propellant 1
The variation with voltage is as follows:
secondly, a relation between the burning rate and the voltage of the oxygen-enriched electric control solid propellant 3 can be obtained through a plurality of tests:
r2＝g(u2)
in the formula, r2The burning speed u of the oxygen-enriched electric control solid propellant 32Is the voltage of the oxygen-enriched ablation circuit;
the density rho of the oxygen-enriched electric control solid propellant 3 can be obtained by measurement2The combustion surface area A of the oxygen-enriched electric control solid propellant 3 can be obtained by measuring the sectional area of the grain2. Therefore, the mass flow of the oxygen-enriched electrically-controlled solid propellant 3
The variation with voltage is as follows:
the equivalence ratio of the solid rocket engine during operation is such that the flow rates of the oxygen-poor fuel gas generator 2 and the oxygen-rich fuel gas generator 4 are only affected by the voltage of the oxygen-poor ablation circuit and the oxygen-rich ablation circuit under the condition of given engine structural parameters and the prescription of the explosive column. Thus, the engine equivalence ratio can be made 1 directly by adjusting the voltage of the oxygen-lean ablation circuit to the oxygen-rich ablation circuit. When the engine starts to work, the oxygen-poor fuel gas generator 2 and the oxygen-rich fuel gas generator 4 are ignited at the same time, the oxygen-poor fuel gas and the oxygen-rich fuel gas enter the rocket combustion chamber 5 at the same time for mixing combustion, and a high-temperature and high-pressure mixture generated by combustion is accelerated and discharged through a tail nozzle 6 which contracts and then expands to generate thrust.
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 (9)
1. A solid rocket engine with continuously adjustable thrust comprises a fuel gas generation assembly, a combustion chamber and a tail nozzle which are sequentially connected, and is characterized in that the fuel gas generation assembly comprises an oxygen-rich fuel gas generator and an oxygen-poor fuel gas generator;
an oxygen-enriched accommodating cavity capable of accommodating an oxygen-enriched electric control solid propellant is arranged in the oxygen-enriched fuel gas generator, an oxygen-enriched ablation circuit capable of ablating the oxygen-enriched fuel gas generated by the oxygen-enriched electric control solid propellant is arranged on the oxygen-enriched fuel gas generator, and the oxygen-enriched accommodating cavity is communicated with the combustion chamber through an oxygen-enriched fuel gas channel;
the oxygen-poor fuel gas generator is internally provided with an oxygen-poor accommodating cavity capable of accommodating an oxygen-poor electric control solid propellant, the oxygen-poor fuel gas generator is provided with an oxygen-poor ablation circuit capable of ablating oxygen-poor fuel gas generated by the oxygen-poor electric control solid propellant, and the oxygen-poor accommodating cavity is communicated with the combustion chamber through an oxygen-poor fuel gas channel;
the oxygen-enriched gas generator is provided with an oxygen-enriched controller capable of controlling the flow of oxygen-enriched gas, and the oxygen-poor gas generator is provided with an oxygen-poor controller capable of controlling the flow of oxygen-poor gas.
2. The solid rocket engine with continuously adjustable thrust force according to claim 1, wherein the oxygen-deficient ablation circuit comprises a first cathode, a first anode and a first power supply electrically connected with the first cathode and the first anode respectively, an oxygen-deficient ablation cavity capable of ablating the oxygen-deficient electrically-controlled solid propellant is arranged between the first cathode and the first anode, and the oxygen-deficient controller is arranged on the first power supply.
3. The solid rocket engine with continuously adjustable thrust of claim 2, wherein the oxygen-enriched ablation circuit comprises a second cathode, a second anode and a second power supply respectively electrically connected with the second cathode and the second anode, an oxygen-enriched ablation cavity capable of ablating the oxygen-enriched electrically-controlled solid propellant is arranged between the second cathode and the second anode, and the oxygen-enriched controller is arranged on the second power supply.
4. The solid-rocket engine with continuously adjustable thrust force of claim 3 wherein said oxygen-lean gas generator is of a cylindrical configuration and said oxygen-lean holding cavity is a cylindrical cavity disposed within said oxygen-lean gas generator;
the oxygen-enriched fuel gas generator is of a hollow columnar structure sleeved outside the oxygen-poor fuel gas generator, and the oxygen-enriched accommodating cavity is an annular columnar cavity arranged inside the oxygen-enriched fuel gas generator.
5. The solid-rocket engine with continuously adjustable thrust force of claim 4, wherein one of the first cathode and the first anode is an electrode rod, the other one of the first cathode and the first anode is an annular electrode plate, the electrode rod is inserted into the axial position of the oxygen-deficient electrically-controlled solid propellant, and the annular electrode plate is wrapped on the side wall of the oxygen-deficient electrically-controlled solid propellant;
and the second cathode and the second anode are both annular electrode plates, one annular electrode plate is attached to the wall of the upper inner ring of the oxygen-enriched electric-control solid propellant, and the other annular electrode plate is attached to the wall of the upper outer ring of the oxygen-enriched electric-control solid propellant.
6. The solid-rocket engine with continuously adjustable thrust force of claim 3, wherein the oxygen-rich gas generator is of a cylindrical structure, and the oxygen-rich accommodating cavity is a cylindrical cavity arranged inside the oxygen-rich gas generator;
the oxygen-poor fuel gas generator is a hollow columnar structure sleeved outside the oxygen-rich fuel gas generator, and the oxygen-poor accommodating cavity is an annular columnar cavity arranged inside the oxygen-poor fuel gas generator.
7. The solid rocket engine with continuously adjustable thrust force of claim 6, wherein one of the second cathode and the second anode is an electrode rod, the other one of the second cathode and the second anode is an annular electrode plate, the electrode rod is inserted into the axial position of the oxygen-enriched electrically-controlled solid propellant, and the annular electrode plate is wrapped on the side wall of the oxygen-enriched electrically-controlled solid propellant;
the first cathode and the first anode are both annular electrode plates, one annular electrode plate is attached to the wall of the upper inner ring of the oxygen-deficient electrically-controlled solid propellant, and the other annular electrode plate is attached to the wall of the upper outer ring of the oxygen-deficient electrically-controlled solid propellant.
8. The solid rocket engine with continuously adjustable thrust force according to claim 1, 2 or 3, wherein the tail pipe is of a flared structure, the combustion chamber is connected with the end with the smaller caliber on the tail pipe, and the end of the combustion chamber connected with the tail pipe is provided with a closing structure.
9. A solid rocket with continuously adjustable thrust, which comprises a rocket body, and is characterized in that the solid rocket engine with continuously adjustable thrust is arranged on the rocket body according to any one of claims 1 to 8.
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| CN111577483B (en) * | 2020-05-18 | 2021-03-26 | 中国人民解放军国防科技大学 | Multi-pulse solid rocket engine |
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| CN112196692B (en) * | 2020-10-14 | 2021-11-12 | 中国人民解放军国防科技大学 | Electrode combustible thrust continuously adjustable riches fires automatically controlled solid ramjet |
| CN112392629B (en) * | 2021-01-04 | 2021-04-09 | 北京航空航天大学 | Solid-liquid-solid co-combustion chamber combined power rocket engine and aircraft |
| CN114412655B (en) * | 2021-12-21 | 2023-11-14 | 西北工业大学 | Integrated adjustable structure of tail nozzle of combustion chamber of wide-range hypersonic ramjet engine |
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| US7958823B2 (en) * | 2004-12-17 | 2011-06-14 | Sawka Wayne N | Controllable digital solid state cluster thrusters for rocket propulsion and gas generation |
| JP5602106B2 (en) * | 2011-07-14 | 2014-10-08 | 三菱重工業株式会社 | Combustion gas supply control mechanism |
| US8950329B2 (en) * | 2012-12-24 | 2015-02-10 | Raytheon Company | Electrically operated propellants |
| US10563617B2 (en) * | 2016-09-23 | 2020-02-18 | Raytheon Company | Electrically operated propellant for solid rocket motor thrust management |
| CN108488005B (en) * | 2018-02-13 | 2020-02-07 | 重庆大学 | Thrust-controllable multi-pulse solid rocket engine |
| CN108843462B (en) * | 2018-04-28 | 2019-04-02 | 西北工业大学 | It is classified pressurized combustion solid propellant rocket |
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