Solid pre-combustion rotary detonation rocket engine

Abstract

The invention discloses a solid pre-combustion rotary 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, and the fuel-rich pre-combustion chamber is of a cylindrical structure and located on the front portion of the engine; the oxygen-enriched pre-combustion chamber is of a cylindrical structure and located on the rear portion of the engine. The detonation combustion chamber is of a cylindrical structure with an annular cross section and is located on the outer side of the oxygen-enriched pre-combustion chamber. The connecting panel is located in the middle of the engine and used for connecting the rich combustion pre-combustion chamber with the oxygen-rich pre-combustion chamber and the detonation combustion chamber. When the engine works, generated rich oxygen and rich combustion high-temperature fuel gas enter the detonation combustion chamber to be mixed and subjected to chemical reaction, detonation waves which are continuously and stably spread in the circumferential direction are formed, detonation products are discharged from an outlet of the detonation combustion chamber and form thrust, and the engine has the advantages of being high in specific impulse, compact in structure, high in reliability and the like; and the application of a pure solid propellant on the rotary detonation rocket engine can be realized.

Description

Technical Field

[0001] The invention relates to the field of aerospace propulsion technology, and in particular to a solid rotating detonation rocket engine. Background Art

[0002] A rotating detonation rocket engine is a space propulsion device that uses one or more rotating detonation waves to continuously rotate and propagate in an annular combustion chamber to generate thrust. Compared with traditional rocket engines, rotating detonation rocket engines have the following advantages: (1) high thermal cycle efficiency, which can theoretically achieve a greater specific impulse; (2) fast combustion speed and high heat capacity, which can greatly shorten the engine structure length. Based on the above characteristics, rotating detonation technology is expected to provide a more efficient and reliable power source for spacecraft and has broad application prospects. In the past decade, both China and foreign countries have continued to invest resources in the technical research and development of rotating detonation rocket engines. At present, technological breakthroughs have been achieved in many directions, and they are steadily moving towards the goal of engineering application.

[0003] At present, the research and development of rotating detonation rocket engines mainly uses gas or liquid propellants, and the research on the application of solid propellants in rotating detonation rocket engines is relatively scarce. In 2023, Wenbin Wu published a paper titled "Experimental research on solid fuel pre-combustion rotating detonation engine" in the journal "ActaAstronautica" Volume 205, proposing a solid fuel gas rotating detonation engine, which uses a gas generator to generate oxygen-depleted fuel gas, which is injected into a rotating detonation combustion chamber and mixed with oxygen and detonated to form a rotating detonation wave, thereby generating thrust. The feasibility of this scheme has been verified through experiments, but there are still the following shortcomings: (1) The space inside the inner shell of the annular rotating detonation combustion chamber has not been effectively utilized; (2) The gas or liquid oxidizer used in the rotating detonation combustion chamber needs to be equipped with a pressurized injection device, making the engine structure more complicated. Summary of the invention

[0004] In order to solve the problem that solid propellants are difficult to apply in rotating detonation rocket engines, the present invention discloses a solid pre-combustion rotating detonation rocket engine. The specific technical solution is as follows:

[0005] A solid 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 connection panel;

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

[0007] The oxygen-enriched precombustion chamber is a cylindrical structure, located at the rear of the engine, and is detachably connected to the connection panel. The oxygen-enriched precombustion 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-rich pre-combustion chamber, and detachably connected to the connection panel. The detonation combustion chamber is used to mix the fuel-rich gas and the oxygen-rich gas to make the fuel-rich gas and the oxygen-rich gas react chemically 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 face of the connecting panel is detachably connected to the fuel-rich precombustion chamber, the rear end face is detachably connected to the oxygen-rich precombustion chamber and the detonation combustion chamber, and the connecting panel, fuel-rich precombustion chamber, oxygen-rich precombustion chamber, and detonation combustion chamber are coaxial after installation, and the connecting panel is used to connect the fuel-rich precombustion chamber, oxygen-rich precombustion chamber, and detonation combustion chamber together.

[0010] Preferably, the oxygen-enriched precombustion chamber comprises an oxygen-enriched precombustion chamber shell, an oxygen-enriched precombustion chamber insulation layer, an oxygen-enriched precombustion chamber charge, an oxygen-enriched precombustion chamber igniter, and an oxygen-enriched precombustion chamber outlet throat liner;

[0011] The oxygen-enriched precombustion chamber shell is a semi-enclosed cylindrical container, the rear end of the oxygen-enriched precombustion chamber is closed, a plurality of through holes evenly arranged along the circumferential direction are arranged on the side of the oxygen-enriched precombustion chamber shell, a flange is arranged at the front end of the oxygen-enriched precombustion chamber shell, the front end flange of the oxygen-enriched precombustion chamber shell is detachably connected to the connection panel, and the front end of the oxygen-enriched precombustion chamber shell is matched with the connection panel through an annular boss groove;

[0012] The oxygen-enriched precombustion chamber insulation layer is pasted inside the oxygen-enriched precombustion chamber shell, and the outer side of the oxygen-enriched precombustion chamber insulation layer is closely attached to the inner wall of the oxygen-enriched precombustion chamber shell and the rear end surface of the connecting panel, so as to prevent the high-temperature combustion gas in the oxygen-enriched precombustion chamber from affecting the mechanical properties of the oxygen-enriched precombustion chamber shell;

[0013] The oxygen-enriched precombustion chamber grain is loaded inside the oxygen-enriched precombustion chamber shell, the outer side of the oxygen-enriched precombustion chamber grain is closely attached to the inner side of the oxygen-enriched precombustion chamber insulation layer, the inner side of the oxygen-enriched precombustion chamber grain is a through hole, and the composition of the oxygen-enriched precombustion chamber grain includes oxygen-enriched propellant, which is used to generate oxygen-enriched combustion gas;

[0014] The oxygen-enriched precombustion chamber igniter is threadedly mounted on the connection panel and extends into the interior of the oxygen-enriched precombustion chamber. The oxygen-enriched precombustion chamber igniter is filled with ignition powder for forming high-temperature combustion gas, thereby igniting the oxygen-enriched precombustion chamber powder column;

[0015] There are multiple oxygen-rich precombustion chamber outlet throat liners, and the multiple oxygen-rich precombustion chamber outlet throat liners are installed in the through holes on the side of the oxygen-rich precombustion chamber shell and are evenly arranged along the circumferential direction. The internal contraction and expansion channels of the multiple oxygen-rich precombustion chamber outlet throat liners are used to connect the interior of the oxygen-rich precombustion chamber and the detonation combustion chamber.

[0016] Preferably, the detonation combustion chamber comprises 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 circular tubular structure, the detonation combustion chamber shell and the oxygen-enriched pre-combustion chamber shell together form an annular cylindrical cavity, and a flange is provided at the front end of the detonation combustion chamber shell;

[0018] The detonation combustion chamber insulation layer is pasted in the annular cylindrical cavity, and the outer side of the detonation combustion chamber insulation layer is closely attached to the inner wall of the annular cylindrical cavity, so as to prevent the high temperature gas in the detonation combustion chamber from affecting the mechanical properties of the detonation combustion chamber shell;

[0019] The detonation combustion chamber outlet throat liner is located at the tail of the detonation combustion chamber, and its inner and outer sides are tightly matched with the oxygen-rich pre-combustion chamber shell and the detonation combustion chamber shell respectively, with a contracting and expanding annular channel in the middle. The detonation combustion chamber outlet throat liner is used as an outlet channel for detonation products.

[0020] Preferably, the fuel-rich precombustion chamber comprises a fuel-rich precombustion chamber shell, a fuel-rich precombustion chamber insulation layer, a fuel-rich precombustion chamber charge, a fuel-rich precombustion chamber igniter, and a fuel-rich precombustion chamber outlet throat liner;

[0021] The rich-fuel precombustion chamber shell is a semi-enclosed cylindrical container, the rich-fuel precombustion chamber igniter is installed at the head of the rich-fuel precombustion chamber shell, a flange is provided at the rear end of the rich-fuel precombustion chamber shell, the rear end flange of the rich-fuel precombustion chamber shell is detachably connected to the connection panel, and the rear end of the rich-fuel precombustion chamber shell is matched with the connection panel through an annular boss groove;

[0022] The fuel-rich precombustion chamber insulation layer is pasted inside the fuel-rich precombustion chamber shell, and the outer side of the fuel-rich precombustion chamber insulation layer is in close contact with the inner wall of the fuel-rich precombustion chamber shell and the front end surface of the connecting panel, so as to prevent the high-temperature gas in the fuel-rich precombustion chamber from affecting the mechanical properties of the fuel-rich precombustion chamber shell;

[0023] The fuel-rich precombustion chamber grain is loaded inside the fuel-rich precombustion chamber shell, the outer side of the fuel-rich precombustion chamber grain is closely attached to the inner side of the fuel-rich precombustion chamber insulation layer, the inner side of the fuel-rich precombustion chamber grain is a through hole, and the composition of the fuel-rich precombustion chamber grain includes fuel-rich propellant, which is used to generate fuel-rich combustion gas;

[0024] The rich precombustion chamber igniter is threadedly mounted on the head of the rich precombustion chamber housing and extends into the rich precombustion chamber. The rich precombustion chamber igniter is filled with ignition powder for forming high-temperature combustion gas, thereby igniting the rich precombustion chamber charge column.

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

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

[0027] Preferably, the engine also includes a center cone, which is a hollow conical structure and is 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 through a thread. The conical outer surface of the center cone is an outer extension of the contraction and expansion channel of the detonation combustion chamber outlet throat liner. The conical outer surface of the center cone and the contraction and expansion channel of the detonation combustion chamber outlet throat liner together form a plug nozzle structure, which is used to further accelerate the expansion of the detonation products, thereby achieving the effect of thrust enhancement.

[0028] Alternatively, an external ignition device is installed in a hole on the detonation combustion chamber shell to assist in ignition and detonation when the fuel-rich gas and the oxygen-rich 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.

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

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

[0031] (1) The solid pre-combustion rotating detonation rocket engine provided by the present invention utilizes detonation combustion to generate thrust, and 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 is designed as an oxygen-rich combustion chamber, thereby effectively reducing the negative mass and making the engine structure more compact;

[0033] (3) The solid pre-combustion rotating detonation rocket engine provided by the present invention adopts two solid pre-combustion chambers and does not require an additional injection device, thereby reducing the complexity of the engine structure and improving the reliability of the engine structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] In order to more clearly illustrate the technical solutions disclosed in the present invention, the following briefly introduces the drawings required to be used in some embodiments disclosed in the present invention. Obviously, the drawings described below are only drawings of some embodiments disclosed in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings. In addition, the drawings described below can be regarded as schematic diagrams, and are not limitations on the actual size of the products involved in the embodiments disclosed in the present invention, the actual process of the method, etc.

[0035] Figure 1 It is a schematic diagram of the appearance of a solid pre-combustion rotating detonation rocket engine provided in the present invention;

[0036] Figure 2 It is a longitudinal cross-sectional view of a solid pre-combustion rotating detonation rocket engine provided by the present invention;

[0037] Figure 3 It is a transverse cross-sectional view of a solid pre-combustion rotating detonation rocket engine provided in the present invention.

[0038] The accompanying drawings are marked as follows:

[0039] 1. Connect the panel;

[0040] 2. Rich precombustion chamber; 2-1. Rich precombustion chamber shell; 2-2. Rich precombustion chamber insulation layer; 2-3. Rich precombustion chamber powder column; 2-4. Rich precombustion chamber igniter; 2-5. Rich precombustion chamber outlet throat lining;

[0041] 3. Oxygen-enriched precombustion chamber; 3-1. Oxygen-enriched precombustion chamber shell; 3-2. Oxygen-enriched precombustion chamber insulation layer; 3-3. Oxygen-enriched precombustion chamber charge column; 3-4. Oxygen-enriched precombustion chamber igniter; 3-5. Oxygen-enriched precombustion chamber outlet throat lining;

[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 lining;

[0043] 5. Center cone. DETAILED DESCRIPTION

[0044] The embodiments disclosed in the present invention will be further described in detail below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0045] Embodiment 1

[0046] The solid pre-combustion rotating detonation rocket engine provided by the present invention has the following appearance: Figure 1 shown.

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

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

[0049] A longitudinal cross-sectional view of a solid pre-combustion rotating detonation rocket engine provided by the present invention is as follows Figure 2 As shown, the engine further includes an oxygen-rich pre-combustion chamber 3, a detonation combustion chamber 4, and a connection 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 connection panel 1 by bolts. The oxygen-enriched pre-combustion chamber 3 is filled with oxygen-enriched propellant, and the oxygen-enriched pre-combustion chamber 3 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-rich pre-combustion chamber 3, and is fastened to the connection panel 1 by bolts. The detonation combustion chamber 4 is used to mix the fuel-rich gas and the oxygen-rich gas, so that the fuel-rich gas and the oxygen-rich 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 part of the engine, the front end face of the connecting panel 1 is fastened to the fuel-rich precombustion chamber 2 by bolts, the rear end face is fastened to the oxygen-rich precombustion chamber 3 and the detonation combustion chamber 4 by bolts, and the connecting panel 1, fuel-rich precombustion chamber 2, oxygen-rich precombustion chamber 3, and detonation combustion chamber 4 are coaxial after installation, and the connecting panel 1 is used to connect the fuel-rich precombustion chamber 2, oxygen-rich precombustion chamber 3, and detonation combustion chamber 4 together.

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

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

[0055] The oxygen-enriched precombustion chamber shell 3-1 is a semi-enclosed cylindrical container, the rear end of the oxygen-enriched precombustion chamber 3 is closed, the side of the oxygen-enriched precombustion chamber shell 3-1 is provided with a plurality of through holes evenly arranged along the circumferential direction, the front end of the oxygen-enriched precombustion chamber shell 3-1 is provided with a flange, the front end flange of the oxygen-enriched precombustion chamber shell 3-1 is fastened to the connection panel 1 by bolts, and the front end of the oxygen-enriched precombustion chamber shell 3-1 is matched with the connection panel 1 by an annular boss groove;

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

[0057] The oxygen-enriched precombustion chamber grain 3-3 is loaded inside the oxygen-enriched precombustion chamber shell 3-1, the outer side of the oxygen-enriched precombustion chamber grain 3-3 is closely attached to the inner side of the oxygen-enriched precombustion chamber insulation layer 3-2, the inner side of the oxygen-enriched precombustion chamber grain 3-3 is a through hole, and the components of the oxygen-enriched precombustion chamber grain 3-3 include oxygen-enriched propellant, which is used to generate oxygen-enriched combustion gas;

[0058] The oxygen-enriched pre-combustion chamber igniter 3-4 is threadedly mounted on the connection panel 1 and extends into the interior of the oxygen-enriched pre-combustion chamber 3. The oxygen-enriched pre-combustion chamber igniter 3-4 is filled with ignition powder for forming high-temperature combustion gas, thereby igniting the oxygen-enriched pre-combustion chamber charge 3-3;

[0059] There are multiple oxygen-rich precombustion chamber outlet throat liners 3-5, and the multiple oxygen-rich precombustion chamber outlet throat liners 3-5 are installed in the through holes on the side of the oxygen-rich precombustion chamber shell 3-1 and are evenly arranged along the circumferential direction. The internal contraction and expansion channels of the multiple oxygen-rich precombustion chamber outlet throat liners 3-5 are used to connect the interior of the oxygen-rich precombustion 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 circular tubular structure, and 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, and an external ignition device is installed in a hole on the detonation combustion chamber shell 4-1, which is used to assist in ignition and detonation when the fuel-rich gas and the oxygen-enriched gas cannot spontaneously detonate to form a detonation wave after being mixed. 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 pasted in 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, so as 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 detonation combustion chamber outlet throat liner 4-3 is located at the tail of the detonation combustion chamber 4, and its inner and outer sides are tightly matched with the oxygen-rich pre-combustion chamber shell 3-1 and the detonation combustion chamber shell 4-1 respectively, with a contracting and expanding annular channel in the middle. The detonation combustion chamber outlet throat liner 4-3 is used as an outlet channel for detonation products.

[0064] The rich precombustion chamber 2 includes a rich precombustion chamber shell 2-1, a rich precombustion chamber insulation layer 2-2, a rich precombustion chamber charge 2-3, a rich precombustion chamber igniter 2-4, and a rich precombustion chamber outlet throat liner 2-5;

[0065] The fuel-rich precombustion chamber shell 2-1 is a semi-enclosed cylindrical container, the fuel-rich precombustion chamber igniter 2-4 is installed at the head of the fuel-rich precombustion chamber shell 2-1, and a flange is provided at the rear end of the fuel-rich precombustion chamber shell 2-1. The rear end flange of the fuel-rich precombustion chamber shell 2-1 is fastened to the connection panel 1 by bolts, and the rear end of the fuel-rich precombustion chamber shell 2-1 is matched with the connection panel 1 by an annular boss groove;

[0066] The fuel-rich precombustion chamber insulation layer 2-2 is pasted inside the fuel-rich precombustion chamber shell 2-1, and the outer side of the fuel-rich precombustion chamber insulation layer 2-2 is in close contact with the inner wall of the fuel-rich precombustion chamber shell 2-1 and the front end surface of the connecting panel 1, so as to prevent the high-temperature combustion gas in the fuel-rich precombustion chamber 2 from affecting the mechanical properties of the fuel-rich precombustion chamber shell 2-1;

[0067] The fuel-rich precombustion chamber grain 2-3 is loaded inside the fuel-rich precombustion chamber shell 2-1, the outer side of the fuel-rich precombustion chamber grain 2-3 is close to the inner side of the fuel-rich precombustion chamber insulation layer 2-2, the inner side of the fuel-rich precombustion chamber grain 2-3 is a through hole, and the composition of the fuel-rich precombustion chamber grain 2-3 includes fuel-rich propellant, which is used to generate fuel-rich combustion gas;

[0068] The rich precombustion chamber igniter 2-4 is threadedly mounted on the head of the rich precombustion chamber housing 2-1 and extends into the rich precombustion chamber 2. The rich precombustion chamber igniter 2-4 is filled with ignition powder to form high-temperature combustion gas, thereby igniting the rich precombustion chamber charge 2-3.

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

[0070] The engine also includes a center cone 5, which is a hollow conical structure and is 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 through a thread. The conical outer surface of the center cone 5 is an outer extension of the contraction and expansion channel of the detonation combustion chamber outlet throat liner 4-3. The conical outer surface of the center cone 5 and the contraction and expansion channel of the detonation combustion chamber outlet throat liner 4-3 together form a plug nozzle structure, which is used to further accelerate the expansion of the detonation products, thereby achieving the effect of thrust enhancement.

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

[0072] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A solid pre-combustion rotating detonation rocket engine, characterized in that: The engine comprises a fuel-rich pre-combustion chamber (2), an oxygen-rich pre-combustion chamber (3), a detonation combustion chamber (4), and a connection panel (1), wherein: The fuel-rich precombustion chamber (2) is a cylindrical structure, located at the front of the engine, and connected to the connection panel (1) by bolts. The fuel-rich precombustion chamber (2) is filled with fuel-rich propellant, and the fuel-rich precombustion chamber (2) is used to generate fuel-rich combustion gas; The detonation combustion chamber (4) is a cylindrical structure with an annular cross section, is located outside the oxygen-rich pre-combustion chamber (3), and is detachably connected to the connection panel (1). The detonation combustion chamber (4) is used to mix the fuel-rich gas and the oxygen-rich gas to cause a chemical reaction between the fuel-rich gas and the oxygen-rich gas to form a detonation wave that propagates continuously and stably in the circumferential direction, and serves as an outlet channel for the detonation products. The connection panel (1) is located in the middle of the engine, the front end face of the connection panel (1) is detachably connected to the fuel-rich precombustion chamber (2), and the rear end face is detachably connected to the oxygen-rich precombustion chamber (3) and the detonation combustion chamber (4), and the connection panel (1), the fuel-rich precombustion chamber (2), the oxygen-rich precombustion chamber (3), and the detonation combustion chamber (4) are coaxial after installation, and the connection panel (1) is used to connect the fuel-rich precombustion chamber (2), the oxygen-rich precombustion chamber (3), and the detonation combustion chamber (4) together.

2. A solid pre-combustion rotating detonation rocket engine according to claim 1, characterized in that: The oxygen-enriched precombustion chamber (3) comprises an oxygen-enriched precombustion chamber shell (3-1), an oxygen-enriched precombustion chamber insulation layer (3-2), an oxygen-enriched precombustion chamber charge (3-3), an oxygen-enriched precombustion chamber igniter (3-4), and an oxygen-enriched precombustion chamber outlet throat liner (3-5); The oxygen-enriched precombustion chamber shell (3-1) is a semi-enclosed cylindrical container, the rear end of the oxygen-enriched precombustion chamber (3) is closed, the side of the oxygen-enriched precombustion chamber shell (3-1) is provided with a plurality of through holes evenly arranged along the circumferential direction, the front end of the oxygen-enriched precombustion chamber shell (3-1) is provided with a flange, the front end flange of the oxygen-enriched precombustion chamber shell (3-1) is detachably connected to the connection panel (1), and the front end of the oxygen-enriched precombustion chamber shell (3-1) is matched with the connection panel (1) through an annular boss groove; The oxygen-enriched precombustion chamber insulation layer (3-2) is adhered to the inside of the oxygen-enriched precombustion chamber shell (3-1), and the outer side of the oxygen-enriched precombustion chamber insulation layer (3-2) is in close contact with the inner wall of the oxygen-enriched precombustion chamber shell (3-1) and the rear end surface of the connecting panel (1), so as to prevent the high-temperature combustion gas in the oxygen-enriched precombustion chamber (3) from affecting the mechanical properties of the oxygen-enriched precombustion chamber shell (3-1); The oxygen-enriched precombustion chamber grain (3-3) is loaded inside the oxygen-enriched precombustion chamber shell (3-1), the outer side of the oxygen-enriched precombustion chamber grain (3-3) is in close contact with the inner side of the oxygen-enriched precombustion chamber insulation layer (3-2), the inner side of the oxygen-enriched precombustion chamber grain (3-3) is a through hole, and the components of the oxygen-enriched precombustion chamber grain (3-3) include oxygen-enriched propellant, which is used to generate oxygen-enriched combustion gas; The oxygen-enriched pre-combustion chamber igniter (3-4) is threadedly mounted on the connection panel (1) and extends into the interior of the oxygen-enriched pre-combustion chamber (3); the oxygen-enriched pre-combustion chamber igniter (3-4) is filled with ignition powder for forming high-temperature combustion gas, thereby igniting the oxygen-enriched pre-combustion chamber powder column (3-3); There are multiple oxygen-rich precombustion chamber outlet throat liners (3-5), and the multiple oxygen-rich precombustion chamber outlet throat liners (3-5) are installed in the through holes on the side of the oxygen-rich precombustion chamber shell (3-1) and are evenly arranged along the circumferential direction. The internal contraction and expansion channels of the multiple oxygen-rich precombustion chamber outlet throat liners (3-5) are used to connect the interior of the oxygen-rich precombustion chamber (3) and the detonation combustion chamber (4).

3. A solid pre-combustion rotating detonation rocket engine according to claim 2, characterized in that: The detonation combustion chamber (4) comprises 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) is a circular tubular structure, the detonation combustion chamber shell (4-1) and the oxygen-enriched pre-combustion chamber shell (3-1) together form an annular cylindrical cavity, and 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 pasted in the annular cylindrical cavity, and the outer side of the detonation combustion chamber insulation layer (4-2) is in close contact with the inner wall of the annular cylindrical cavity, so as to prevent the high-temperature combustion gas in the detonation combustion chamber (4) from affecting the mechanical properties of the detonation combustion chamber shell (4-1); The detonation combustion chamber outlet throat liner (4-3) is located at the tail of the detonation combustion chamber (4), and its inner and outer sides are respectively tightly matched with the oxygen-enriched pre-combustion chamber shell (3-1) and the detonation combustion chamber shell (4-1), and the middle is a contraction-expansion annular channel. The detonation combustion chamber outlet throat liner (4-3) is used as an outlet channel for detonation products.

4. A solid pre-combustion rotating detonation rocket engine according to claim 3, characterized in that: The rich precombustion chamber (2) comprises a rich precombustion chamber shell (2-1), a rich precombustion chamber insulation layer (2-2), a rich precombustion chamber charge (2-3), a rich precombustion chamber igniter (2-4), and a rich precombustion chamber outlet throat liner (2-5); The rich-fuel precombustion chamber shell (2-1) is a semi-enclosed cylindrical container, the rich-fuel precombustion chamber igniter (2-4) is installed at the head of the rich-fuel precombustion chamber shell (2-1), the rear end of the rich-fuel precombustion chamber shell (2-1) is provided with a flange, the rear end flange of the rich-fuel precombustion chamber shell (2-1) is detachably connected to the connection panel (1), and the rear end of the rich-fuel precombustion chamber shell (2-1) is matched with the connection panel (1) through an annular boss groove; The fuel-rich precombustion chamber insulation layer (2-2) is adhered to the inside of the fuel-rich precombustion chamber shell (2-1), and the outer side of the fuel-rich precombustion chamber insulation layer (2-2) is in close contact with the inner wall of the fuel-rich precombustion chamber shell (2-1) and the front end surface of the connecting panel (1), so as to prevent the high-temperature combustion gas in the fuel-rich precombustion chamber (2) from affecting the mechanical properties of the fuel-rich precombustion chamber shell (2-1); The fuel-rich precombustion chamber charge (2-3) is loaded inside the fuel-rich precombustion chamber shell (2-1), the outer side of the fuel-rich precombustion chamber charge (2-3) is in close contact with the inner side of the fuel-rich precombustion chamber insulation layer (2-2), the inner side of the fuel-rich precombustion chamber charge (2-3) is a through hole, and the components of the fuel-rich precombustion chamber charge (2-3) include fuel-rich propellant, which is used to generate fuel-rich combustion gas; The rich precombustion chamber igniter (2-4) is threadedly mounted on the head of the rich precombustion chamber housing (2-1) and extends into the rich precombustion chamber (2). The rich precombustion chamber igniter (2-4) is filled with ignition powder for forming high-temperature combustion gas, thereby igniting the rich precombustion chamber powder column (2-3); The connection panel (1) is provided with a plurality of through holes evenly arranged along the circumferential direction, and the front end of the oxygen-rich precombustion chamber shell (3-1) is provided with a plurality of through holes evenly arranged along the circumferential direction. The number of through holes at the front end of the oxygen-rich precombustion chamber shell (3-1) is the same as the number of through holes on the connection panel (1). There are a plurality of rich fuel precombustion chamber outlet throat liners (2-5). The plurality of rich fuel precombustion chamber outlet throat liners (2-5) are installed in the through holes at the front ends of the connection panel (1) and the oxygen-rich precombustion chamber shell (3-1) and are evenly arranged along the circumferential direction. The internal contraction and expansion channels of the plurality of rich fuel precombustion chamber outlet throat liners (2-5) are used to connect the interior of the rich fuel precombustion chamber (2) and the detonation combustion chamber (4).

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

6. A solid pre-combustion rotating detonation rocket engine according to claim 3, characterized in that: The engine also includes a center cone (5), which is a hollow conical structure and is 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) through a thread. The conical outer side surface of the center 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 side surface of the center cone (5) and the contraction and expansion channel of the detonation combustion chamber outlet throat liner (4-3) together form a plug nozzle structure for further accelerating the expansion of 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 in a hole on the detonation combustion chamber shell (4-1) for assisting ignition and detonation when the fuel-rich gas and the oxygen-rich gas cannot spontaneously detonate to 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.

Images