Combustible spoiler-based dual-thrust solid-liquid rocket engine system and working method

Abstract

The application belongs to the technical field of rocket engines, and discloses a double-thrust solid-liquid rocket engine system based on a combustible spoiler and a working method thereof, which comprises the following steps: a front propellant column, a four-fan-hole combustible spoiler and a rear propellant column are sequentially arranged in a combustion chamber shell; a chemical bed component is used for decomposing injected oxidants; the four-fan-hole combustible spoiler, the front propellant column and the rear propellant column are combusted under the action of high-temperature and high-pressure gas generated by the decomposition of the oxidants; the four-fan-hole combustible spoiler arranged in a combustion chamber passage of the engine can change the original flame layer structure, so that the oxidant flow and the pyrolysis products of the fuel can be fully mixed and reacted, and the combustion efficiency of the engine can be improved. The four-fan-hole combustible spoiler simultaneously strengthens the turbulent effect, so that the burning rate of the rear fuel can be several times higher than that of the front fuel. The application has a simple structure and is easy to implement.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of rocket engine, and relates to a double-thrust solid-liquid rocket engine system based on combustible spoiler and a working method. BACKGROUND

[0002] The propellant of a typical solid-liquid rocket engine is composed of solid fuel and liquid oxidizer. The solid-liquid rocket engine has some obvious advantages over the solid rocket engine, such as wide-range thrust regulation, multiple start-on-demand, higher specific impulse, long-time work and better safety, etc. Compared with the liquid rocket engine, the solid-liquid rocket engine has a simpler structure and a higher density specific impulse. At present, the solid-liquid rocket engine is applied in the fields of sounding rockets, target projectiles and commercial spaceflight, and has a broad prospect; however, the double-thrust solid-liquid rocket engine has two significant problems that limit its development.

[0003] Firstly, the solid-liquid rocket engine can realize two-stage thrust by adjusting the oxidizer flow, but this thrust regulation mode will bring the negative effect that the engine is easy to deviate from the optimal oxygen-fuel ratio because the fuel flow is controlled by the oxidizer flow and the relationship is not linear. The oxygen-fuel ratio is a crucial design parameter for the rocket engine and greatly affects the performance of the engine. The deviation of the optimal oxygen-fuel ratio during the working process of the solid-liquid rocket engine will bring significant performance degradation, mainly manifested as a decrease in specific impulse, which means that more propellant needs to be consumed to generate the same thrust, which is not conducive to the advantages of the solid-liquid rocket engine in variable thrust and high specific impulse, and greatly restricts its development. Secondly, the oxidizer of the solid-liquid rocket engine is difficult to fully mix with the pyrolysis fuel, and this non-premixed combustion mode makes the combustion efficiency of the solid-liquid rocket engine low. The addition of a spoiler structure in the combustion chamber improves the combustion efficiency after the gas is mixed by the spoiler. However, the introduction of the spoiler and the additional installation structure increases the complexity and reduces the engine packing coefficient, and does not solve the problem of deviation from the optimal oxygen-fuel ratio during the variable thrust process. SUMMARY

[0004] The present application aims to solve the problems in the prior art that the two-stage of the double-thrust solid-liquid rocket engine is difficult to work near the optimal oxygen-fuel ratio, and the oxidizer of the solid-liquid rocket engine is difficult to fully mix with the pyrolysis fuel, and provides a double-thrust solid-liquid rocket engine system based on combustible spoiler and a working method.

[0005] To achieve the above-mentioned purpose, the present application adopts the following technical solutions:

[0006] The double-thrust solid-liquid rocket engine system based on combustible spoiler comprises a combustion chamber component, a catalytic bed component, a pre-chamber component, a post-chamber component and a post-head component.

[0007] The combustion chamber component comprises four fan-shaped hole combustible spoiler, front section grain, rear section grain and combustion chamber shell, the four fan-shaped hole combustible spoiler is arranged between the front section grain and the rear section grain, the four fan-shaped hole combustible spoiler, the front section grain and the rear section grain are arranged inside the combustion chamber shell, the front combustion chamber component and the rear combustion chamber component are arranged at two ends of the combustion chamber shell respectively, the catalytic bed component is arranged at one end of the front combustion chamber component, the rear head component is arranged at one end of the rear combustion chamber component, the rear combustion chamber component is provided with a nozzle, and the nozzle passes through the rear head component, the catalytic bed component is used for decomposing the injected oxidant, under the action of high-temperature and high-pressure gas generated by the decomposition of the oxidant, the four fan-shaped hole combustible spoiler, the front section grain and the rear section grain are combusted, the nozzle converts the heat energy of the high-temperature combustion gas into kinetic energy through expansion, and thrust is generated by the recoil effect.

[0008] Further improvement of the present application is that:

[0009] Further, the catalytic bed component comprises catalytic bed head cover plate, catalytic bed shell and catalytic bed adapter flange, the catalytic bed head cover plate is connected with the catalytic bed shell through bolts, and the catalytic bed shell and the catalytic bed adapter flange are connected through bolts, and the catalytic bed adapter flange is arranged on the front combustion chamber component.

[0010] Further, the front combustion chamber component comprises front combustion chamber heat insulation layer and front combustion chamber shell, the front combustion chamber heat insulation layer is arranged inside the front combustion chamber shell, the outer side of the combustion chamber shell is provided with a first combustion chamber flange, and the catalytic bed adapter flange, the front combustion chamber shell and the first combustion chamber flange are sequentially fixedly connected through bolts.

[0011] Further, the rear combustion chamber component comprises rear combustion chamber heat insulation layer and rear combustion chamber shell, the rear combustion chamber heat insulation layer is arranged inside the rear combustion chamber shell, the rear head component comprises rear head shell and rear head heat insulation layer, the rear head heat insulation layer is arranged inside the rear head shell, the rear head shell is arranged on the rear combustion chamber shell, the outer side of the combustion chamber shell is provided with a second combustion chamber flange, and the second combustion chamber flange, the rear combustion chamber shell and the rear head shell are connected through bolts.

[0012] Further, the rear combustion chamber component is provided with a nozzle, and the nozzle passes through the rear head component, specifically, one end of the rear head shell is provided with a nozzle pressing plate, the nozzle pressing plate fixes the nozzle, one end of the nozzle communicates with the space composed of the rear combustion chamber shell and the rear head shell, and the other end communicates with the external space.

[0013] Further, the four-fan-hole combustible spoiler, the front section grain and the rear section grain and the combustion chamber shell need to be evenly coated with heat insulation and fire retardant putty to prevent high-temperature combustion gas from leaking out through the gaps between the four-fan-hole combustible spoiler, the front section grain and the rear section grain and the combustion chamber shell.

[0014] Further, the catalytic bed component further comprises a molybdenum-based silver mesh catalytic bed; the molybdenum-based silver mesh catalytic bed decomposes the oxidizing agent injected into the front combustion chamber component to generate high-temperature oxygen and water vapor; the four-fan-hole combustible spoiler, the front section grain and the rear section grain are pyrolyzed and combusted by the high-temperature oxygen and water vapor, and the four-fan-hole combustible spoiler changes from a four-fan-hole state to a single circular hole state after combustion.

[0015] The working method of the double-thrust solid-liquid rocket engine system based on the combustible spoiler comprises the following steps: injecting an oxidizing agent into the front combustion chamber component; the oxidizing agent is decomposed under the action of the molybdenum-based silver mesh catalytic bed to generate high-temperature oxygen and water vapor; the four-fan-hole combustible spoiler, the front section grain and the rear section grain are pyrolyzed and combusted by the high-temperature oxygen and water vapor, and the four-fan-hole combustible spoiler changes from a four-fan-hole state to a single circular hole state after combustion; after the four-fan-hole combustible spoiler changes to a single circular hole state, the flow of the oxidizing agent injected into the front combustion chamber component is adjusted to make the engine always work near the optimal oxygen-fuel ratio; the nozzle converts the heat energy of the high-temperature combustion gas into kinetic energy through expansion, and generates thrust through recoil.

[0016] Compared with the prior art, the present application has the following beneficial effects:

[0017] The present application sequentially sets the front section grain, the four-fan-hole combustible spoiler and the rear section grain inside the combustion chamber shell; the catalytic bed component is used to decompose the injected oxidizing agent, and the four-fan-hole combustible spoiler, the front section grain and the rear section grain are combusted under the action of the high-temperature and high-pressure gas generated by the decomposition of the oxidizing agent; the four-fan-hole combustible spoiler arranged in the engine combustion chamber passage can change the original flame layer structure, so that the oxidizing agent flow and the pyrolysis products of the fuel can be fully mixed and reacted, and the engine combustion efficiency can be improved. The four-fan-hole combustible spoiler also strengthens the turbulent effect, so that the burning rate of the rear section fuel can be several times higher than that of the front section. The present application has a simple structure and is easy to implement. BRIEF DESCRIPTION OF DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly introduced as follows. It should be understood that the following drawings only show some of the embodiments of the present application, and therefore should not be regarded as a limitation on the scope, and for those of ordinary skill in the art, other related drawings can also be obtained without creative labor on the basis of these drawings.

[0019] Figure 1 Structure diagram of the double-thrust solid-liquid rocket engine system based on the combustible spoiler of the present application;

[0020] Figure 2 Cross-sectional view of the four-petal combustible spoiler;

[0021] Figure 3 (a) is a state diagram of the four-petal combustible spoiler when combustion is not performed;

[0022] Figure 3 (b) is a state diagram of the four-petal combustible spoiler when combustion is performed;

[0023] Figure 3 (c) is a state diagram of the four-petal combustible spoiler after combustion;

[0024] Figure 4 Data diagram of the thrust and flow during the thermal test process of the double-thrust solid-liquid rocket engine based on the combustible spoiler;

[0025] Figure 5 (a) is a curve diagram of the oxygen-fuel ratio of the engine in the first stage;

[0026] Figure 5 (b) is a diagram showing the relationship between the oxygen-fuel ratio and the vacuum impulse ratio of the engine in the second stage.

[0027] Wherein, 1 is the four-petal combustible spoiler, 2 is the front grain, 3 is the rear grain, 4 is the catalytic bed head cover plate, 5 is the catalytic bed shell, 6 is the molybdenum-based silver mesh catalytic bed, 7 is the catalytic bed adapter flange, 8 is the front combustion chamber insulation layer, 9 is the front combustion chamber shell, 10 is the first combustion chamber flange, 11 is the second combustion chamber flange, 12 is the rear combustion chamber insulation layer, 13 is the rear combustion chamber shell, 14 is the rear head shell, 15 is the rear head insulation layer, 16 is the combustion chamber shell, 17 is the nozzle, and 18 is the nozzle pressure plate. DETAILED DESCRIPTION

[0028] In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the following will clearly and completely describe the technical solutions in the embodiments of the present application with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some but not all of the embodiments of the present application. The components of the embodiments of the present application described and shown in the drawings can be arranged and designed in various different configurations.

[0029] Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the claimed application, but only represents selected embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative work are within the scope of protection of the present application.

[0030] It should be noted that: similar reference numbers and letters represent similar items in the following drawings, therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.

[0031] In the description of the embodiments of the present application, it should be noted that, if the orientation or position relationship indicated by the terms "upper", "lower", "horizontal", "inner" and the like is based on the orientation or position relationship shown in the drawings, or is the orientation or position relationship when the product of the present application is usually placed, which is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the indicated device or element must have a particular orientation, be constructed and operated in a particular orientation, therefore, it cannot be understood as a limitation on the present application. In addition, the terms "first", "second" and the like are only used for differentiation in description, and cannot be understood as indicating or implying relative importance.

[0032] In addition, if the term "horizontal" appears, it does not mean that the component must be absolutely horizontal, but can be slightly inclined. For example, "horizontal" only means that its direction is relatively more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly inclined.

[0033] In the description of the embodiments of the present application, it should also be noted that, unless otherwise explicitly specified and limited, if the terms "arrangement", "installation", "connection", "connection" appear, they should be understood in a broad sense, for example, can be fixedly connected, can be detachably connected, or integrally connected; can be mechanically connected, can be electrically connected; can be directly connected, can be indirectly connected through an intermediate medium, can be the communication inside two elements. For those of ordinary skill in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0034] The present application will be described in further detail below with reference to the drawings:

[0035] Referring toFigure 1 The application discloses a double-thrust solid-liquid rocket engine system based on a combustible spoiler, which comprises a combustion chamber component, a catalytic bed component, a front combustion chamber component, a rear combustion chamber component and a rear head component.

[0036] Referring to Figure 2 The combustion chamber component comprises four-fan-hole combustible spoilers 1, a front section propellant column 2, a rear section propellant column 3 and a combustion chamber shell 16; the four-fan-hole combustible spoilers 1 are arranged between the front section propellant column 2 and the rear section propellant column 3; the four-fan-hole combustible spoilers 1, the front section propellant column 2 and the rear section propellant column 3 are arranged inside the combustion chamber shell 16; the front section propellant column 2 is located upstream of the spoilers and is tightly attached to the front end surface of the four-fan-hole combustible spoilers 1, and the burning rate of the front section propellant column 2 is hardly affected by the four-fan-hole combustible spoilers 1; the rear section propellant column 3 is located downstream of the spoilers and is tightly attached to the rear end surface of the four-fan-hole combustible spoilers 1, and the burning rate of the rear section propellant column 3 is increased due to the strong spoiler effect. The front combustion chamber component and the rear combustion chamber component are arranged at two ends of the combustion chamber shell 16 respectively; the catalytic bed component is arranged at one end of the front combustion chamber component; the rear head component is arranged at one end of the rear combustion chamber component; a nozzle 17 is arranged on the rear combustion chamber component and penetrates through the rear head component; the catalytic bed component is used for decomposing the injected oxidant, and the four-fan-hole combustible spoilers 1, the front section propellant column 2 and the rear section propellant column 3 are combusted under the action of the high-temperature and high-pressure gas generated by the decomposition of the oxidant; the nozzle 17 converts the heat energy of the high-temperature combustion gas into kinetic energy through the expansion effect, and generates thrust through the recoil effect. The front combustion chamber and the rear combustion chamber can make the mixing between the oxidant and the pyrolysis fuel more uniform and increase the gas residence time, so as to improve the combustion efficiency of the solid-liquid rocket engine. The four-fan-hole combustible spoilers 1, the tubular front section propellant column 2 and the tubular rear section propellant column 3 are all made of high-density polyethylene (HDPE) material, and the three components together form the solid fuel.

[0037] The four-fan-hole combustible spoilers 1 arranged in the engine combustion chamber channel change the original flame layer structure, so that the oxidant flow and the pyrolysis product of the fuel can be fully mixed and reacted, and the combustion efficiency of the engine is improved. The four-fan-hole combustible spoilers 1 simultaneously strengthen the turbulent effect, so that the burning rate of the rear section fuel can be several times higher than that of the front section. Compared with the single-round-hole combustible spoiler, the four-fan-hole combustible spoiler can make the burning rate of the rear section propellant column higher, and the fan-hole form can ensure that there is less residual propellant in the late combustion stage of the spoiler, so as to prevent the spoiler from being blown off and causing danger.

[0038] The catalytic bed component comprises a catalytic bed head cover plate 4, a catalytic bed shell 5 and a catalytic bed adapter flange 7; the catalytic bed head cover plate 4 is connected with the catalytic bed shell 5 through bolts; the catalytic bed shell 5 and the catalytic bed adapter flange 7 are connected through bolts; the catalytic bed adapter flange 7 is arranged on the front combustion chamber component. The front combustion chamber component comprises a front combustion chamber insulation layer 8 and a front combustion chamber shell 9; the front combustion chamber insulation layer 8 is arranged inside the front combustion chamber shell 9; the combustion chamber shell 16 is provided with a first combustion chamber flange 10 outside; the catalytic bed adapter flange 7, the front combustion chamber shell 9 and the first combustion chamber flange 10 are sequentially fixedly connected through bolts.

[0039] The rear combustion chamber component comprises a rear combustion chamber insulation layer 12 and a rear combustion chamber shell 13; the rear combustion chamber insulation layer 12 is arranged inside the rear combustion chamber shell 13; the rear head component comprises a rear head shell 14 and a rear head insulation layer 15; the rear head insulation layer 15 is arranged inside the rear head shell 14; the rear head shell 14 is arranged on the rear combustion chamber shell 13; the combustion chamber shell 16 is provided with a second combustion chamber flange 11 outside; the second combustion chamber flange 11, the rear combustion chamber shell 13 and the rear head shell 14 are connected through bolts.

[0040] The rear combustion chamber component is provided with a nozzle 17, and the nozzle 17 penetrates through the rear head component; specifically, one end of the rear head shell 14 is provided with a nozzle pressing plate 18; the nozzle pressing plate 18 fixes the nozzle 17; one end of the nozzle 17 communicates with the space composed of the rear combustion chamber shell 13 and the rear head shell 14; the other end communicates with the outside space.

[0041] The four-fan-hole combustible spoiler 1, the front section grain 2 and the rear section grain 3 and the combustion chamber shell 16 need to be evenly coated with heat insulation and fire retardant putty to prevent high-temperature combustion gas from leaking out through the gaps between the four-fan-hole combustible spoiler 1, the front section grain 2 and the rear section grain 3 and the combustion chamber shell 16. The four-fan-hole combustible spoiler 1 is evenly distributed around the center of a circle with four fans at equal intervals.

[0042] The catalytic bed component further comprises a molybdenum-based silver mesh catalytic bed 6; the molybdenum-based silver mesh catalytic bed 6 decomposes the oxidizing agent injected into the front combustion chamber component to generate high-temperature oxygen and water vapor; the high-temperature oxygen and water vapor make the four-fan-hole combustible spoiler 1, the front section grain 2 and the rear section grain 3 pyrolyze and burn; after burning, the four-fan-hole combustible spoiler 1 changes from a four-fan-hole state to a single-circle-hole state, as shown in Figure 3 (a), Figure 3 (b) and Figure 3 (c).

[0043] The working method of the double-thrust solid-liquid rocket engine system based on the combustible spoiler comprises the following steps: injecting an oxidizer into a forward combustion chamber component, decomposing the oxidizer under the action of a molybdenum-based silver mesh catalytic bed 6 to generate high-temperature oxygen and water vapor, pyrolyzing and burning the four-fan-hole combustible spoiler 1, the front section propellant column 2 and the rear section propellant column 3 through the high-temperature oxygen and water vapor, wherein the four-fan-hole combustible spoiler 1 changes from a four-fan-hole state to a single-hole state after burning, adjusting the flow of the oxidizer injected into the forward combustion chamber component to make the engine always work near the optimal oxygen-fuel ratio, and the nozzle 17 converts the heat energy of the high-temperature combustion gas into kinetic energy through expansion and generates thrust through recoil.

[0044] The engine uses high-concentration 95% hydrogen peroxide as an oxidizer, and the hydrogen peroxide is decomposed into high-temperature oxygen and water vapor after passing through the catalytic bed, so that the solid HDPE fuel is pyrolyzed and burned. Figure 4 The data of the thrust and flow of the double-thrust solid-liquid rocket engine with a combustible spoiler in the thermal test process are shown. Figure 4 In the experiment, 5s, 10s and 15s are pulsed to preheat and activate the catalytic bed, the formal ignition is at 20.2s, the oxidizer flow is set to 180g / s, the work is 6.6s, 40g / s, and the work is 13.4s, and the results show that the error between the prediction and the test results is within an acceptable range. Figure 5 The oxygen-fuel ratio in the two-stage working process of the engine is maintained near the optimal oxygen-fuel ratio, which guarantees the high specific impulse performance of the engine.

[0045] The oxidizer flow injected into the forward combustion chamber component is adjusted to make the engine always work near the optimal oxygen-fuel ratio, and the specific is:

[0046] The numerical simulation of the flow field in the solid-liquid rocket engine is carried out, and the burning rate formula of each combustion surface is obtained and the specific impulse efficiency of the engine

[0047] The internal ballistic calculation of the engine is carried out by the burning rate formula and the specific impulse efficiency, the zero-dimensional internal ballistic assumption, the instantaneous equilibrium pressure method and the parallel layer combustion theorem are adopted, the combustion chamber pressure and the thrust change curve with time in the working process of the engine are obtained, and then the optimal oxygen-fuel ratio is obtained.

[0048] wherein, is the burning rate of the combustion surface, a and n are constants related only to the oxidizer, G o is the flow rate of the oxidizer, and the calculation method is the oxidizer flow to the corresponding passage area A o ratio

[0049]

[0050] In the first stage, the four-petal-hole combustible trip plate 1, the front section grain 2 and the rear section grain 3 are pyrolyzed and combusted, and the four-petal-hole combustible trip plate 1 is in the four-petal-hole state; the specific impulse efficiency of the engine is 95%. In the second stage, the four-petal-hole combustible trip plate 1, the front section grain 2 and the rear section grain 3 continue to be combusted, and the four-petal-hole combustible trip plate 1 is in the single circular hole state; the specific impulse efficiency of the engine is 85%. The specific impulse efficiency of the engine is given by the experimental value.

[0051] In the case of ignoring the combustion of the front and rear end surfaces of the grain, the burning rate formula is shown in Table 1.

[0052] Table 1

[0053]

[0054] In the second stage, the four-petal-hole combustible trip plate 1, the front section grain 2 and the rear section grain 3 continue to be combusted, and the four-petal-hole combustible trip plate 1 is in the single circular hole state; the specific impulse efficiency of the engine is 85%.

[0055] Table 2

[0056]

[0057] The engine interior trajectory is calculated by the burning rate formula and the specific impulse efficiency, the zero-dimensional interior trajectory assumption, the instantaneous equilibrium pressure method and the parallel layer combustion theorem. The engine interior trajectory calculation technology is currently mature, and is not described in detail. The interior trajectory calculation is to ultimately obtain the pressure and thrust curves of the combustion chamber in the engine working process, i.e. the pc-t and F-t curves, and also to obtain other key parameters, such as the fuel flow, the engine oxygen-fuel ratio O / F, etc. In the present example, by adjusting the oxidizer flow of the two-stage engine, the final oxidizer flow is 180 g / s for working 6.6 s and 40 g / s for working 13.4 s, as shown in (a) and (b), the engine works in the vicinity of the optimal oxygen-fuel ratio 6.7 throughout the whole process. Figure 5 Figure 5

[0058] The above is only a preferred embodiment of the present application, and is not used to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.​​

Claims

1. A dual-thrust solid-liquid hybrid rocket engine system based on combustible spoiler, characterized by, Comprise: combustion chamber components, catalytic bed components, pre-chamber components, post-chamber components and post-head components; The combustion chamber components comprise: four fan-shaped hole combustible spoiler (1), front section grain (2), rear section grain (3) and combustion chamber shell (16); The four fan-shaped hole combustible spoiler (1) is arranged between the front section grain (2) and the rear section grain (3); The four fan-shaped hole combustible spoiler (1), the front section grain (2) and the rear section grain (3) are arranged inside the combustion chamber shell (16); The pre-chamber component and the post-chamber component are arranged at both ends of the combustion chamber shell (16) respectively; The catalytic bed component is arranged at one end of the pre-chamber component; The post-head component is arranged at one end of the post-chamber component; The post-chamber component is provided with a nozzle (17), and the nozzle (17) penetrates the post-head component; The catalytic bed component is used for decomposing the injected oxidant, under the action of high temperature and high pressure gas generated by the decomposition of the oxidant, the four fan-shaped hole combustible spoiler (1), the front section grain (2) and the rear section grain (3) are combusted; The nozzle (17) converts the heat energy of the high-temperature combustion gas into kinetic energy through expansion, and generates thrust by recoil. The four fan-shaped hole combustible spoiler (1) is centered on a circle center, and four fan-shaped holes are uniformly distributed around the circle center at equal intervals; High-temperature oxygen and water vapor make the four fan-shaped hole combustible spoiler (1), the front section grain (2) and the rear section grain (3) pyrolyze and combust, and the four fan-shaped hole combustible spoiler (1) changes from a four-fan-shaped hole state to a single-circle-hole state after combustion.

2. The combustible fin-based dual-thrust solid-propellant hybrid rocket engine system according to claim 1, wherein, The catalytic bed component comprises: a catalytic bed head cover plate (4), a catalytic bed shell (5) and a catalytic bed adapter flange (7); The catalytic bed head cover plate (4) and the catalytic bed shell (5) are connected by bolts; The catalytic bed shell (5) and the catalytic bed adapter flange (7) are connected by bolts; The catalytic bed adapter flange (7) is arranged on the pre-chamber component.

3. The combustible-fin-based dual-thrust solid-propellant hybrid rocket engine system according to claim 2, wherein, The pre-chamber component comprises: a pre-chamber insulation layer (8) and a pre-chamber shell (9); The pre-chamber insulation layer (8) is arranged inside the pre-chamber shell (9); The combustion chamber shell (16) is provided with a first combustion chamber flange (10) outside; The catalytic bed adapter flange (7), the pre-chamber shell (9) and the first combustion chamber flange (10) are sequentially fixedly connected by screws.

4. The combustible-fin-based dual-thrust solid-propellant liquid- fueled rocket engine system according to claim 3, wherein, The post-chamber component comprises a post-chamber insulation layer (12) and a post-chamber shell (13); The post-chamber insulation layer (12) is arranged inside the post-chamber shell (13); The post-head component comprises a post-head shell (14) and a post-head insulation layer (15); The post-head insulation layer (15) is arranged inside the post-head shell (14); The post-head shell (14) is arranged on the post-chamber shell (13); The combustion chamber shell (16) is provided with a second combustion chamber flange (11) outside; The second combustion chamber flange (11), the post-chamber shell (13) and the post-head shell (14) are connected by bolts.

5. The combustible-fin-based dual-thrust solid-propellant hybrid rocket engine system according to claim 4, wherein, The back combustion chamber component is provided with a nozzle (17) penetrating through the back head component, in particular, one end of the back head shell (14) is provided with a nozzle pressing plate (18); the nozzle pressing plate (18) fixes the nozzle (17); one end of the nozzle (17) communicates with the space composed of the back combustion chamber shell (13) and the back head shell (14); the other end communicates with the outside space.

6. The combustible-fin-based dual-thrust solid-propellant liquid- fueled rocket engine system according to claim 5, wherein, The four-fan-hole combustible spoiler (1), the front section grain (2) and the rear section grain (3) and the combustion chamber shell (16) need to be evenly coated with heat insulation and fire retardant putty to prevent high-temperature combustion gas from leaking out through the gap between the four-fan-hole combustible spoiler (1), the front section grain (2) and the rear section grain (3) and the combustion chamber shell (16); the four-fan-hole combustible spoiler (1) is evenly distributed around the center of a circle with four fans at equal intervals.

7. The combustible-fin-based dual-thrust solid-propellant hybrid rocket engine system according to claim 6, wherein The catalytic bed component further comprises a molybdenum-based silver mesh catalytic bed (6); the molybdenum-based silver mesh catalytic bed (6) decomposes the oxidizing agent injected into the front combustion chamber component to generate high-temperature oxygen and water vapor; the four-fan-hole combustible spoiler (1), the front section grain (2) and the rear section grain (3) are pyrolyzed and combusted by the high-temperature oxygen and water vapor; after combustion, the four-fan-hole combustible spoiler (1) changes from a four-fan-hole state to a single-circle-hole state.

8. A method of operating a dual-thrust solid-liquid hybrid rocket engine system based on combustible spoiler, characterized by, The method acts on the combustible spoiler-based double-thrust solid-liquid rocket engine system of claim 7, which comprises: injecting an oxidizing agent into the front combustion chamber component; the oxidizing agent is decomposed under the action of the molybdenum-based silver mesh catalytic bed (6) to generate high-temperature oxygen and water vapor; the four-fan-hole combustible spoiler (1), the front section grain (2) and the rear section grain (3) are pyrolyzed and combusted by the high-temperature oxygen and water vapor; after combustion, the four-fan-hole combustible spoiler (1) changes from a four-fan-hole state to a single-circle-hole state; after the four-fan-hole combustible spoiler (1) changes to a single-circle-hole state, the flow of the oxidizing agent injected into the front combustion chamber component is adjusted to keep the engine working near the optimal oxygen-to-fuel ratio; the nozzle (17) converts the heat energy of the high-temperature combustion gas into kinetic energy through expansion and generates thrust through recoil.

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