Double-thrust solid-liquid rocket engine system based on combustible spoiler and working method

Abstract

The invention 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.The double-thrust solid-liquid rocket engine system based on the combustible spoiler comprises the steps that a front-section grain, the four-fan-shaped-hole combustible spoiler and a rear-section grain are sequentially arranged in a combustion chamber shell; the chemical bed component is used for decomposing the injected oxidizing agent, and the four-sector-hole combustible spoiler, the front-section grain and the rear-section grain are combusted under the action of high-temperature and high-pressure gas generated by decomposing the oxidizing agent; the four-fan-shaped-hole combustible spoiler arranged in the combustion chamber channel of the engine can change the original flame layer structure, so that the incoming flow of an oxidizing agent and a fuel pyrolysis product are fully mixed and react, and the combustion efficiency of the engine is improved. The four-fan-shaped-hole combustible spoiler enhances the turbulence effect at the same time, so that the fuel burning speed of the rear section can be increased by several times compared with that of the front section. The device is simple in structure and easy to implement.

Description

Technical Field

[0001] The invention belongs to the technical field of rocket engines and relates to a dual-thrust solid-liquid rocket engine system based on a combustible spoiler and a working method. Background Art

[0002] The propellant of a typical solid-liquid rocket engine is composed of solid fuel and liquid oxidizer. Solid-liquid rocket engines have some obvious advantages over solid rocket engines, such as wide range thrust adjustment, multiple starts on demand, high specific impulse performance, long working time and good safety. Compared with liquid rocket engines, solid-liquid rocket engines have a simple structure and higher density specific impulse. At present, solid-liquid rocket engines have been used in sounding rockets, target missiles and commercial aerospace, and have broad prospects; however, there are two significant problems in dual-thrust solid-liquid rocket engines that limit their development.

[0003] First, solid-liquid rocket engines can achieve two-stage thrust by adjusting the oxidizer flow rate, but since the fuel flow rate is controlled by the oxidizer flow rate and this relationship is not linear, this thrust adjustment method will bring about the negative impact of the engine's easy deviation from the optimal oxygen-fuel ratio. The oxygen-fuel ratio is a crucial design parameter for rocket engines and greatly affects the performance of the engine. The problem of deviation from the optimal oxygen-fuel ratio during the operation of solid-liquid rocket engines will lead to a significant performance decline, mainly manifested in a decrease in specific impulse, which means that more propellant is required to produce the same thrust, which is not conducive to the advantages of variable thrust and high specific impulse of solid-liquid rocket engines, and greatly restricts its development. Second, the oxidizer of the solid-liquid rocket engine is difficult to fully mix with the pyrolysis fuel. This non-premixed combustion method makes the combustion efficiency of the solid-liquid rocket engine low. A spoiler structure is added to the combustion chamber, and the gas is mixed after passing through the spoiler, thereby improving the combustion efficiency. However, the introduction of spoilers and additional mounting structures increases the complexity, reduces the engine loading factor, and does not solve the problem of deviation from the optimal oxygen-fuel ratio during variable thrust. Summary of the invention

[0004] The purpose of the present invention is to solve the problem in the prior art that the two stages of a dual-thrust solid-liquid rocket engine are difficult to operate near the optimal oxygen-fuel ratio, and the oxidant of the solid-liquid rocket engine is difficult to fully mix with the pyrolysis fuel, and to provide a dual-thrust solid-liquid rocket engine system and working method based on a combustible spoiler.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] A dual-thrust solid-liquid rocket engine system based on a combustible spoiler, comprising: a combustion chamber component, a catalytic bed component, a front combustion chamber component, an afterburner component and a rear head component;

[0007] The combustion chamber components include: a four-sector-hole combustible spoiler, a front-stage grain, a rear-stage grain and a combustion chamber shell; the four-sector-hole combustible spoiler is arranged between the front-stage grain and the rear-stage grain; the four-sector-hole combustible spoiler, the front-stage grain and the rear-stage grain are arranged inside the combustion chamber shell; the front combustion chamber component and the afterburner chamber component are respectively arranged at both ends of the combustion chamber shell; 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 afterburner chamber component; a nozzle is arranged on the afterburner chamber component, and the nozzle passes through the rear head component; the catalytic bed component is used to decompose the injected oxidant, and under the action of the high-temperature and high-pressure gas generated by the decomposition of the oxidant, the four-sector-hole combustible spoiler, the front-stage grain and the rear-stage grain are burned; the nozzle converts the thermal energy of the high-temperature combustion gas generated by the combustion into kinetic energy through expansion, and generates thrust by recoil.

[0008] A further improvement of the present invention is:

[0009] Furthermore, the catalytic bed component includes: a catalytic bed head cover, a catalytic bed shell and a catalytic bed adapter flange; the catalytic bed head cover and the catalytic bed shell are connected by bolts; the catalytic bed shell and the catalytic bed adapter flange are connected by bolts; the catalytic bed adapter flange is arranged on the front combustion chamber component.

[0010] Furthermore, the front combustion chamber components include: a front combustion chamber insulation layer and a front combustion chamber shell; the front combustion chamber insulation layer is arranged inside the front combustion chamber shell; a first combustion chamber flange is arranged on the outside of the combustion chamber shell; the catalytic bed adapter flange, the front combustion chamber shell and the first combustion chamber flange are fixedly connected in sequence by screws.

[0011] Furthermore, the afterburner chamber component includes an afterburner chamber insulation layer and an afterburner chamber shell; the afterburner chamber insulation layer is arranged inside the afterburner chamber shell; the rear head component includes a rear head shell and a rear head insulation layer; the rear head insulation layer is arranged inside the rear head shell; the rear head shell is arranged on the afterburner chamber shell; a second combustion chamber flange is arranged on the outside of the combustion chamber shell; the second combustion chamber flange, the afterburner chamber shell and the rear head shell are connected by bolts.

[0012] Furthermore, a nozzle is provided on the afterburner component, and the nozzle passes through the rear head component, specifically: a nozzle pressing plate is provided at one end of the rear head shell; the nozzle pressing plate fixes the nozzle; one end of the nozzle is connected to the space formed by the afterburner shell and the rear head shell; and the other end is in communication with the external space.

[0013] Furthermore, heat-insulating flame-retardant putty needs to be evenly applied between the four-sector-hole combustible spoiler, the front-stage grain column, the rear-stage grain column and the combustion chamber shell to prevent high-temperature combustion gas from escaping through the gaps between the four-sector-hole combustible spoiler, the front-stage grain column, the rear-stage grain column and the combustion chamber shell; the four-sector-shaped combustible spoiler is centered on the center of the circle, and the four sectors are evenly distributed around the center of the circle at equal intervals.

[0014] Furthermore, the catalytic bed component also includes a molybdenum-based silver mesh catalytic bed; the molybdenum-based silver mesh catalytic bed decomposes the oxidant injected into the front combustion chamber component to produce high-temperature oxygen and water vapor; the four-fan-shaped hole combustible spoiler, the front section propellant and the rear section propellant are pyrolyzed and burned by the high-temperature oxygen and water vapor, and after the combustion, the four-fan-shaped hole combustible spoiler changes its shape from a four-fan-shaped hole state to a single circular hole state.

[0015] The working method of a dual-thrust solid-liquid rocket engine system based on a combustible spoiler comprises: injecting an oxidant into a front combustion chamber component, the oxidant is decomposed under the action of a molybdenum-based silver mesh catalytic bed to generate high-temperature oxygen and water vapor; the four-sector-hole combustible spoiler, the front-stage grain column and the rear-stage grain column are pyrolyzed and burned by the high-temperature oxygen and water vapor, and the shape of the four-sector-hole combustible spoiler changes from a four-sector-hole state to a single circular hole state after combustion; after the state of the four-sector-hole combustible spoiler changes to a single circular hole state, adjusting the flow rate of the oxidant injected into the front combustion chamber component so that the engine always works near the optimal oxygen-fuel ratio; the nozzle converts the heat energy of the high-temperature combustion gas generated by the combustion into kinetic energy through expansion, and generates thrust by recoil.

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

[0017] The present invention sequentially arranges a front-stage charge, a four-sector-hole combustible spoiler and a rear-stage charge inside the combustion chamber shell; the chemical bed component is used to decompose the injected oxidant, and under the action of the high-temperature and high-pressure gas generated by the decomposition of the oxidant, the four-sector-hole combustible spoiler, the front-stage charge and the rear-stage charge are burned; the four-sector-hole combustible spoiler arranged in the engine combustion chamber channel can change the original flame layer structure, so that the oxidant flow and the fuel pyrolysis products can be fully mixed and reacted, and the engine combustion efficiency can be improved. The four-sector-hole combustible spoiler also strengthens the turbulence effect, so that the combustion rate of the rear-stage fuel can be increased several times compared with the front stage. The present invention has a simple structure and is easy to implement. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments are briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0019] Figure 1 It is a structural schematic diagram of a dual-thrust solid-liquid rocket engine system based on a combustible spoiler according to the present invention;

[0020] Figure 2 The cross-sectional view of the flammable spoiler with four fan-shaped holes;

[0021] Figure 3 (a) is a diagram showing the state of the four-sector hole combustible spoiler when it is not burning;

[0022] Figure 3 (b) is a diagram showing the state of the four-sector hole combustible spoiler when it is burning;

[0023] Figure 3 (c) is a diagram showing the state of the four-sector-shaped flammable spoiler after combustion;

[0024] Figure 4 A schematic diagram of thrust and flow data during the hot test of a dual-thrust solid-liquid rocket engine with a combustible spoiler;

[0025] Figure 5 (a) is a graph showing the oxygen-fuel ratio of the engine in the working state at one stage;

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

[0027] Among them, 1-four-fan-shaped hole combustible spoiler, 2-front section charge, 3-rear section charge, 4-catalytic bed head cover, 5-catalytic bed shell, 6-molybdenum-based silver mesh catalytic bed, 7-catalytic bed adapter flange, 8-front combustion chamber insulation layer, 9-front combustion chamber shell, 10-first combustion chamber flange, 11-second combustion chamber flange, 12-afterburner chamber insulation layer, 13-afterburner chamber shell, 14-rear head shell, 15-rear head insulation layer, 16-combustion chamber shell, 17-nozzle, 18-nozzle pressure plate. DETAILED DESCRIPTION

[0028] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0029] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0030] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0031] In the description of the embodiments of the present invention, it should be noted that if the terms "upper", "lower", "horizontal", "inner", etc. indicate an orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the invention is usually placed when in use, it is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first", "second", etc. are only used to distinguish the 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 tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", which does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0033] In the description of the embodiments of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0034] The present invention is further described in detail below in conjunction with the accompanying drawings:

[0035] See also Figure 1 , the present invention discloses a dual-thrust solid-liquid rocket engine system based on a combustible spoiler, comprising: a combustion chamber component, a catalytic bed component, a front combustion chamber component, an afterburner component and a rear head component;

[0036] See also Figure 2 The combustion chamber components include: a four-sector-hole combustible spoiler 1, a front-stage grain 2, a rear-stage grain 3 and a combustion chamber shell 16; the four-sector-hole combustible spoiler 1 is arranged between the front-stage grain 2 and the rear-stage grain 3; the four-sector-hole combustible spoiler 1, the front-stage grain 2 and the rear-stage grain 3 are arranged inside the combustion chamber shell 16; the front-stage grain 2 is located upstream of the spoiler and is closely attached to the front end surface of the four-sector-hole combustible spoiler 1, and the burning rate of the front-stage grain 2 is almost unaffected by the four-sector-hole combustible spoiler 1; the rear-stage grain 3 is located downstream of the spoiler and is closely attached to the rear end surface of the four-sector-hole combustible spoiler 1, and the strong turbulence effect increases its burning rate. The front combustion chamber component and the afterburner component are respectively arranged at the two ends of the combustion chamber shell 16; the catalytic bed component is arranged at one end of the front combustion chamber component; the rear end cover component is arranged at one end of the afterburner component; a nozzle 17 is arranged on the afterburner component, and the nozzle 17 passes through the rear end cover component; the catalytic bed component is used to decompose the injected oxidant, and under the action of the high-temperature and high-pressure gas generated by the decomposition of the oxidant, the four-sector-hole combustible spoiler 1, the front section grain column 2 and the rear section grain column 3 are burned; the nozzle 17 converts the heat energy of the high-temperature combustion gas generated by the combustion into kinetic energy through expansion, and generates thrust by recoil. The front combustion chamber and the afterburner can make the mixing between the oxidant and the pyrolysis fuel more uniform and increase the residence time of the combustion gas, so as to improve the combustion efficiency of the solid-liquid rocket engine. The four-sector-hole combustible spoiler 1, the tubular front section grain column 2 and the tubular rear section grain column 3 are all made of high-density polyethylene HDPE material, and the three together constitute the solid fuel.

[0037] The four-sector-hole combustible spoiler 1 disposed in the engine combustion chamber channel changes the original flame layer structure, allowing the oxidant flow and the fuel pyrolysis products to be fully mixed and reacted, thereby improving the engine combustion efficiency. The four-sector-hole combustible spoiler 1 also enhances the turbulence effect, allowing the fuel burning rate in the rear section to be increased several times compared to the front section. The four-sector-hole combustible spoiler can increase the burning rate of the rear section of the propellant column more than the single-circular-hole combustible spoiler, and the sector-shaped hole form can ensure that there is less residual propellant in the later stage of the spoiler combustion, so as to avoid the spoiler being blown off and causing danger.

[0038] The catalytic bed components include: 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 front combustion chamber components. The front combustion chamber components include: 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; a first combustion chamber flange 10 is arranged outside the combustion chamber shell 16; the catalytic bed adapter flange 7, the front combustion chamber shell 9 and the first combustion chamber flange 10 are fixedly connected in sequence by screws.

[0039] The afterburner chamber component includes an afterburner chamber insulation layer 12 and an afterburner chamber shell 13; the afterburner chamber insulation layer 12 is arranged inside the afterburner chamber shell 13; the rear head component includes 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 afterburner chamber shell 13; a second combustion chamber flange 11 is arranged on the outside of the combustion chamber shell 16; the second combustion chamber flange 11, the afterburner chamber shell 13 and the rear head shell 14 are connected by bolts.

[0040] A nozzle 17 is provided on the afterburner component, and the nozzle 17 passes through the rear head component, specifically: a nozzle pressing plate 18 is provided at one end of the rear head shell 14; the nozzle pressing plate 18 fixes the nozzle 17; one end of the nozzle 17 is connected to the space formed by the afterburner shell 13 and the rear head shell 14; the other end is in communication with the external space.

[0041] The four-sector-hole combustible spoiler 1, the front-stage grain column 2, the rear-stage grain column 3 and the combustion chamber shell 16 need to be evenly coated with heat-insulating flame-retardant putty to prevent high-temperature combustion gas from escaping through the gaps between the four-sector-hole combustible spoiler 1, the front-stage grain column 2, the rear-stage grain column 3 and the combustion chamber shell 16. The four-sector-hole combustible spoiler 1 is centered on the center of the circle, and the four sectors are evenly distributed around the center of the circle at equal intervals.

[0042] The catalytic bed component also includes a molybdenum-based silver mesh catalytic bed 6; the molybdenum-based silver mesh catalytic bed 6 decomposes the oxidant injected into the front combustion chamber component to generate high-temperature oxygen and water vapor; the four-sector-hole combustible spoiler 1, the front-stage powder column 2 and the rear-stage powder column 3 are pyrolyzed and burned by the high-temperature oxygen and water vapor. After the combustion, the four-sector-hole combustible spoiler 1 changes from a four-sector-hole state to a single circular hole state, see Figure 3 (a) Figure 3 (b) and Figure 3 (c).

[0043] The working method of a dual-thrust solid-liquid rocket engine system based on a combustible spoiler comprises: injecting an oxidant into a front combustion chamber component, the oxidant is decomposed under the action of a molybdenum-based silver mesh catalytic bed 6 to generate high-temperature oxygen and water vapor; the four-sector-hole combustible spoiler 1, the front-stage grain column 2 and the rear-stage grain column 3 are pyrolyzed and burned by the high-temperature oxygen and water vapor, and the four-sector-hole combustible spoiler 1 changes from a four-sector-hole state to a single circular hole state after combustion; after the state of the four-sector-hole combustible spoiler 1 changes to a single circular hole state, adjusting the flow rate of the oxidant injected into the front combustion chamber component so that the engine always works near the optimal oxygen-fuel ratio; the nozzle 17 converts the heat energy of the high-temperature combustion gas generated by the combustion into kinetic energy through expansion, and generates thrust by recoil.

[0044] The engine of the present invention uses high-concentration 95% hydrogen peroxide as an oxidant. The hydrogen peroxide is decomposed into high-temperature oxygen and water vapor after passing through a catalytic bed, so that the solid HDPE fuel is pyrolyzed and burned. Figure 4 The thrust and flow rate data of the hot test process of the dual-thrust solid-liquid rocket engine with a combustible spoiler described in the present invention are displayed. Figure 4 In the experiment, three pulse starts were carried out at 5s, 10s and 15s to preheat and activate the catalyst bed. The formal ignition was at 20.2s. The oxidant flow rate was set to 180g / s, working for 6.6s, 40g / s, working for 13.4s. The results showed that the error between the predicted and experimental results was within an acceptable range. Figure 5 It shows that the oxygen-fuel ratio during the two-stage operation of the engine is maintained near the optimal oxygen-fuel ratio, which ensures the engine's higher specific impulse performance.

[0045] Adjust the oxidant flow rate injected into the front combustion chamber components so that the engine always operates near the optimal oxygen-fuel ratio, specifically:

[0046] By carrying out numerical simulation of the flow field in solid-liquid rocket engines, the burning rate formulas of each burning surface are obtained. and engine specific impulse efficiency

[0047] The engine internal ballistics is calculated based on the burning rate formula and specific impulse efficiency. The zero-dimensional internal ballistics assumption, instantaneous equilibrium pressure method and parallel layer combustion theorem are adopted to obtain the curves of combustion chamber pressure and thrust changing with time during the engine operation process, thereby obtaining the optimal oxygen-fuel ratio.

[0048] in, is the burning rate of the burning surface, a and n are constants related only to the oxidant, G o is the oxidant flow rate, calculated as The corresponding channel area A o Ratio

[0049]

[0050] In the first stage, the four-sector-hole combustible spoiler 1, the front-stage grain 2 and the rear-stage grain 3 are pyrolyzed and burned, and the four-sector-hole combustible spoiler 1 is in the state of four-sector-holes; the engine specific impulse efficiency In the second stage, the four-sector-shaped combustible spoiler 1, the front-stage grain 2 and the rear-stage grain 3 continue to burn, and the four-sector-shaped combustible spoiler 1 is in a single circular hole state; the engine specific impulse efficiency The engine specific impulse efficiency is given by experimental experience.

[0051] When the combustion of the front and rear ends of the propellant column is ignored, the burning rate formula is shown in Table 1.

[0052] Table 1

[0053]

[0054] The charge shape of the second-stage engine is basically transformed into a tubular charge, and its burning rate formula is shown in Table 2.

[0055] Table 2

[0056]

[0057] The engine internal ballistics calculation is carried out based on the burning rate formula and specific impulse efficiency, and the zero-dimensional internal ballistics assumption, instantaneous equilibrium pressure method and parallel layer combustion theorem are adopted. The engine internal ballistics calculation technology is relatively mature at present, so I will not elaborate on it. The internal ballistic calculation is to finally obtain the curves of the combustion chamber pressure and thrust changing with time during the operation of the engine, that is, the pc-t and Ft curves. At the same time, other key parameters can also be obtained, such as fuel flow rate, engine oxygen-fuel ratio O / F, etc. In this example, by adjusting the oxidizer flow rate of the two stages of the engine, the final oxidizer flow rate is 180g / s for 6.6s and 40g / s for 13.4s. Figure 5 (a) and Figure 5 As shown in (b), the engine operates at an optimal oxygen-fuel ratio of 6.7 throughout the entire process.

[0058] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A dual-thrust solid-liquid rocket engine system based on a combustible spoiler, characterized in that: include: Combustion chamber parts, catalytic bed parts, front combustion chamber parts, after combustion chamber parts and rear head parts; The combustion chamber components include: a four-sector-hole combustible spoiler (1), a front-stage charge (2), a rear-stage charge (3) and a combustion chamber shell (16); the four-sector-hole combustible spoiler (1) is arranged between the front-stage charge (2) and the rear-stage charge (3); the four-sector-hole combustible spoiler (1), the front-stage charge (2) and the rear-stage charge (3) are arranged inside the combustion chamber shell (16); the front combustion chamber component and the rear combustion chamber component are respectively arranged at two ends of the combustion chamber shell (16); the catalytic bed component is arranged at the front combustion chamber The rear end cover component is arranged at one end of the afterburner component; the afterburner component is provided with a nozzle (17), and the nozzle (17) passes through the rear end cover component; the catalytic bed component is used to decompose the injected oxidant, and under the action of the high-temperature and high-pressure gas generated by the decomposition of the oxidant, the four-sector-hole combustible spoiler (1), the front section charge column (2) and the rear section charge column (3) are burned; the nozzle (17) converts the heat energy of the high-temperature combustion gas generated by the combustion into kinetic energy through the expansion effect, and generates thrust by the recoil effect.

2. The dual-thrust solid-liquid rocket engine system based on a combustible spoiler according to claim 1 is characterized in that: 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; and the catalytic bed adapter flange (7) is arranged on the front combustion chamber component.

3. The dual-thrust solid-liquid rocket engine system based on a combustible spoiler according to claim 2 is characterized in that: The front combustion chamber components include: 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); a first combustion chamber flange (10) is arranged on the outside of the combustion chamber shell (16); the catalytic bed adapter flange (7), the front combustion chamber shell (9) and the first combustion chamber flange (10) are fixedly connected in sequence by screws.

4. The dual-thrust solid-liquid rocket engine system based on a combustible spoiler according to claim 3 is characterized in that: The afterburner chamber component comprises an afterburner chamber insulation layer (12) and an afterburner chamber shell (13); the afterburner chamber insulation layer (12) is arranged inside the afterburner 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 afterburner chamber shell (13); a second combustion chamber flange (11) is arranged on the outside of the combustion chamber shell (16); the second combustion chamber flange (11), the afterburner chamber shell (13) and the rear head shell (14) are connected by bolts.

5. The dual-thrust solid-liquid rocket engine system based on a combustible spoiler according to claim 4 is characterized in that: The afterburner component is provided with a nozzle (17), and the nozzle (17) passes through the rear head component, specifically: a nozzle pressing plate (18) is provided at one end of the rear head shell (14); the nozzle pressing plate (18) fixes the nozzle (17); one end of the nozzle (17) is connected to the space formed by the afterburner shell (13) and the rear head shell (14); and the other end is in communication with the external space.

6. The dual-thrust solid-liquid rocket engine system based on a combustible spoiler according to claim 5 is characterized in that: A heat-insulating flame-retardant putty is evenly applied between the four-sector-hole combustible spoiler (1), the front-stage grain column (2), the rear-stage grain column (3) and the combustion chamber shell (16) to prevent high-temperature combustion gas from escaping through the gaps between the four-sector-hole combustible spoiler (1), the front-stage grain column (2), the rear-stage grain column (3) and the combustion chamber shell (16); the four-sector-hole combustible spoiler (1) is centered on the center of the circle, and the four sectors are evenly distributed around the center of the circle at equal intervals.

7. The dual-thrust solid-liquid rocket engine system based on a combustible spoiler according to claim 6 is characterized in that: The catalytic bed component also includes a molybdenum-based silver mesh catalytic bed (6); the molybdenum-based silver mesh catalytic bed (6) decomposes the oxidant injected into the front combustion chamber component to generate high-temperature oxygen and water vapor; the four-sector-hole combustible spoiler (1), the front-stage charge column (2) and the rear-stage charge column (3) are pyrolyzed and burned by the high-temperature oxygen and water vapor, and after the combustion, the four-sector-hole combustible spoiler (1) changes its shape from a four-sector-hole state to a single circular hole state.

8. The working method of the dual-thrust solid-liquid rocket engine system based on the combustible spoiler is characterized in that: The dual-thrust solid-liquid rocket engine system based on the combustible spoiler as described in claim 7, the method being: injecting an oxidant into the front combustion chamber component, the oxidant being decomposed under the action of a molybdenum-based silver mesh catalytic bed (6) to produce high-temperature oxygen and water vapor; the four-sector-hole combustible spoiler (1), the front-stage grain (2) and the rear-stage grain (3) are pyrolyzed and burned by the high-temperature oxygen and water vapor, and the four-sector-hole combustible spoiler (1) changes from a four-sector-hole state to a single circular hole state after combustion; after the state of the four-sector-hole combustible spoiler (1) changes to a single circular hole state, adjusting the flow rate of the oxidant injected into the front combustion chamber component so that the engine always operates near the optimal oxygen-fuel ratio; the nozzle (17) converts the thermal energy of the high-temperature combustion gas generated by the combustion into kinetic energy through expansion, and generates thrust by recoil.

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