CN110469426B - Solid rocket engine with continuously adjustable thrust and solid rocket - Google Patents

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

A continuously adjustable thrust solid rocket motor and solid rocket

technical field

The invention relates to the technical field of solid rocket motors, in particular to a solid rocket motor with continuously adjustable thrust and a solid rocket.

Background technique

A solid rocket motor is a rocket motor fueled by solid propellant. It mainly consists of combustion chamber shell, solid propellant charge and nozzle. The outstanding features of solid rocket motors are simple structure, few parts required, and generally no moving parts. The above features make the solid rocket motor highly reliable, easy to maintain and operate. Therefore, solid rocket motors are widely used in various missiles, and the trend of solidification of various tactical and strategic missile power systems is becoming more and more obvious.

For existing solid or liquid rocket engines, direct flow regulation is often used to control engine thrust. For rocket engines that use solid fuel, the existing method of adjusting the flow is usually mechanical adjustment, which has a narrow adjustment range and requires actuating parts, such as a control valve to control the flow, and ultimately change the thrust Effect. For rocket engines using liquid fuel, the flow rate is generally adjusted by the injection pressure drop. This adjustment and its supply method are more complicated, with many parts and components, and the reliability is relatively low.

SUMMARY OF THE INVENTION

Aiming at the problems in the prior art that the fuel flow adjustment range of the solid rocket motor is relatively narrow and requires moving parts, the present invention provides a solid rocket motor with continuously adjustable thrust and a solid rocket, which help to solve the problem of traditional solid rocket motor thrust regulation The scope is narrow, the technical difficulty is high, and the liquid rocket engine supply and regulation system is complex.

In order to achieve the above purpose, the present invention provides a solid rocket motor with continuously adjustable thrust, including a gas generating assembly, a combustion chamber and a tail nozzle that are connected in sequence, and the gas generating assembly includes an oxygen-enriched fuel gas generator and an oxygen-depleted fuel gas generator. device;

The oxygen-enriched gas generator is provided with an oxygen-enriched accommodating cavity capable of accommodating an oxygen-enriched electronically controlled solid propellant, and the oxygen-enriched fuel gas generator is provided with an oxygen-enriched fuel gas that can ablate the oxygen-enriched electrically controlled solid propellant. The oxygen-enriched ablation circuit, the oxygen-enriched accommodation cavity is communicated with the combustion chamber through an oxygen-enriched fuel gas channel;

The oxygen-depleted fuel gas generator is provided with an oxygen-depleted accommodating cavity capable of accommodating the oxygen-depleted electronically controlled solid propellant, and the oxygen-depleted fuel gas generator is provided with an oxygen-depleted fuel gas capable of ablating the oxygen-depleted electronically controlled solid propellant. The oxygen-lean ablation circuit is connected with the combustion chamber through the oxygen-lean gas channel;

The oxygen-enriched fuel gas generator is provided with an oxygen-enriched controller capable of controlling the flow rate of the oxygen-enriched fuel gas, and the oxygen-depleted fuel gas generator is provided with an oxygen-lean controller capable of controlling the flow rate of the oxygen-enriched fuel gas.

Further preferably, the oxygen-depleted ablation circuit includes a first cathode, a first anode, and a first power supply electrically connected to the first cathode and the first anode, respectively, and an ablative device is provided between the first cathode and the first anode. The oxygen-depleted ablation cavity of the oxygen-depleted solid propellant is electronically controlled, and the oxygen-depleted controller is set on the first power supply.

Further preferably, the oxygen-enriched ablation circuit includes a second cathode, a second anode, and a second power supply electrically connected to the second cathode and the second anode, respectively, and an ablative device is provided between the second cathode and the second anode. The oxygen-enriched ablation chamber of the oxygen-enriched electronically controlled solid propellant, the oxygen-enriched controller is set on the second power supply.

Further preferably, the oxygen-depleted fuel gas generator is of a columnar structure, and the oxygen-depleted accommodating cavity is a cylindrical cavity provided inside the oxygen-depleted fuel gas generator;

The oxygen-enriched fuel gas generator is a hollow cylindrical structure sheathed outside the oxygen-depleted fuel gas generator, and the oxygen-enriched accommodating cavity is an annular cylindrical cavity provided inside the oxygen-enriched fuel gas generator.

Further preferably, one of the first cathode and the first anode is an electrode rod, and the other is a ring-shaped electrode plate, the electrode rod is inserted in the axial position of the oxygen-poor electronically controlled solid propellant, and the ring-shaped electrode plate is wrapped in the oxygen-poor electronically controlled solid propellant. the side walls of the solid propellant;

Both the second cathode and the second anode are annular electrode plates, one annular electrode plate is attached to the wall of the inner ring of the oxygen-rich electrically controlled solid propellant, and the other annular electrode plate is attached to the oxygen-enriched electrically controlled solid propellant propellant on the walls of the outer ring.

Further preferably, the oxygen-enriched fuel gas generator has a columnar structure, and the oxygen-enriched accommodating cavity is a cylindrical cavity arranged inside the oxygen-enriched fuel gas generator;

The oxygen-depleted fuel gas generator is a hollow cylindrical structure that is sheathed outside the oxygen-enriched fuel gas generator, and the oxygen-depleted accommodating cavity is an annular cylindrical cavity provided inside the oxygen-depleted fuel gas generator.

Further preferably, one of the second cathode and the second anode is an electrode rod, the other is a ring-shaped electrode plate, the electrode rod is inserted in the axial position of the oxygen-rich electronically controlled solid propellant, and the ring-shaped electrode plate is wrapped in the oxygen-rich electronically controlled solid propellant. the side walls of the solid propellant;

Both the first cathode and the first anode are annular electrode plates, one annular electrode plate is attached to the wall of the inner ring on the oxygen-depleted electric control solid propellant, and the other annular electrode plate is attached to the oxygen depleted electric control solid propellant. propellant on the walls of the outer ring.

Further preferably, the tail nozzle has a flared flared structure, the combustion chamber is connected to the end of the tail nozzle with a smaller diameter, and the end of the combustion chamber connected to the tail nozzle is provided with a closing structure.

In order to achieve the above object, the present invention also provides a solid rocket with continuously adjustable thrust, including a rocket body, and the rocket body is provided with the aforementioned solid rocket motor with continuously adjustable thrust.

The invention discloses a solid rocket motor with continuously adjustable thrust and a solid rocket. Different from the traditional solid rocket motor, the gas generating component in this solution is designed as two independent oxygen-enriched gas generators and oxygen-depleted gas generators. The oxygen-enriched gas generator and the oxygen-depleted gas generator are loaded with oxygen-enriched electronically controlled solid propellant and oxygen-depleted electronically controlled solid propellant, respectively. The oxygen-depleted electronically controlled solid propellant generates fuel flow after gasification, thereby realizing real-time continuous adjustment of engine thrust to meet different flight conditions, broadening the flight envelope of the engine, and helping to solve the thrust adjustment range of traditional solid rocket engines. Narrow, technically difficult problems and complex liquid rocket engine supply and regulation systems.

Description of drawings

In order to explain the embodiments of the present invention or the technical solutions in the prior art more clearly, the following briefly introduces the accompanying drawings that need to be used in the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description are only These are some embodiments of the present invention, and for those of ordinary skill in the art, other drawings can also be obtained according to the structures shown in these drawings without creative efforts.

1 is a front sectional view of a solid rocket motor with continuously adjustable thrust in an embodiment of the present invention;

FIG. 2 is a side sectional view of a solid rocket motor with continuously adjustable thrust in an embodiment of the present invention;

Fig. 3 is the first installation structure diagram of the first cathode, the first anode and the oxygen-depleted electronically controlled solid propellant in the embodiment of the present invention;

Fig. 4 is the first installation structure diagram of the second cathode, the second anode and the oxygen-enriched electronically controlled solid propellant in the embodiment of the present invention;

Fig. 5 is the second installation structure diagram of the second cathode, the second anode and the oxygen-enriched electronically controlled solid propellant in the embodiment of the present invention;

FIG. 6 is a second installation structure diagram of the first cathode, the first anode and the oxygen-depleted electronically controlled solid propellant in the embodiment of the present invention.

Description of reference numerals: 1- oxygen-depleted electronically controlled solid propellant, 2- oxygen-depleted gas generator, 3- oxygen-enriched electronically controlled solid propellant, 4-oxygen-enriched gas generator, 5-combustion chamber, 6-tail spray tube, 7-oxygen-enriched fuel gas channel, 8-oxygen-depleted fuel gas channel, 9-first cathode, 10-first anode, 11-second cathode, 12-second anode,

The realization, functional characteristics and advantages of the present invention will be further described with reference to the accompanying drawings in conjunction with the embodiments.

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relationship between various components under a certain posture (as shown in the accompanying drawings). The relative positional relationship, the movement situation, etc., if the specific posture changes, the directional indication also changes accordingly.

In addition, descriptions such as "first", "second", etc. in the present invention are only for descriptive purposes, and should not be construed as indicating or implying their relative importance or implicitly indicating the number of indicated technical features. Thus, a feature delimited with "first", "second" may expressly or implicitly include at least one of that feature. In the description of the present invention, "plurality" means at least two, such as two, three, etc., unless otherwise expressly and specifically defined.

In the present invention, unless otherwise expressly specified and limited, the terms "connected", "fixed" and the like should be understood in a broad sense, for example, "fixed" may be a fixed connection, a detachable connection, or an integrated; It can be a mechanical connection, an electrical connection, a physical connection or a wireless communication connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal connection of two elements or the interaction between the two elements. unless otherwise expressly qualified. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but must be based on the realization by those of ordinary skill in the art. When the combination of technical solutions is contradictory or cannot be realized, it should be considered that the combination of technical solutions does not exist and is not within the scope of protection claimed by the present invention.

As shown in Figures 1-2, a solid rocket motor with continuously adjustable thrust includes a gas generating assembly, a combustion chamber 5 and a tail nozzle 6 connected in sequence, and the gas generating assembly includes an oxygen-enriched gas generator 4 and a lean gas generator 4. Oxygen gas generator 2.

The oxygen-enriched fuel gas generator 4 is provided with an oxygen-enriched accommodation cavity capable of accommodating the oxygen-enriched electronically controlled solid propellant 3, and the oxygen-enriched fuel gas generator 4 is provided with an oxygen-enriched electric control chamber that is not shown in the figure. The oxygen-enriched ablation circuit of the oxygen-enriched fuel gas generated by the solid propellant 3, the oxygen-enriched accommodation cavity is communicated with the combustion chamber 5 through the oxygen-enriched fuel gas channel 7; wherein, the oxygen-enriched electronically controlled solid propellant 3 is combined and polymerized by the fuel and the oxidant Formation, the content of oxidant in the oxygen-enriched electronically controlled solid propellant 3 is much more than that of the fuel. After the oxygen-enriched ablation circuit is energized, the fuel and the oxidant in the oxygen-enriched electronically controlled solid propellant 3 are burned under the action of ablation. , and then produce oxygen-enriched fuel gas, which then flows into the combustion chamber 5. Since the content of oxidant is much more than that of fuel, most or all of the oxygen-enriched fuel gas is oxidant. The oxygen-enriched electrically controlled solid propellant 3 in this embodiment can be obtained by the preparation method of the electrically controlled solid propellant disclosed in the patent CN106905091A.

The oxygen-depleted fuel gas generator 2 is provided with an oxygen-depleted accommodating chamber capable of accommodating the oxygen-depleted electronically controlled solid propellant 1, and the oxygen-depleted fuel gas generator 2 is provided with a non-illustrated oxygen-depleted electronic control chamber capable of ablating the oxygen-depleted propellant. The oxygen-depleted ablation circuit of the oxygen-depleted fuel gas generated by the solid propellant 1, the oxygen-depleted accommodating cavity is communicated with the combustion chamber 5 through the oxygen-depleted fuel gas channel 8; wherein, the oxygen-depleted electronically controlled solid propellant 1 is combined and polymerized by the fuel and the oxidant Formation, the content of oxidant in the oxygen-depleted electronically controlled solid propellant 1 is much less than that of the fuel. After the oxygen-depleted ablation circuit is energized, the fuel and the oxidant in the oxygen-depleted electronically controlled solid propellant 1 undergo a combustion reaction under the action of ablation. , and then produce oxygen-lean gas, which then flows into the combustion chamber 5. Since the content of oxidant is far less than that of fuel, most or all of the oxygen-lean gas is fuel. The oxygen-depleted electronically controlled solid propellant 1 in this embodiment can be obtained by the preparation method of the electronically controlled solid propellant disclosed in patent CN106905091A.

The oxygen-enriched fuel gas generator 4 is provided with an oxygen-enriched controller that can control the flow of oxygen-enriched fuel gas and is not shown, and the oxygen-depleted fuel gas generator 2 is provided with an oxygen-enriched fuel gas flow rate that can control the oxygen-enriched fuel gas flow and is not shown. the oxygen lean controller. Through two independent oxygen-enriched gas generators 4 and oxygen-lean gas generators 2, oxygen-enriched gas generators 4 and oxygen-lean gas generators 2 are loaded with oxygen-enriched electronically controlled solid propellants 3 and oxygen-depleted electronically controlled solid propellants, respectively. 1. The fuel flow on the oxygen-enriched electronically controlled solid propellant 3 and the oxygen-depleted electronically controlled solid propellant 1 is adjusted in real time through the oxygen-enriched controller and the oxygen-depleted controller, so as to realize the real-time continuous adjustment of the engine thrust to meet different requirements. The flight conditions and the widening of the flight envelope of the engine are helpful to solve the problems of narrow thrust adjustment range and high technical difficulty of traditional solid rocket engines and the complex problems of liquid rocket engine supply and adjustment systems.

The voltage on the oxygen-enriched ablation circuit and the oxygen-depleted ablation circuit is adjusted by the oxygen-enriched controller and the oxygen-lean controller, so as to adjust the ablation reaction on the oxygen-enriched electronically controlled solid propellant 3 and the oxygen-depleted electrically controlled solid propellant 1. Reaction rate, and then achieve the effect of adjusting the flow rate of oxygen-enriched gas and oxygen-lean gas. On the premise of maintaining the equivalence ratio of oxygen-enriched gas and oxygen-lean gas to 1, changing the flow supply of oxygen-lean gas and oxygen-enriched gas at the same time can realize the engine Real-time continuous adjustment of thrust to meet different flight conditions and broaden the flight envelope of the engine.

Preferably, the oxygen-depleted fuel gas generator 2 has a columnar structure, and the oxygen-depleted accommodating cavity is a cylindrical cavity provided inside the oxygen-depleted fuel gas generator 2; The hollow cylindrical structure outside the gas generator 2, the oxygen-enriched accommodation cavity is an annular cylindrical cavity arranged inside the oxygen-enriched gas generator 4, under this structure, the oxygen-depleted electronically controlled solid propellant 1 is a columnar structure , the oxygen-enriched electronically controlled solid propellant 3 has a hollow columnar structure, which is the structure shown in this embodiment.

At this time, the oxygen-depleted ablation circuit includes a first power supply, a first cathode 9 and a first anode 10 that are electrically connected, and the oxygen-depleted controller is set on the first power supply, because the power supply in the prior art itself has the ability to adjust the output voltage Therefore, the oxygen lean controller in this embodiment is integrated on the first power supply, which will not be repeated here. One of the first cathode 9 and the first anode 10 is an electrode rod, and the other is a ring-shaped electrode plate. The electrode rod is inserted in the axial position of the oxygen-depleted electronically controlled solid propellant 1, and the annular electrode plate is wrapped in the oxygen-depleted electronically controlled solid propellant 1. The side wall of the propellant 1 is shown in FIG. 3; an ablation cavity is formed between the first cathode 9 and the first anode 10, and then the oxygen-depleted electrically controlled solid propellant 1 of the cylindrical structure is ablated, resulting in a depleted Oxygen fuel gas; the oxygen-enriched ablation circuit includes a second power supply, a second cathode 11 and a second anode 12 of the electrical connection, and the oxygen-enriched controller is set on the second power supply, because the power supply in the prior art itself has the ability to adjust the output voltage Therefore, the oxygen enrichment controller in this embodiment is integrated on the second power supply, which will not be repeated here. Both the second cathode 11 and the second anode 12 are annular electrode plates, one annular electrode plate is attached to the wall of the inner ring on the oxygen-enriched electronically controlled solid propellant 3, and the other annular electrode plate is attached to the oxygen-enriched solid propellant 3 On the wall of the outer ring on the electrically controlled solid propellant 3, as shown in Figure 4; an ablation cavity is formed between the second cathode 11 and the second anode 12, and then the oxygen-rich electrically controlled solid propellant of the hollow cylindrical structure is formed. 3 Perform ablation to produce oxygen-enriched gas.

or:

The oxygen-enriched fuel gas generator 4 is a columnar structure, and the oxygen-enriched accommodating cavity is a cylindrical cavity arranged inside the oxygen-enriched fuel gas generator 4; 4 outside the hollow columnar structure, the oxygen-depleted accommodating cavity is an annular columnar cavity arranged inside the oxygen-depleted fuel gas generator 2, under this structure, the oxygen-enriched electronically controlled solid propellant 3 The electronically controlled solid propellant 1 has a hollow cylindrical structure.

At this time, the oxygen-enriched ablation circuit includes a second power supply, a second cathode 11 and a second anode 12 that are electrically connected, and the oxygen-enriched controller is set on the second power supply, because the power supply in the prior art itself has the ability to adjust the output voltage Therefore, the oxygen enrichment controller in this embodiment is integrated on the second power supply, which will not be repeated here. One of the second cathode 11 and the second anode 12 is an electrode rod, and the other is a ring-shaped electrode plate. The electrode rod is inserted in the axial position of the oxygen-enriched electrically controlled solid propellant 3, and the annular electrode plate is wrapped in the oxygen-enriched electrically controlled solid propellant 3. The side wall of the propellant 3 is shown in FIG. 5 ; an ablation cavity is formed between the second cathode 11 and the second anode 12 , and then the oxygen-enriched electrically controlled solid propellant 3 in the columnar structure is ablated to produce an ablation chamber. Oxygen fuel gas; the oxygen-depleted ablation circuit includes the first power supply, the first cathode 9 and the first anode 10 of the electrical connection, and the oxygen-depleted controller is set on the first power supply, because the power supply in the prior art itself has the ability to adjust the output voltage Therefore, the oxygen lean controller in this embodiment is integrated on the first power supply, which will not be repeated here. 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 on the oxygen-depleted electrically controlled solid propellant 1, and the other annular electrode plate is attached to the oxygen-depleted solid propellant 1. On the wall of the outer ring of the electronically controlled solid propellant 1, as shown in Figure 6; an ablation cavity is formed between the first cathode 9 and the first anode 10, and the oxygen-depleted electronically controlled solid propellant of the hollow cylindrical structure is formed. 1 Perform ablation to produce oxygen-depleted fuel gas.

Further preferably, the tail nozzle 6 is a flared flare structure, the combustion chamber 5 is connected to the end of the tail nozzle 6 with a smaller diameter, and the combustion chamber 5 is connected to the end of the tail nozzle 6. It is equipped with a closing structure, and the structure of first closing and then flaring is adopted, which makes the thrust effect generated by gas combustion more significant.

The coaxially installed structure of the oxygen-depleted gas generator 2 and the oxygen-enriched gas generator 4 can fully improve the volume utilization rate of the charging space inside the engine, carry more propellants, and increase the range of the rocket. Of course, the oxygen-depleted gas generator 2 and the oxygen-enriched gas generator 4 do not have to be installed coaxially, and can be installed at a reasonable position according to the overall flight layout. Even if the oxygen-depleted fuel gas generator 2 and the oxygen-enriched fuel gas generator 4 are installed separately, they can enter the supplementary combustion chamber through two fuel gas inlets.

The specific working process of the solid rocket motor with continuously adjustable thrust in this embodiment is:

First, the relationship between the burning rate and the voltage of the oxygen-depleted electronically controlled solid propellant 1 can be obtained through multiple experiments:

r ₁ =f(u ₁ )

In the formula, r ₁ is the burning rate of the oxygen-depleted electronically controlled solid propellant 1, and u ₁ is the voltage of the oxygen-depleted ablation circuit;

随电压的变化关系式如下：The density ρ ₁ of the oxygen-depleted electrically controlled solid propellant 1 can be obtained by measuring, and the combustion surface area A _{1 of the oxygen-depleted electrically controlled solid propellant 1 can be obtained by measuring the grain cross-sectional area of the oxygen-depleted electrically controlled solid propellant 1} . Therefore, the mass flow rate of the oxygen-depleted electronically controlled solid propellant 1

The relationship with voltage is as follows:

Secondly, the relationship between the burning rate and the voltage of the oxygen-enriched electronically controlled solid propellant 3 can be obtained through multiple tests:

r ₂ =g(u ₂ )

In the formula, r ₂ is the burning rate of the oxygen-enriched electronically controlled solid propellant 3, and u ₂ is the voltage of the oxygen-enriched ablation circuit;

随电压的变化关系式如下：The density ρ ₂ of the oxygen-enriched electrically controlled solid propellant 3 can be obtained by measuring, and the burning surface area A ₂ of the oxygen-enriched electrically controlled solid propellant 3 can be obtained by measuring the grain cross-sectional area of the oxygen-enriched electrically controlled solid propellant 3 . Therefore, the mass flow rate of the oxygen-enriched electronically controlled solid propellant 3

The relationship with voltage is as follows:

When the solid rocket motor is working, the equivalence ratio should be such that, given the engine structural parameters and grain formula, the flow rates of the oxygen-depleted gas generator 2 and the oxygen-enriched gas generator 4 are only affected by the oxygen-lean ablation circuit and the oxygen-enriched combustion. Corrosion circuit voltage effects. Therefore, the engine equivalence ratio can be made 1 by directly adjusting the voltages of the oxygen-lean ablation circuit and the oxygen-rich ablation circuit. When the engine starts to work, the oxygen-lean gas generator 2 and the oxygen-enriched gas generator 4 are ignited at the same time, and the oxygen-lean gas and the rich gas enter the rocket combustion chamber 5 for mixing and combustion. The expanded tail nozzle 6 is accelerated and discharged to generate thrust.

The above descriptions are only the preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Under the inventive concept of the present invention, the equivalent structural transformations made by the contents of the description and drawings of the present invention, or the direct/indirect application Other related technical fields are included in the scope of patent protection of the present invention.

Claims (9)

1. a solid rocket motor with continuously adjustable thrust, comprising a fuel gas generating assembly, a combustion chamber and a tail nozzle that are connected successively, it is characterized in that, the fuel gas generating assembly comprises an oxygen-enriched fuel gas generator and an oxygen-depleted fuel gas generator; The oxygen-enriched gas generator is provided with an oxygen-enriched accommodating cavity capable of accommodating an oxygen-enriched electronically controlled solid propellant, and the oxygen-enriched fuel gas generator is provided with an oxygen-enriched fuel gas that can ablate the oxygen-enriched electrically controlled solid propellant. The oxygen-enriched ablation circuit, the oxygen-enriched accommodation cavity is communicated with the combustion chamber through an oxygen-enriched fuel gas channel; The oxygen-depleted fuel gas generator is provided with an oxygen-depleted accommodating cavity capable of accommodating the oxygen-depleted electronically controlled solid propellant, and the oxygen-depleted fuel gas generator is provided with an oxygen-depleted fuel gas capable of ablating the oxygen-depleted electronically controlled solid propellant. The oxygen-lean ablation circuit is connected with the combustion chamber through the oxygen-lean gas channel; The oxygen-enriched fuel gas generator is provided with an oxygen-enriched controller capable of controlling the flow rate of the oxygen-enriched fuel gas, and the oxygen-depleted fuel gas generator is provided with an oxygen-lean controller capable of controlling the flow rate of the oxygen-enriched fuel gas. 2 . The solid rocket motor with continuously adjustable thrust according to claim 1 , wherein the oxygen-depleted ablation circuit comprises a first cathode, a first anode, and a first cathode and a first anode electrically connected to the first cathode and the first anode respectively. 3 . A power source, an oxygen-depleted ablation chamber capable of ablating the oxygen-depleted electronically controlled solid propellant is arranged between the first cathode and the first anode, and the oxygen-depleted controller is arranged on the first power source. 3. The solid rocket motor with continuously adjustable thrust according to claim 2, wherein the oxygen-enriched ablation circuit comprises a second cathode, a second anode, and a second cathode and a second anode electrically connected to the second cathode and the second anode respectively. Two power sources, an oxygen-enriched ablation chamber capable of ablating the oxygen-enriched electronically controlled solid propellant is arranged between the second cathode and the second anode, and the oxygen-enriched controller is arranged on the second power source. 4. The solid rocket motor with continuously adjustable thrust according to claim 3, wherein the oxygen-depleted fuel gas generator is a columnar structure, and the oxygen-depleted accommodating cavity is a columnar structure arranged inside the oxygen-depleted fuel gas generator. cavity; The oxygen-enriched fuel gas generator is a hollow cylindrical structure sheathed outside the oxygen-depleted fuel gas generator, and the oxygen-enriched accommodating cavity is an annular cylindrical cavity provided inside the oxygen-enriched fuel gas generator. 5. The solid rocket motor with continuously adjustable thrust according to claim 4 is characterized in that, one of the first cathode and the first anode is an electrode rod, and the other is an annular electrode plate, and the electrode rod is inserted into the oxygen-depleted battery. The axial position of the solid propellant is controlled, and the annular electrode plate is wrapped around the side wall of the oxygen-depleted electronically controlled solid propellant; Both the second cathode and the second anode are annular electrode plates, one annular electrode plate is attached to the wall of the inner ring of the oxygen-rich electrically controlled solid propellant, and the other annular electrode plate is attached to the oxygen-enriched electrically controlled solid propellant propellant on the walls of the outer ring. 6. The solid rocket motor with continuously adjustable thrust according to claim 3, wherein the oxygen-enriched fuel gas generator is a columnar structure, and the oxygen-enriched accommodating cavity is a columnar structure arranged inside the oxygen-enriched fuel gas generator. cavity; The oxygen-depleted fuel gas generator is a hollow cylindrical structure that is sheathed outside the oxygen-enriched fuel gas generator, and the oxygen-depleted accommodating cavity is an annular cylindrical cavity provided inside the oxygen-depleted fuel gas generator. 7. The solid rocket motor with continuously adjustable thrust according to claim 6 is characterized in that, one of the second cathode and the second anode is an electrode rod, and the other is an annular electrode plate, and the electrode rod is inserted into the oxygen-enriched battery. The axial position of the solid propellant is controlled, and the annular electrode plate is wrapped around the side wall of the oxygen-enriched electronically controlled solid propellant; Both the first cathode and the first anode are annular electrode plates, one annular electrode plate is attached to the wall of the inner ring on the oxygen-depleted electric control solid propellant, and the other annular electrode plate is attached to the oxygen depleted electric control solid propellant. propellant on the walls of the outer ring. 8. The solid rocket motor with continuously adjustable thrust according to claim 1, 2 or 3, wherein the tail nozzle is a flared flared structure, and the upper diameter of the combustion chamber and the tail nozzle is smaller One end of the combustion chamber connected to the tail nozzle is provided with a closing structure. 9. A solid rocket with continuously adjustable thrust, comprising a rocket body, wherein the rocket body is provided with the continuously adjustable solid rocket motor according to any one of claims 1 to 8.

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