A solid preburn rotary detonation rocket engine

Abstract

The application discloses a solid pre-combustion rotating detonation rocket engine, which comprises a fuel-rich pre-combustion chamber, an oxygen-rich pre-combustion chamber, a detonation combustion chamber and a connecting panel, wherein the fuel-rich pre-combustion chamber is in a cylindrical structure and located at the front part of the engine; the oxygen-rich pre-combustion chamber is in a cylindrical structure and located at the rear part of the engine; the detonation combustion chamber is in a cylindrical structure with an annular cross section and located outside the oxygen-rich pre-combustion chamber; and the connecting panel is located at the middle part of the engine and used for connecting the fuel-rich pre-combustion chamber, the oxygen-rich pre-combustion chamber and the detonation combustion chamber. When the engine works, the oxygen-rich and fuel-rich high-temperature gases generated by the engine enter the detonation combustion chamber, are mixed and chemically reacted, form a detonation wave which continuously and stably propagates along the circumferential direction, and the detonation products are discharged from the outlet of the detonation combustion chamber and form a thrust. The engine has the advantages of high specific impulse, compact structure, high reliability and the like, and can realize the application of pure solid propellant on the rotating detonation rocket engine.

Description

Technical Field

[0001] This invention relates to the field of aerospace propulsion technology, specifically to a solid rotating detonation rocket engine. Background Technology

[0002] A rotating detonation rocket engine is a space propulsion device that generates thrust by continuously rotating and propagating one or more rotating detonation waves within a ring-shaped combustion chamber. Compared with traditional rocket engines, rotating detonation rocket engines have the following advantages: (1) high thermodynamic cycle efficiency, theoretically achieving a greater specific impulse; (2) fast combustion speed and high thermal intensity, which can significantly shorten the engine structure length. Based on these characteristics, rotating detonation technology is expected to provide a more efficient and reliable power source for spacecraft, with broad application prospects. In the past decade, domestic and international efforts have been continuously invested in tackling key technologies related to rotating detonation rocket engines, and breakthroughs have been achieved in multiple directions, steadily progressing towards the goal of engineering application.

[0003] Currently, the research and development of rotating detonation rocket engines mainly uses gaseous or liquid propellants, while research on the application of solid propellants in rotating detonation rocket engines is relatively scarce. In 2023, Wenbin Wu published a paper entitled "Experimental research on solid fuel pre-combustion rotating detonation engine" in Volume 205 of the journal "Acta Astronautica", proposing a solid fuel pre-combustion rotating detonation engine. This engine uses a gas generator to produce oxygen-deficient gas, which is injected into the rotating detonation combustion chamber to mix with oxygen and detonate to form a rotating detonation wave, thereby generating thrust. The feasibility of this scheme has been verified by experiments, but it still has the following shortcomings: (1) the space inside the inner shell of the annular rotating detonation combustion chamber has not been effectively utilized; (2) the gaseous or liquid oxidizer used in the rotating detonation combustion chamber needs to be equipped with a pressurized injection device, making the engine structure more complex. Summary of the Invention

[0004] To address the current difficulties in applying solid propellants in rotating detonation rocket engines, this invention discloses a solid pre-combustion rotating detonation rocket engine, the specific technical solution of which is as follows:

[0005] A solid-fuel pre-combustion rotating detonation rocket engine, the engine comprising a fuel-rich pre-combustion chamber, an oxygen-rich pre-combustion chamber, a detonation combustion chamber, and a connecting panel;

[0006] The fuel-rich pre-combustion chamber is a cylindrical structure located at the front of the engine and is connected to the connecting panel by bolts. The fuel-rich pre-combustion chamber is filled with fuel-rich propellant and is used to generate fuel-rich gas.

[0007] The oxygen-enriched pre-combustion chamber is a cylindrical structure located at the rear of the engine and is detachably connected to the connecting panel. The oxygen-enriched pre-combustion chamber is filled with oxygen-enriched propellant and is used to generate oxygen-enriched combustion gas.

[0008] The detonation combustion chamber is a cylindrical structure with an annular cross-section, located outside the oxygen-enriched pre-combustion chamber, and is detachably connected to the connecting panel. The detonation combustion chamber is used to mix the fuel-enriched gas and the oxygen-enriched gas, so that the fuel-enriched gas and the oxygen-enriched gas undergo a chemical reaction to form a detonation wave that propagates continuously and stably in the circumferential direction, and serves as an outlet channel for the detonation products.

[0009] The connecting panel is located in the middle of the engine. The front end of the connecting panel is detachably connected to the fuel-rich pre-combustion chamber, and the rear end is detachably connected to the oxygen-rich pre-combustion chamber and the detonation combustion chamber. The connecting panel, the fuel-rich pre-combustion chamber, the oxygen-rich pre-combustion chamber, and the detonation combustion chamber are coaxial after installation. The connecting panel is used to connect the fuel-rich pre-combustion chamber, the oxygen-rich pre-combustion chamber, and the detonation combustion chamber together.

[0010] Preferably, the oxygen-enriched pre-combustion chamber includes an oxygen-enriched pre-combustion chamber shell, an oxygen-enriched pre-combustion chamber insulation layer, an oxygen-enriched pre-combustion chamber propellant charge, an oxygen-enriched pre-combustion chamber igniter, and an oxygen-enriched pre-combustion chamber outlet throat liner.

[0011] The oxygen-enriched pre-combustion chamber shell is a semi-enclosed cylindrical container. The rear end of the oxygen-enriched pre-combustion chamber is closed. The side of the oxygen-enriched pre-combustion chamber shell is provided with multiple through holes evenly arranged in the circumferential direction. The front end of the oxygen-enriched pre-combustion chamber shell is provided with a flange. The front end flange of the oxygen-enriched pre-combustion chamber shell is detachably connected to the connecting panel. The front end of the oxygen-enriched pre-combustion chamber shell and the connecting panel are engaged by an annular boss and groove.

[0012] The insulation layer of the oxygen-enriched pre-combustion chamber is adhered to the inside of the oxygen-enriched pre-combustion chamber shell, and the outer side of the insulation layer is closely attached to the inner wall of the oxygen-enriched pre-combustion chamber shell and the rear end face of the connecting panel, in order to prevent the high-temperature gas in the oxygen-enriched pre-combustion chamber from affecting the mechanical properties of the oxygen-enriched pre-combustion chamber shell.

[0013] The oxygen-enriched pre-combustion chamber propellant is filled inside the oxygen-enriched pre-combustion chamber shell. The outer side of the oxygen-enriched pre-combustion chamber propellant is in close contact with the inner side of the oxygen-enriched pre-combustion chamber insulation layer. The inner side of the oxygen-enriched pre-combustion chamber propellant has a through hole. The composition of the oxygen-enriched pre-combustion chamber propellant includes oxygen-enriched propellant, which is used to generate oxygen-enriched fuel gas.

[0014] The oxygen-enriched pre-combustion chamber igniter is threaded onto the connecting panel and extends into the oxygen-enriched pre-combustion chamber. The oxygen-enriched pre-combustion chamber igniter is filled with igniting powder to form high-temperature gas, thereby igniting the propellant column of the oxygen-enriched pre-combustion chamber.

[0015] The oxygen-enriched pre-combustion chamber outlet throat liner has multiple outlet throat liners, which are installed in the through holes on the side of the oxygen-enriched pre-combustion chamber shell and are evenly arranged circumferentially. The internal contraction and expansion channels of the multiple outlet throat liners are used to connect the interior of the oxygen-enriched pre-combustion chamber and the detonation combustion chamber.

[0016] Preferably, the detonation combustion chamber includes a detonation combustion chamber shell, a detonation combustion chamber insulation layer, and a detonation combustion chamber outlet throat liner;

[0017] The detonation combustion chamber shell is a cylindrical structure. The detonation combustion chamber shell and the oxygen-enriched pre-combustion chamber shell together form an annular cylindrical cavity. A flange is provided at the front end of the detonation combustion chamber shell.

[0018] The heat insulation layer of the detonation combustion chamber is adhered to the inside of the annular cylindrical cavity, and the outer side of the heat insulation layer of the detonation combustion chamber is closely attached to the inner wall of the annular cylindrical cavity, in order to prevent the high-temperature gas inside the detonation combustion chamber from affecting the mechanical properties of the detonation combustion chamber shell.

[0019] The outlet throat liner of the detonation combustion chamber is located at the tail of the detonation combustion chamber. Its inner and outer sides are tightly fitted with the shell of the oxygen-enriched pre-combustion chamber and the shell of the detonation combustion chamber, respectively. The middle part is a contraction and expansion annular channel. The outlet throat liner of the detonation combustion chamber is used as an outlet channel for detonation products.

[0020] Preferably, the fuel-rich pre-combustion chamber includes a fuel-rich pre-combustion chamber shell, a fuel-rich pre-combustion chamber insulation layer, a fuel-rich pre-combustion chamber propellant charge, a fuel-rich pre-combustion chamber igniter, and a fuel-rich pre-combustion chamber outlet throat liner.

[0021] The fuel-rich pre-combustion chamber shell is a semi-enclosed cylindrical container. The fuel-rich pre-combustion chamber igniter is installed at the head of the fuel-rich pre-combustion chamber shell. A flange is provided at the rear end of the fuel-rich pre-combustion chamber shell. The rear flange of the fuel-rich pre-combustion chamber shell is detachably connected to the connecting panel. The rear end of the fuel-rich pre-combustion chamber shell and the connecting panel are engaged by an annular boss and groove.

[0022] The insulation layer of the fuel-rich pre-combustion chamber is adhered to the inside of the fuel-rich pre-combustion chamber shell, and the outer side of the insulation layer of the fuel-rich pre-combustion chamber is in close contact with the inner wall of the fuel-rich pre-combustion chamber shell and the front end face of the connecting panel, in order to prevent the high-temperature gas in the fuel-rich pre-combustion chamber from affecting the mechanical properties of the fuel-rich pre-combustion chamber shell.

[0023] The fuel-rich pre-combustion chamber propellant is filled inside the fuel-rich pre-combustion chamber shell. The outer side of the fuel-rich pre-combustion chamber propellant is in close contact with the inner side of the fuel-rich pre-combustion chamber insulation layer. The inner side of the fuel-rich pre-combustion chamber propellant has a through hole. The fuel-rich pre-combustion chamber propellant includes fuel-rich propellant for generating fuel-rich gas.

[0024] The fuel-rich pre-combustion chamber igniter is threadedly installed at the head of the fuel-rich pre-combustion chamber shell and extends into the interior of the fuel-rich pre-combustion chamber. The fuel-rich pre-combustion chamber igniter is filled with igniting powder to generate high-temperature gas, thereby igniting the fuel-rich pre-combustion chamber propellant column.

[0025] The connecting panel is provided with a plurality of through holes evenly arranged circumferentially, and the front end of the oxygen-enriched pre-combustion chamber shell is provided with a plurality of through holes evenly arranged circumferentially. The number of through holes at the front end of the oxygen-enriched pre-combustion chamber shell is the same as the number of through holes on the connecting panel. There are a plurality of outlet throat liners for the fuel-enriched pre-combustion chamber. The plurality of outlet throat liners for the fuel-enriched pre-combustion chamber are installed in the through holes at the front end of the connecting panel and the oxygen-enriched pre-combustion chamber shell and are evenly arranged circumferentially. The internal contraction and expansion channels of the plurality of outlet throat liners for the fuel-enriched pre-combustion chamber are used to connect the interior of the fuel-enriched pre-combustion chamber and the detonation combustion chamber.

[0026] Preferably, the connecting panel, the rear flange of the fuel-rich pre-combustion chamber shell, the front flange of the oxygen-rich pre-combustion chamber shell, and the front flange of the detonation combustion chamber shell are fastened together by bolts.

[0027] Preferably, the engine further includes a central cone, which is a hollow conical structure located at the tail of the solid pre-combustion rotating detonation rocket engine. It is connected to the rear end of the oxygen-rich pre-combustion chamber shell via threads. The conical outer surface of the central cone is an extension of the detonation combustion chamber outlet throat liner contraction and expansion channel on the outside. The conical outer surface of the central cone and the detonation combustion chamber outlet throat liner contraction and expansion channel together form a plug-type nozzle structure, which is used to further expand and accelerate the detonation products, thereby achieving the effect of thrust enhancement.

[0028] Alternatively, an external ignition device may be installed on the shell of the detonation combustion chamber through an opening. This device is used to assist in ignition and detonation when the rich combustion gas and the oxygen-rich combustion gas cannot spontaneously detonate to form a detonation wave after being mixed. The external ignition device may be a spark plug, explosive, hot jet tube, plasma igniter, or other device with ignition function.

[0029] The working principle of the solid pre-combustion rotating detonation rocket engine disclosed in this invention is as follows: The fuel-rich pre-combustion chamber and the oxygen-rich pre-combustion chamber are respectively filled with fuel-rich propellant and oxygen-rich propellant. When the engine is working, the fuel-rich pre-combustion chamber and the oxygen-rich pre-combustion chamber generate fuel-rich gas and oxygen-rich gas respectively. The fuel-rich gas and the oxygen-rich gas are injected into the annular detonation combustion chamber through the outlet throat of the fuel-rich pre-combustion chamber and the outlet throat of the oxygen-rich pre-combustion chamber respectively. They are mixed and undergo a chemical reaction in the detonation combustion chamber. After the detonation-to-detonation process, a detonation wave is spontaneously formed and propagates continuously and stably in the circumferential direction. The detonation products are discharged from the outlet throat of the detonation combustion chamber and form thrust.

[0030] The beneficial effects achieved by this invention are as follows:

[0031] (1) The solid pre-combustion rotating detonation rocket engine provided by the present invention generates thrust by detonation combustion, which can achieve a higher specific impulse compared with conventional solid engines.

[0032] (2) The solid pre-combustion rotating detonation rocket engine provided by the present invention makes full use of the space inside the annular detonation combustion chamber and designs it as an oxygen-rich combustion chamber, thereby effectively reducing negative mass and making the engine structure more compact.

[0033] (3) The solid pre-combustion rotating detonation rocket engine provided by the present invention uses two solid pre-combustion chambers, eliminating the need for additional injection devices, which reduces the complexity of the engine structure and improves the reliability of the engine structure. Attached Figure Description

[0034] To more clearly illustrate the technical solutions disclosed in this invention, the accompanying drawings used in some embodiments of this invention will be briefly described below. Obviously, the drawings described below are merely drawings of some embodiments of this invention, and those skilled in the art can obtain other drawings based on these drawings. Furthermore, the drawings described below can be considered schematic diagrams and are not intended to limit the actual dimensions of the products or the actual flow of the methods involved in the embodiments of this invention.

[0035] Figure 1 This is a schematic diagram of the external shape of a solid pre-combustion rotating detonation rocket engine provided in this invention;

[0036] Figure 2 This is a longitudinal sectional view of a solid pre-combustion rotating detonation rocket engine provided in this invention;

[0037] Figure 3 This is a cross-sectional view of a solid pre-combustion rotating detonation rocket engine provided in this invention.

[0038] The attached figures are labeled as follows:

[0039] 1. Connection panel;

[0040] 2. Rich-fuel pre-combustion chamber; 2-1. Rich-fuel pre-combustion chamber shell; 2-2. Rich-fuel pre-combustion chamber insulation layer; 2-3. Rich-fuel pre-combustion chamber propellant charge; 2-4. Rich-fuel pre-combustion chamber igniter; 2-5. Rich-fuel pre-combustion chamber outlet throat liner;

[0041] 3. Oxygen-enriched pre-combustion chamber; 3-1. Oxygen-enriched pre-combustion chamber shell; 3-2. Oxygen-enriched pre-combustion chamber insulation layer; 3-3. Oxygen-enriched pre-combustion chamber propellant; 3-4. Oxygen-enriched pre-combustion chamber igniter; 3-5. Oxygen-enriched pre-combustion chamber outlet throat liner.

[0042] 4. Detonation combustion chamber; 4-1. Detonation combustion chamber shell; 4-2. Detonation combustion chamber insulation layer; 4-3. Detonation combustion chamber outlet throat liner;

[0043] 5. Central cone. Detailed Implementation

[0044] The embodiments disclosed in this invention will now be described in further detail with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this invention, and not all embodiments.

[0045] Example 1

[0046] The solid pre-combustion rotating detonation rocket engine provided in this invention has the following shape: Figure 1 As shown.

[0047] The engine includes a fuel-rich pre-combustion chamber 2;

[0048] The fuel-rich pre-combustion chamber 2 is a cylindrical structure located at the front of the engine and is fastened to the connecting panel 1 by bolts. The fuel-rich pre-combustion chamber 2 is filled with fuel-rich propellant and is used to generate fuel-rich gas.

[0049] A longitudinal sectional view of a solid pre-combustion rotating detonation rocket engine provided in this invention is shown below. Figure 2 As shown, the engine also includes an oxygen-rich pre-combustion chamber 3, a knock combustion chamber 4, and a connecting panel 1;

[0050] The oxygen-enriched pre-combustion chamber 3 is a cylindrical structure located at the rear of the engine and is fastened to the connecting panel 1 by bolts. The oxygen-enriched pre-combustion chamber 3 is filled with oxygen-enriched propellant and is used to generate oxygen-enriched combustion gas.

[0051] The detonation combustion chamber 4 is a cylindrical structure with an annular cross-section, located outside the oxygen-enriched pre-combustion chamber 3, and is fastened to the connecting panel 1 by bolts. The detonation combustion chamber 4 is used to mix the fuel-enriched gas and the oxygen-enriched gas, so that the fuel-enriched gas and the oxygen-enriched gas undergo a chemical reaction to form a detonation wave that propagates continuously and stably in the circumferential direction, and serves as an outlet channel for the detonation products.

[0052] The connecting panel 1 is located in the middle of the engine. The front end of the connecting panel 1 is fastened to the fuel-rich pre-combustion chamber 2 by bolts, and the rear end is fastened to the oxygen-rich pre-combustion chamber 3 and the detonation combustion chamber 4 by bolts. The connecting panel 1, the fuel-rich pre-combustion chamber 2, the oxygen-rich pre-combustion chamber 3, and the detonation combustion chamber 4 are coaxial after installation. The connecting panel 1 is used to connect the fuel-rich pre-combustion chamber 2, the oxygen-rich pre-combustion chamber 3, and the detonation combustion chamber 4 together.

[0053] A cross-sectional view of a solid pre-combustion rotating detonation rocket engine provided in this invention is shown below. Figure 3 As shown, the cutting position markings are as follows: Figure 2 As shown.

[0054] like Figure 3 As shown, the oxygen-enriched pre-combustion chamber 3 includes an oxygen-enriched pre-combustion chamber shell 3-1, an oxygen-enriched pre-combustion chamber insulation layer 3-2, an oxygen-enriched pre-combustion chamber propellant 3-3, an oxygen-enriched pre-combustion chamber igniter 3-4, and an oxygen-enriched pre-combustion chamber outlet throat liner 3-5.

[0055] The oxygen-enriched pre-combustion chamber shell 3-1 is a semi-enclosed cylindrical container. The rear end of the oxygen-enriched pre-combustion chamber 3 is closed. The side of the oxygen-enriched pre-combustion chamber shell 3-1 is provided with a plurality of through holes evenly arranged in the circumferential direction. The front end of the oxygen-enriched pre-combustion chamber shell 3-1 is provided with a flange. The front end flange of the oxygen-enriched pre-combustion chamber shell 3-1 is fastened to the connecting panel 1 by bolts. The front end of the oxygen-enriched pre-combustion chamber shell 3-1 and the connecting panel 1 are engaged by an annular boss groove.

[0056] The oxygen-enriched pre-combustion chamber insulation layer 3-2 is pasted inside the oxygen-enriched pre-combustion chamber shell 3-1. The outer side of the oxygen-enriched pre-combustion chamber insulation layer 3-2 is closely attached to the inner wall of the oxygen-enriched pre-combustion chamber shell 3-1 and the rear end face of the connecting panel 1, in order to prevent the high-temperature gas in the oxygen-enriched pre-combustion chamber 3 from affecting the mechanical properties of the oxygen-enriched pre-combustion chamber shell 3-1.

[0057] The oxygen-enriched pre-combustion chamber propellant 3-3 is filled inside the oxygen-enriched pre-combustion chamber shell 3-1. The outer side of the oxygen-enriched pre-combustion chamber propellant 3-3 is closely attached to the inner side of the oxygen-enriched pre-combustion chamber insulation layer 3-2. The inner side of the oxygen-enriched pre-combustion chamber propellant 3-3 is a through hole. The composition of the oxygen-enriched pre-combustion chamber propellant 3-3 includes oxygen-enriched propellant, which is used to generate oxygen-enriched gas.

[0058] The oxygen-enriched pre-combustion chamber igniter 3-4 is threadedly installed on the connecting panel 1 and extends into the oxygen-enriched pre-combustion chamber 3. The oxygen-enriched pre-combustion chamber igniter 3-4 is filled with igniting powder to form high-temperature gas, thereby igniting the oxygen-enriched pre-combustion chamber propellant column 3-3.

[0059] There are multiple outlet throat liners 3-5 of the oxygen-enriched pre-combustion chamber. The multiple outlet throat liners 3-5 of the oxygen-enriched pre-combustion chamber are installed in the through holes on the side of the oxygen-enriched pre-combustion chamber shell 3-1 and are evenly arranged in the circumferential direction. The internal contraction and expansion channels of the multiple outlet throat liners 3-5 of the oxygen-enriched pre-combustion chamber are used to connect the interior of the oxygen-enriched pre-combustion chamber 3 and the detonation combustion chamber 4.

[0060] like Figure 2 As shown, the detonation combustion chamber 4 includes a detonation combustion chamber shell 4-1, a detonation combustion chamber insulation layer 4-2, and a detonation combustion chamber outlet throat liner 4-3;

[0061] The detonation combustion chamber shell 4-1 is a cylindrical structure. The detonation combustion chamber shell 4-1 and the oxygen-enriched pre-combustion chamber shell 3-1 together form an annular cylindrical cavity. A flange is provided at the front end of the detonation combustion chamber shell 4-1. An external ignition device is installed on the detonation combustion chamber shell 4-1 through an opening. It is used to assist in ignition and detonation when the rich combustion gas and the oxygen-enriched gas cannot spontaneously detonate to form a detonation wave after mixing. The external ignition device can be a spark plug, explosive, hot jet tube, plasma igniter or other device with ignition function.

[0062] The detonation combustion chamber insulation layer 4-2 is adhered to the inside of the annular cylindrical cavity, and the outer side of the detonation combustion chamber insulation layer 4-2 is closely attached to the inner wall of the annular cylindrical cavity, in order to prevent the high-temperature gas in the detonation combustion chamber 4 from affecting the mechanical properties of the detonation combustion chamber shell 4-1.

[0063] The outlet throat liner 4-3 of the detonation combustion chamber is located at the tail of the detonation combustion chamber 4. Its inner and outer sides are tightly fitted with the oxygen-enriched pre-combustion chamber shell 3-1 and the detonation combustion chamber shell 4-1, respectively. The middle part is a contraction and expansion annular channel. The outlet throat liner 4-3 of the detonation combustion chamber is used as the outlet channel for detonation products.

[0064] The fuel-rich pre-combustion chamber 2 includes a fuel-rich pre-combustion chamber shell 2-1, a fuel-rich pre-combustion chamber insulation layer 2-2, a fuel-rich pre-combustion chamber propellant 2-3, a fuel-rich pre-combustion chamber igniter 2-4, and a fuel-rich pre-combustion chamber outlet throat liner 2-5.

[0065] The fuel-rich pre-combustion chamber shell 2-1 is a semi-enclosed cylindrical container. The fuel-rich pre-combustion chamber igniter 2-4 is installed at the head of the fuel-rich pre-combustion chamber shell 2-1. A flange is provided at the rear end of the fuel-rich pre-combustion chamber shell 2-1. The rear flange of the fuel-rich pre-combustion chamber shell 2-1 is fastened to the connecting panel 1 by bolts. The rear end of the fuel-rich pre-combustion chamber shell 2-1 and the connecting panel 1 are engaged by an annular boss and groove.

[0066] The heat insulation layer 2-2 of the fuel-rich pre-combustion chamber is pasted inside the fuel-rich pre-combustion chamber shell 2-1. The outer side of the heat insulation layer 2-2 of the fuel-rich pre-combustion chamber is closely attached to the inner wall of the fuel-rich pre-combustion chamber shell 2-1 and the front end face of the connecting panel 1, in order to prevent the high-temperature gas in the fuel-rich pre-combustion chamber 2 from affecting the mechanical properties of the fuel-rich pre-combustion chamber shell 2-1.

[0067] The fuel-rich pre-combustion chamber propellant 2-3 is filled inside the fuel-rich pre-combustion chamber shell 2-1. The outer side of the fuel-rich pre-combustion chamber propellant 2-3 is closely attached to the inner side of the fuel-rich pre-combustion chamber insulation layer 2-2. The inner side of the fuel-rich pre-combustion chamber propellant 2-3 is a through hole. The composition of the fuel-rich pre-combustion chamber propellant 2-3 includes fuel-rich propellant, which is used to generate fuel-rich gas.

[0068] The fuel-rich pre-combustion chamber igniter 2-4 is threadedly installed at the head of the fuel-rich pre-combustion chamber housing 2-1 and extends into the fuel-rich pre-combustion chamber 2. The fuel-rich pre-combustion chamber igniter 2-4 is filled with igniting powder to form high-temperature gas, thereby igniting the fuel-rich pre-combustion chamber propellant column 2-3.

[0069] The connecting panel 1 is provided with a plurality of through holes evenly arranged in the circumferential direction. The front end of the oxygen-enriched pre-combustion chamber shell 3-1 is provided with a plurality of through holes evenly arranged in the circumferential direction. The number of through holes at the front end of the oxygen-enriched pre-combustion chamber shell 3-1 is the same as the number of through holes on the connecting panel 1. There are a plurality of outlet throat liners 2-5 for the fuel-enriched pre-combustion chamber. The plurality of outlet throat liners 2-5 for the fuel-enriched pre-combustion chamber are installed in the through holes at the front end of the connecting panel 1 and the oxygen-enriched pre-combustion chamber shell 3-1 and are evenly arranged in the circumferential direction. The internal contraction and expansion channels of the plurality of outlet throat liners 2-5 for the fuel-enriched pre-combustion chamber 2 and the detonation combustion chamber 4 are used to connect the interior of the fuel-enriched pre-combustion chamber 2 and the detonation combustion chamber 4.

[0070] The engine also includes a central cone 5, which is a hollow conical structure located at the tail of the solid pre-combustion rotating detonation rocket engine. It is connected to the rear end of the oxygen-rich pre-combustion chamber shell 3-1 by threads. The conical outer surface of the central cone 5 is an extension of the contraction and expansion channel of the detonation combustion chamber outlet throat liner 4-3. The conical outer surface of the central cone 5 and the contraction and expansion channel of the detonation combustion chamber outlet throat liner 4-3 together form a plug-type nozzle structure, which is used to further expand and accelerate the detonation products, thereby achieving the effect of thrust enhancement.

[0071] The working principle of the solid pre-combustion rotating detonation rocket engine disclosed in this invention is as follows: The fuel-rich pre-combustion chamber 2 and the oxygen-rich pre-combustion chamber 3 are respectively filled with fuel-rich propellant and oxygen-rich propellant. When the engine is working, the fuel-rich pre-combustion chamber 2 and the oxygen-rich pre-combustion chamber 3 generate fuel-rich gas and oxygen-rich gas respectively. The fuel-rich gas and the oxygen-rich gas are injected into the annular detonation combustion chamber 4 through the outlet throat of the fuel-rich pre-combustion chamber 2 and the outlet throat of the oxygen-rich pre-combustion chamber 3 respectively. They are mixed and undergo chemical reaction in the detonation combustion chamber 4. After the detonation-to-detonation process, a detonation wave is spontaneously formed and propagates continuously and stably in the circumferential direction. The detonation products are discharged from the outlet throat liner 4-3 of the detonation combustion chamber and form thrust.

[0072] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A solid pre-combustion rotating detonation rocket engine, characterized in that: The engine includes a fuel-rich pre-combustion chamber (2), an oxygen-rich pre-combustion chamber (3), a detonation combustion chamber (4), and a connecting panel (1), wherein: The fuel-rich pre-combustion chamber (2) is a cylindrical structure located at the front of the engine and is connected to the connecting panel (1) by bolts. The fuel-rich pre-combustion chamber (2) is filled with fuel-rich pre-combustion chamber propellant and is used to generate fuel-rich gas. The oxygen-enriched pre-combustion chamber is a cylindrical structure located at the rear of the engine and is detachably connected to the connecting panel. The oxygen-enriched pre-combustion chamber is filled with an oxygen-enriched pre-combustion chamber propellant, and the oxygen-enriched pre-combustion chamber is used to generate oxygen-enriched fuel gas. The oxygen-enriched pre-combustion chamber shell (3-1) is a semi-closed cylindrical container. The rear end of the oxygen-enriched pre-combustion chamber (3) is closed, and the front side of the oxygen-enriched pre-combustion chamber shell (3-1) is provided with a plurality of through holes evenly arranged in the circumferential direction. There are multiple oxygen-enriched pre-combustion chamber outlet throat liners (3-5). Multiple oxygen-enriched pre-combustion chamber outlet throat liners (3-5) are installed in the through holes on the side of the oxygen-enriched pre-combustion chamber shell (3-1). The internal contraction and expansion channels of the multiple oxygen-enriched pre-combustion chamber outlet throat liners (3-5) are used to connect the interior of the oxygen-enriched pre-combustion chamber (3) and the detonation combustion chamber (4). The detonation combustion chamber (4) is a cylindrical structure with an annular cross-section, located outside the oxygen-enriched pre-combustion chamber (3), and is detachably connected to the connecting panel (1). The detonation combustion chamber (4) is used to mix the rich combustion gas and the oxygen-enriched gas, so that the rich combustion gas and the oxygen-enriched gas undergo a chemical reaction to form a detonation wave that propagates continuously and stably along the circumference, and serves as an outlet channel for the detonation products. The connecting panel (1) is located in the middle of the engine. The front end of the connecting panel (1) is detachably connected to the fuel-rich pre-combustion chamber (2), and the rear end is detachably connected to the oxygen-rich pre-combustion chamber (3) and the detonation combustion chamber (4). The connecting panel (1), the fuel-rich pre-combustion chamber (2), the oxygen-rich pre-combustion chamber (3), and the detonation combustion chamber (4) are coaxial after installation. The connecting panel (1) is used to connect the fuel-rich pre-combustion chamber (2), the oxygen-rich pre-combustion chamber (3), and the detonation combustion chamber (4) together. The connecting panel (1) is provided with a plurality of through holes evenly arranged in the circumferential direction. The front end of the oxygen-enriched pre-combustion chamber shell (3-1) is provided with a plurality of through holes evenly arranged in the circumferential direction. The number of through holes at the front end of the oxygen-enriched pre-combustion chamber shell (3-1) is the same as the number of through holes on the connecting panel (1). There are a plurality of outlet throat liners (2-5) for the fuel-enriched pre-combustion chamber. The plurality of outlet throat liners (2-5) for the fuel-enriched pre-combustion chamber are installed in the through holes of the connecting panel (1). The internal contraction and expansion channels of the plurality of outlet throat liners (2-5) for the fuel-enriched pre-combustion chamber (2) are used to connect the interior of the fuel-enriched pre-combustion chamber (2) and the detonation combustion chamber (4).

2. The solid pre-combustion rotating detonation rocket engine according to claim 1, characterized in that: The oxygen-enriched pre-combustion chamber (3) includes an oxygen-enriched pre-combustion chamber shell (3-1), an oxygen-enriched pre-combustion chamber insulation layer (3-2), an oxygen-enriched pre-combustion chamber propellant column (3-3), an oxygen-enriched pre-combustion chamber igniter (3-4), and an oxygen-enriched pre-combustion chamber outlet throat liner (3-5). The front end of the oxygen-enriched pre-combustion chamber shell (3-1) is provided with a flange. The front end flange of the oxygen-enriched pre-combustion chamber shell (3-1) is detachably connected to the connecting panel (1), and the front end of the oxygen-enriched pre-combustion chamber shell (3-1) and the connecting panel (1) are engaged by an annular boss groove. The oxygen-enriched pre-combustion chamber insulation layer (3-2) is pasted inside the oxygen-enriched pre-combustion chamber shell (3-1), and the outer side of the oxygen-enriched pre-combustion chamber insulation layer (3-2) is closely attached to the inner wall of the oxygen-enriched pre-combustion chamber shell (3-1) and the rear end face of the connecting panel (1) to prevent the high-temperature gas in the oxygen-enriched pre-combustion chamber (3) from affecting the mechanical properties of the oxygen-enriched pre-combustion chamber shell (3-1). The oxygen-enriched pre-combustion chamber propellant (3-3) is filled inside the oxygen-enriched pre-combustion chamber shell (3-1). The outer side of the oxygen-enriched pre-combustion chamber propellant (3-3) is closely attached to the inner side of the oxygen-enriched pre-combustion chamber insulation layer (3-2). The inner side of the oxygen-enriched pre-combustion chamber propellant (3-3) is a through hole. The composition of the oxygen-enriched pre-combustion chamber propellant (3-3) includes oxygen-enriched propellant, which is used to generate oxygen-enriched gas. The oxygen-enriched pre-combustion chamber igniter (3-4) is threaded onto the connecting panel (1) and extends into the oxygen-enriched pre-combustion chamber (3). The oxygen-enriched pre-combustion chamber igniter (3-4) is filled with igniting powder to form high-temperature gas, thereby igniting the oxygen-enriched pre-combustion chamber propellant column (3-3).

3. A solid pre-combustion rotating detonation rocket engine according to claim 2, characterized in that: The detonation combustion chamber (4) includes a detonation combustion chamber shell (4-1), a detonation combustion chamber insulation layer (4-2), and a detonation combustion chamber outlet throat liner (4-3); The detonation combustion chamber shell (4-1) has a cylindrical structure. The detonation combustion chamber shell (4-1) and the oxygen-enriched pre-combustion chamber shell (3-1) together form an annular cylindrical cavity. A flange is provided at the front end of the detonation combustion chamber shell (4-1). The detonation combustion chamber insulation layer (4-2) is adhered to the inside of the annular cylindrical cavity, and the outer side of the detonation combustion chamber insulation layer (4-2) is closely attached to the inner wall of the annular cylindrical cavity to prevent the high-temperature gas in the detonation combustion chamber (4) from affecting the mechanical properties of the detonation combustion chamber shell (4-1). The outlet throat liner (4-3) of the detonation combustion chamber is located at the tail of the detonation combustion chamber (4). Its inner and outer sides are closely fitted with the oxygen-enriched pre-combustion chamber shell (3-1) and the detonation combustion chamber shell (4-1) respectively. The middle part is a contraction and expansion annular channel. The outlet throat liner (4-3) of the detonation combustion chamber is used as the outlet channel for detonation products.

4. A solid pre-combustion rotating detonation rocket engine according to claim 3, characterized in that: The fuel-rich pre-combustion chamber (2) includes a fuel-rich pre-combustion chamber shell (2-1), a fuel-rich pre-combustion chamber insulation layer (2-2), a fuel-rich pre-combustion chamber propellant charge (2-3), a fuel-rich pre-combustion chamber igniter (2-4), and a fuel-rich pre-combustion chamber outlet throat liner (2-5). The fuel-rich pre-combustion chamber shell (2-1) is a semi-enclosed cylindrical container. The fuel-rich pre-combustion chamber igniter (2-4) is installed at the head of the fuel-rich pre-combustion chamber shell (2-1). A flange is provided at the rear end of the fuel-rich pre-combustion chamber shell (2-1). The rear flange of the fuel-rich pre-combustion chamber shell (2-1) is detachably connected to the connecting panel (1). The rear end of the fuel-rich pre-combustion chamber shell (2-1) and the connecting panel (1) are engaged by an annular boss groove. The heat insulation layer (2-2) of the fuel-rich pre-combustion chamber is attached to the inside of the fuel-rich pre-combustion chamber shell (2-1). The outer side of the heat insulation layer (2-2) of the fuel-rich pre-combustion chamber is closely attached to the inner wall of the fuel-rich pre-combustion chamber shell (2-1) and the front end face of the connecting panel (1) to prevent the high-temperature gas in the fuel-rich pre-combustion chamber (2) from affecting the mechanical properties of the fuel-rich pre-combustion chamber shell (2-1). The fuel-rich pre-combustion chamber propellant (2-3) is filled inside the fuel-rich pre-combustion chamber shell (2-1). The outer side of the fuel-rich pre-combustion chamber propellant (2-3) is closely attached to the inner side of the fuel-rich pre-combustion chamber insulation layer (2-2). The inner side of the fuel-rich pre-combustion chamber propellant (2-3) is a through hole. The fuel-rich pre-combustion chamber propellant (2-3) includes fuel-rich propellant for generating fuel-rich gas. The fuel-rich pre-combustion chamber igniter (2-4) is threaded onto the head of the fuel-rich pre-combustion chamber housing (2-1) and extends into the fuel-rich pre-combustion chamber (2). The fuel-rich pre-combustion chamber igniter (2-4) is filled with igniting powder to form high-temperature gas, thereby igniting the fuel-rich pre-combustion chamber propellant column (2-3).

5. A solid pre-combustion rotating detonation rocket engine according to claim 4, characterized in that: The connecting panel (1), the rear flange of the fuel-rich pre-combustion chamber shell (2-1), the front flange of the oxygen-rich pre-combustion chamber shell (3-1), and the front flange of the detonation combustion chamber shell (4-1) are fastened together by bolts.

6. A solid pre-combustion rotating detonation rocket engine according to claim 3, characterized in that: The engine also includes a central cone (5), which is a hollow conical structure located at the tail of the solid pre-combustion rotating detonation rocket engine. It is connected to the rear end of the oxygen-rich pre-combustion chamber shell (3-1) by threads. The conical outer surface of the central cone (5) is an extension of the contraction and expansion channel of the detonation combustion chamber outlet throat liner (4-3) on the outside. The conical outer surface of the central cone (5) and the contraction and expansion channel of the detonation combustion chamber outlet throat liner (4-3) together form a plug-type nozzle structure, which is used to further expand and accelerate the detonation products, thereby increasing the thrust.

7. A solid pre-combustion rotating detonation rocket engine according to claim 3, characterized in that: An external ignition device is installed on the shell (4-1) of the detonation combustion chamber. It is used to assist in ignition and detonation when the rich combustion gas and the oxygen-rich combustion gas cannot spontaneously detonate and form a detonation wave after being mixed. The external ignition device is a spark plug, explosive, hot jet tube, plasma igniter or other device with ignition function.

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