Double-fuel-gas-generator type solid rocket rotary detonation engine

Abstract

The invention relates to a double-fuel-gas-generator type solid rocket rotating detonation engine which comprises a shell, an oxygen-poor fuel gas generator, an oxygen-rich fuel gas generator and a detonating tube. The oxygen-poor fuel gas generator and the oxygen-rich fuel gas generator are installed in the shell, and the detonating tube is installed on the shell. An oxygen-deficient solid propellant for generating primary oxygen-deficient fuel gas is arranged in the oxygen-deficient fuel gas generator; an oxygen-enriched solid propellant for generating primary oxygen-enriched fuel gas is arranged in the oxygen-enriched fuel gas generator; the oxygen-deficient fuel gas generator is provided with a first channel for outputting the primary oxygen-deficient fuel gas; the oxygen-enriched gas generator is provided with a second channel for outputting the primary oxygen-enriched gas; the first channel is communicated with the second channel, so that the primary oxygen-poor fuel gas and the primary oxygen-rich fuel gas are mixed to form premixed gas; and the detonating tube is used for detonating the premixed gas. The structure is simple, no complex supply system exists, maintenance and operation are convenient, the propellant can be stored for a long time, and response is rapid.

Description

Technical Field

[0001] The invention relates to the field of aerospace, and in particular to a dual-gas generator type solid rocket rotating detonation engine. Background Art

[0002] Solid rocket engines rely on the combustion of solid propellants to produce high-temperature and high-pressure combustion gas, which is discharged at high speed after energy conversion through the nozzle, generating powerful thrust. It is mainly composed of a combustion chamber shell, solid propellant charge, and nozzle. Solid rocket engines have the advantages of simple structure, reliable operation, simple use, and good maneuverability.

[0003] At present, there are two types of combustion waves in nature: one is the deflagration wave and the other is the detonation wave. The deflagration wave usually propagates toward the unburned mixture at a relatively low speed, and is controlled by the mass diffusion and heat diffusion of laminar or turbulent flow, which is approximately an isobaric combustion process. The detonation wave is a combustion method in which the shock wave is tightly coupled with the reaction surface and propagates at supersonic speed. It has theoretical advantages such as self-pressurization, fast heat release rate, and high thermal cycle efficiency. The performance of solid rocket engines based on the deflagration combustion method is currently close to the theoretical limit and it is difficult to further improve it significantly. The solid rocket engine using the detonation combustion method is expected to achieve high thermal cycle efficiency and lightweight structure.

[0004] Liquid fuel rotating detonation rocket engines, which have developed rapidly in recent years, generally carry oxidizers and fuels separately, and use a relatively complex supply system to adjust the flow in real time. The engine system is complex and has many parts. Compared with solid rocket engines, liquid fuel rotating detonation rocket engines do not have advantages in rapid response, maintenance and operation, and are difficult to use in aircraft power systems that require high reliability, simple operation and fast response. In addition, there are more mature solid powder fuel detonation rocket engines, in which powder fuel and powder oxidizer are carried separately, and use a set of powder supply devices respectively, and the system is still relatively complex.

[0005] Therefore, the existing rotating detonation rocket engine has the following main disadvantages: (1) For liquid fuel rotating detonation rocket engines, the oxidizer and fuel are usually carried separately, and a relatively complex supply system is used to adjust the flow rate in real time. The engine system is complex, with many parts, slow response, and complex maintenance and operation; (2) For solid powder fuel detonation rocket engines, powder fuel and powder oxidizer are carried separately, and each requires a relatively complex set of powder supply and fluidization devices, which still makes it have the defects of complex structure, maintenance and operation. Summary of the invention

[0006] The object of the present invention is to provide a dual-gas generator type solid rocket rotating detonation engine.

[0007] To achieve the above-mentioned purpose, the present invention provides a dual-gas generator type solid rocket rotating detonation engine, comprising: a housing, an oxygen-depleted gas generator and an oxygen-rich gas generator installed in the housing, and a detonator installed on the housing; The oxygen-depleted fuel gas generator is provided with an oxygen-depleted solid propellant for generating a primary oxygen-depleted fuel gas; The oxygen-enriched fuel gas generator is provided with an oxygen-enriched solid propellant for generating a primary oxygen-enriched fuel gas; The oxygen-depleted fuel gas generator is provided with a first channel for outputting the primary oxygen-depleted fuel gas; The oxygen-enriched fuel gas generator is provided with a second channel for outputting the primary oxygen-enriched fuel gas; The first channel is connected to the second channel so as to be used for mixing the primary oxygen-depleted fuel gas and the primary oxygen-rich fuel gas to form a premixed gas; The detonator is used to detonate the premixed gas.

[0008] According to one aspect of the present invention, along the output direction of the primary oxygen-enriched fuel gas, the second channel includes a contraction section and an expansion section that are connected in sequence; A gas outlet communicating with the first channel is provided on the wall surface of the expansion section.

[0009] According to one aspect of the present invention, the primary oxygen-depleted fuel gas and the primary oxygen-rich fuel gas are mixed at a flow rate of equivalence ratio of 1 to form the premixed gas.

[0010] According to one aspect of the present invention, the housing comprises: a generator installation section for arranging the oxygen-lean gas generator and the oxygen-rich gas generator, a detonation combustion chamber section for constructing a detonation combustion chamber, and a tail nozzle for accelerating the expansion and discharge of combustion products; The generator installation section, the detonation combustion chamber section and the tail nozzle are coaxially arranged in sequence; The oxygen-depleted fuel gas generator and the oxygen-rich fuel gas generator are coaxially installed in the generator installation section; The second passage is arranged to communicate with the detonation combustion chamber; The detonator is installed in the detonation combustion chamber section.

[0011] According to one aspect of the present invention, the oxygen-depleted fuel gas generator is a cylindrical generator; The oxygen-enriched fuel gas generator is a ring-shaped generator; The oxygen-rich gas generator is disposed around the oxygen-poor gas generator.

[0012] According to one aspect of the present invention, the oxygen-depleted fuel gas generator comprises: a first filling chamber section, a first gas collecting chamber section and a central cone; The first filling cavity section and the first gas collecting cavity section are coaxially arranged to be interconnected; The first filling cavity section is a hollow cylinder with one end open and the other end closed; The first gas collecting chamber section is a hollow cylinder with one end open and the other end closed; The open end of the first filling cavity section is connected to the open end of the first gas collecting cavity section; The central cone is disposed in the first gas collecting cavity section, and the central cone is coaxially fixed to the closed end of the first gas collecting cavity section with the first gas collecting cavity section; The tip of the central cone is opposite to the first filling cavity section; The first channel is disposed on a side wall of the first gas collection chamber segment, and the first channel is disposed adjacent to a closed end of the first gas collection chamber segment; The first channel is arranged to be inclined relative to the axial direction of the first gas collecting chamber section, and its inclination angle is consistent with the generatrix angle of the central cone.

[0013] According to one aspect of the present invention, the axial angle between the first channel and the first gas collecting chamber section is 45° to 60°; Along the axial direction of the first gas collecting cavity section, the first channel is adjacent to the large diameter end of the central cone, or a portion of the inner wall surface of the first channel is aligned with the outer side surface of the large diameter end of the central cone; A plurality of first channels are evenly spaced along the circumference of the first gas collecting cavity segment.

[0014] According to one aspect of the present invention, the oxygen-enriched fuel gas generator comprises: a second filling chamber section, a second gas collecting chamber section and an annular channel member for forming the second channel; The second filling cavity section and the second gas collecting cavity section are coaxially arranged to be interconnected; The second filling cavity section is a hollow annular cylinder with one end open and the other end closed; The second gas collecting chamber section is a hollow annular cylinder with one end open at both ends; The open end of the second filling cavity section is connected to the second gas collecting cavity section; The annular channel member is disposed in the second gas collecting chamber segment, and the annular channel member is coaxially fixed with the second gas collecting chamber segment at an end away from the second filling chamber segment; The second channel is coaxially arranged with the second gas collecting chamber section; The annular channel member is provided with a transition channel for connecting the first channel and the gas outlet.

[0015] According to one aspect of the present invention, the second filling cavity segment is coaxially arranged on the outside of the first filling cavity segment, and the second gas collecting cavity segment is coaxially arranged on the outside of the first gas collecting cavity segment; One end of the second gas collection chamber section away from the second filling chamber section is arranged flush with one end of the first gas collection chamber section away from the first filling chamber section; or, The oxygen-enriched fuel gas generator is coaxially arranged on the outside of the first gas collecting cavity section with the first gas collecting cavity section; One end of the second gas collection chamber section away from the second filling chamber section is arranged flush with one end of the first gas collection chamber section away from the first filling chamber section.

[0016] According to one aspect of the present invention, the inner side surfaces of the first filling cavity section and the first gas collecting cavity section are respectively provided with a first high-silicon-oxygen thermal insulation lining; The inner sides of the second filling cavity section and the second gas collecting cavity section are respectively provided with a second high-silicon-oxygen thermal insulation lining; The oxygen-deficient solid propellant comprises: a first solid propellant body and a first coating sleeve coated on the outside of the first solid propellant body; The oxygen-enriched solid propellant comprises: a second solid propellant body and a second coating sleeve coated on the outside of the second solid propellant body; The detonator is connected to the detonation combustion chamber section at a tangential position; The inner wall of the detonator tube is designed with a coil spring; The annular channel member is a Laval nozzle and is made of piezoelectric ceramic material.

[0017] According to one solution of the present invention, the structure of the present invention is simple and reliable. By coaxially arranging the oxygen-depleted gas generator and the oxygen-rich gas generator and adopting the method of surrounding the oxygen-depleted gas generator with the oxygen-rich gas generator, the overall structure is effectively simplified, and the gas passages between them can be flexibly and conveniently arranged, thereby greatly reducing the overall structural complexity.

[0018] According to a solution of the present invention, the structure is simple, there is no complicated supply system, the operation is reliable, the maintenance and operation are convenient, the propellant can be stored for a long time, and the response is rapid.

[0019] According to one solution of the present invention, the dual gas generators used in the present invention can work separately and independently, have the advantages of not affecting each other, can work continuously after one ignition, and have extremely high working reliability.

[0020] According to one solution of the present invention, two gas generators work to generate oxygen-depleted gas and oxygen-rich gas respectively, wherein the oxygen-depleted gas is mainly fuel, and the oxygen-rich gas is mainly oxidant, and after the two are mixed, they can further react to release energy for a secondary time, so that this solution has more abundant thrust and can have a wider range of uses.

[0021] According to one scheme of the present invention, the present invention utilizes oxygen-depleted and oxygen-rich propellants to be loaded separately in two gas generators, and the matching of fuel and oxidizer is achieved by designing appropriate propellant parameters and gas generator structure, which can give full play to the performance advantages of solid rocket engines based on solid propellants, and help solve the problem that traditional solid rocket engine configurations are difficult to achieve detonation combustion. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 is a structural diagram schematically showing a dual-gas generator type solid rocket rotating detonation engine according to an embodiment of the present invention; Figure 2 is a structural diagram schematically showing a dual-gas generator type solid rocket rotating detonation engine according to another embodiment of the present invention; Figure 3 The figure schematically shows the installation structure of the detonator and the shell according to one embodiment of the present invention. DETAILED DESCRIPTION

[0023] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0024] When describing the embodiments of the present invention, the orientation or positional relationship expressed by the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the orientation or positional relationship shown in the relevant drawings and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operate in a specific orientation. Therefore, the above terms should not be understood as limiting the present invention.

[0025] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments cannot be described one by one here, but the embodiments of the present invention are not therefore limited to the following embodiments.

[0026] Combination Figure 1 and Figure 3 As shown, according to one embodiment of the present invention, a dual-gas generator type solid rocket rotating detonation engine of the present invention includes: an outer shell 11, an oxygen-lean gas generator 12 and an oxygen-rich gas generator 13 installed in the outer shell 11, and a detonator 14 installed on the outer shell 11; in this embodiment, the oxygen-lean gas generator 12 is provided with an oxygen-lean solid propellant 12b for generating a primary oxygen-lean gas 12a; the oxygen-rich gas generator 13 is provided with an oxygen-rich solid propellant 13b for generating a primary oxygen-rich gas 13a. Furthermore, the oxygen-depleted gas generator 12 is provided with a first channel 12c for outputting the primary oxygen-depleted gas 12a; the oxygen-rich gas generator 13 is provided with a second channel 13c for outputting the primary oxygen-rich gas 13a; wherein the first channel 12c is connected to the second channel 13c so as to be used for mixing the primary oxygen-depleted gas 12a and the primary oxygen-rich gas 13a to form a premixed gas; in this embodiment, the first channel 12c is a hole channel, and the second channel 13c is an annular channel, thereby, the way in which the first channel 12c and the second channel 13c are connected can form a hole-slit mixing method to form a premixed gas.

[0027] In this embodiment, the detonator 14 is used to detonate the premixed gas, whereby the detonator 14 is ignited and detonated to generate a strong hot jet to detonate the premixed gas, so that the premixed gas forms a continuous rotating detonation wave to achieve rotating detonation combustion of the premixed gas, thereby achieving the effect of secondary energy release.

[0028] like Figure 1 As shown, according to one embodiment of the present invention, along the output direction of the primary oxygen-enriched fuel gas 13a, the second channel 13c includes a contraction section 13c1 and an expansion section 13c2 which are connected in sequence; wherein, the wall surface of the expansion section 13c2 has a fuel gas outlet which is connected to the first channel 12c.

[0029] By means of the above arrangement, by arranging the gas outlet of the primary oxygen-depleted gas 12a on the expansion wall surface of the expansion section 13c2 of the second channel 13c, the mixing distance of the primary oxygen-depleted gas 12a and the primary oxygen-rich gas 13a can be made longer, which is more conducive to forming a uniformly mixed premixed gas.

[0030] like Figure 1 As shown, according to one embodiment of the present invention, the primary oxygen-depleted fuel gas 12a and the primary oxygen-rich fuel gas 13a are mixed at a flow rate of an equivalence ratio of 1 to form a premixed gas; wherein the equivalence ratio of 1 means that the ratio of fuel and oxidant just meets the stoichiometric ratio required for complete combustion, there is no excess fuel or oxidant, and theoretically no excess oxygen or unburned fuel remains during the combustion process.

[0031] Through the above arrangement, the full combustion of the primary oxygen-depleted fuel gas 12a and the primary oxygen-rich fuel gas 13a is effectively guaranteed, and the combustion and working performance of the present invention is fully guaranteed.

[0032] like Figure 1 As shown, according to one embodiment of the present invention, the housing 11 includes: a generator installation section 11a for arranging an oxygen-depleted gas generator 12 and an oxygen-rich gas generator 13, a detonation combustion chamber section 11b for constructing a detonation combustion chamber, and a tail nozzle 11c for accelerating the expansion and discharge of combustion products; in this embodiment, the generator installation section 11a, the detonation combustion chamber section 11b and the tail nozzle 11c are coaxially arranged in sequence; in this embodiment, the generator installation section 11a, the detonation combustion chamber section 11b and the tail nozzle 11c are hollow cylindrical structures. Among them, the generator installation section 11a and the detonation combustion chamber section 11b can be straight cylinder structures respectively; and the tail nozzle 11c is a variable diameter cylindrical structure, and the diameter of the tail nozzle 11c is first reduced and then increased in the direction away from the detonation combustion chamber section 11b, so as to realize the expansion and accelerated discharge of the premixed gas after the secondary combustion to generate thrust.

[0033] In this embodiment, the oxygen-depleted gas generator 12 and the oxygen-rich gas generator 13 are coaxially installed in the generator installation section 11a; wherein, the second channel 13c of the oxygen-rich gas generator 13 is connected to the detonation combustion chamber; thus, the primary oxygen-depleted gas 12a can be fully mixed with the primary oxygen-rich gas 13a at the outlet position of the second channel 13c through the first channel 12c, and the premixed gas formed by the mixing enters the detonation combustion chamber for ignition and detonation of the detonator 14. Furthermore, the detonator 14 is installed in the detonation combustion chamber section 11b to ignite the premixed gas entering the detonation combustion chamber.

[0034] like Figure 1 As shown, according to one embodiment of the present invention, the oxygen-depleted gas generator 12 is a cylindrical generator; the oxygen-rich gas generator 13 is an annular generator; thus, the oxygen-rich gas generator 13 is arranged around the oxygen-depleted gas generator 12 .

[0035] Through the above arrangement, the oxygen-rich gas generator 13 and the oxygen-depleted gas generator 12 are separately arranged to effectively realize the separate generation of the primary oxygen-depleted gas 12a and the primary oxygen-rich gas 13a, and the oxygen-rich gas generator 13 is arranged around the oxygen-depleted gas generator 12 to effectively and conveniently connect them at the output position, effectively shortening the gas mixing path and substantially reducing the structural difficulty between them.

[0036] like Figure 1As shown, according to an embodiment of the present invention, the oxygen-depleted fuel gas generator 12 includes: a first filling chamber section 121, a first gas collecting chamber section 122 and a central cone 123; wherein the first filling chamber section 121 and the first gas collecting chamber section 122 are coaxially arranged to be interconnected; in this embodiment, the first filling chamber section 121 is a hollow cylinder with an opening at one end and a closed end at the other end; the first gas collecting chamber section 122 is a hollow cylinder with an opening at one end and a closed end at the other end; wherein the open end of the first filling chamber section 121 is connected to the open end of the first gas collecting chamber section 122. In this embodiment, the central cone 123 is arranged in the first gas collecting chamber section 122, and the central cone 123 is coaxially fixed to the closed end of the first gas collecting chamber section 122 with the first gas collecting chamber section 122. In this embodiment, the tip of the central cone 123 is opposite to the first filling cavity segment 121 ; further, the first channel 12c is arranged on the side wall of the first gas collecting cavity segment 122 , and the first channel 12c is arranged adjacent to the closed end of the first gas collecting cavity segment 122 .

[0037] In this embodiment, a high temperature resistant ceramic coating is provided on the conical surface of the central cone 123 to resist the scouring of the high temperature primary oxygen-depleted fuel gas 12a and reduce the flow resistance to the primary oxygen-depleted fuel gas 12a, so as to ensure the working stability of the present invention. In another embodiment, the central cone 123 can also be made of an anti-ablation material as a whole, for example, it can be made of a molybdenum alloy, a carbon-carbon composite material, etc., to further ensure its working stability.

[0038] In this embodiment, the central cone 123 can be configured as a solid cone or a hollow cone, and can be configured according to actual needs to effectively ensure the flexibility of its configuration.

[0039] like Figure 1 As shown, according to an embodiment of the present invention, the first channel 12c is arranged to be inclined relative to the axial direction of the first gas collecting chamber section 122, and its inclination angle is consistent with the generatrix angle of the central cone 123. Through the above arrangement, it is effectively ensured that the airflow can be smoothly output through the first channel 12c after passing through the central cone 123, which effectively ensures the smooth output and is more beneficial to ensuring the working performance of the present invention.

[0040] like Figure 1As shown, according to an embodiment of the present invention, the axial angle between the first channel 12c and the first gas collecting chamber section 122 is 45° to 60°. Through the above arrangement, it can be fully ensured that the input range of the primary oxygen-depleted gas 12a in the radial range is more easily matched with the output primary oxygen-rich gas 13a, so as to fully realize the accompanying mixing of the primary oxygen-depleted gas 12a during the flow of the primary oxygen-rich gas 13a. If the angle is greater than 60°, it is easy to make the output direction of the primary oxygen-depleted gas 12a and the primary oxygen-rich gas 13a have too large an angle, thereby causing the disadvantage of blocking the primary oxygen-rich gas 13a. If the angle is less than 45°, it is easy to make the mixing position of the primary oxygen-depleted gas 12a and the primary oxygen-rich gas 13a too far back, which is easy to cause uneven mixing of the premixed gas.

[0041] like Figure 1 As shown, according to one embodiment of the present invention, along the axial direction of the first gas collecting chamber section 122, the first channel 12c is adjacent to the large diameter end of the central cone 123, or a portion of the inner wall surface of the first channel 12c is aligned with the outer side surface of the large diameter end of the central cone 123.

[0042] Through the above-mentioned arrangement, based on the first channel 12c being adjacent to the central cone 123 or partially aligning the wall surface with the outer side surface of the central cone 123, it can be effectively ensured that the first channel 12c can more conveniently and smoothly receive the gas flowing through the central cone 123, so that the output of the gas is more continuous flow field, which is more beneficial to ensuring the working performance of the present invention.

[0043] like Figure 1 As shown, according to one embodiment of the present invention, a plurality of first channels 12c are equally spaced along the circumference of the first gas collecting chamber segment 122 .

[0044] Through the above arrangement, the uniform output of the gas in the circumferential direction is effectively guaranteed, which is beneficial to ensuring the full mixing of the gas after blending.

[0045] like Figure 1As shown, according to one embodiment of the present invention, the oxygen-enriched fuel gas generator 13 comprises: a second filling chamber section 131, a second gas collecting chamber section 132 and an annular channel member 133 for forming a second channel 13c; wherein the second filling chamber section 131 and the second gas collecting chamber section 132 are coaxially arranged to communicate with each other. In this embodiment, the second filling chamber section 131 is a hollow annular cylinder with one end open and the other end closed; the second gas collecting chamber section 132 is a hollow annular cylinder with one end open; the open end of the second filling chamber section 131 is connected to the second gas collecting chamber section 132. In this embodiment, the annular channel member 133 is arranged in the second gas collecting chamber section 132, and the annular channel member 133 is coaxially fixed with the second gas collecting chamber section 132 at one end away from the second filling chamber section 131; wherein the second channel 13c is coaxially arranged with the second gas collecting chamber section 132, and along the direction away from the second gas collecting chamber section 132, the second channel 13c is arranged such that its diameter is first reduced and then increased based on the arrangement of the contraction section 13c1 and the expansion section 13c2. In this embodiment, the annular channel member 133 is provided with a transition channel for connecting the first channel 12c and the gas outlet; wherein the inlet of the transition channel is connected to the first channel 12c, and the outlet of the transition channel is connected to the gas outlet provided on the wall surface of the expansion section 13c2 on the annular channel member 133, and of course, the gas outlet can also be directly formed on the wall surface of the expansion section 13c2 based on the transition channel.

[0046] like Figure 1 As shown, according to one embodiment of the present invention, the annular channel member 133 is a Laval nozzle, and the minimum annular throat formed by the annular channel member 133 can block the internal pressure when the oxygen-enriched gas generator 13 is working. In this embodiment, the annular channel member 133 can be made of piezoelectric ceramic material, so that the preset position of the annular channel member 133 can be greatly deformed by applying voltage, thereby changing the throat area in the annular channel member 133, and then controlling the gas flow rate of the primary oxygen-enriched gas 13a; thereby, the gas outlet can be flexibly arranged and adjusted on the expansion section 13c2, so that the use of the present invention is more flexible.

[0047] like Figure 1 As shown, according to one embodiment of the present invention, the second filling chamber segment 131 is coaxially arranged on the outside of the first filling chamber segment 121 with the first filling chamber segment 121, and the second gas collecting chamber segment 132 is coaxially arranged on the outside of the first gas collecting chamber segment 122 with the first gas collecting chamber segment 122; wherein, the end of the second gas collecting chamber segment 132 away from the second filling chamber segment 131 is arranged flush with the end of the first gas collecting chamber segment 122 away from the first filling chamber segment 121; in this embodiment, the side walls of the second filling chamber segment 131 and the first filling chamber segment 121 may be independent of each other or may be shared; correspondingly, the side walls of the second gas collecting chamber segment 132 and the first gas collecting chamber segment 122 may be independent of each other or may be shared.

[0048] like Figure 2 As shown, in another embodiment, the oxygen-enriched gas generator 13 is coaxially arranged with the first gas collecting chamber section 122 on the outside of the first gas collecting chamber section 122; wherein, the end of the second gas collecting chamber section 132 away from the second filling chamber section 131 is arranged flush with the end of the first gas collecting chamber section 122 away from the first filling chamber section 121. In this embodiment, in order to facilitate the coaxial arrangement of the oxygen-enriched gas generator 13 on the outside of the first gas collecting chamber section 122, the radial dimension of the first gas collecting chamber section 122 can be set smaller to fully increase the installation space of the oxygen-enriched gas generator 13; wherein, the side wall of the oxygen-enriched gas generator 13 and the side wall of the first gas collecting chamber section 122 can be independent of each other, or can be set to be shared.

[0049] Through the above arrangement, by making the oxygen-rich gas generator 13 and the oxygen-lean gas generator 12 completely coaxial or partially coaxial, a flexible selection can be made according to the design requirements of the axial length and radial size of the entire engine, so that the present invention has more flexible adaptability. When the oxygen-rich gas generator 13 and the oxygen-lean gas generator 12 are completely coaxially arranged, the axial length of the entire engine can be effectively shortened, so that the present invention can be applied to an installation space with a smaller axial length. Correspondingly, when the oxygen-rich gas generator 13 and the oxygen-lean gas generator 12 are partially coaxially arranged, the radial size of the entire engine can be effectively controlled, so that the present invention can be applied to an installation space with a smaller radial size.

[0050] like Figure 1 As shown, according to one embodiment of the present invention, the inner sides of the first filling cavity segment 121 and the first gas collecting cavity segment 122 are respectively provided with a first high-silicon oxide thermal insulation lining; the inner sides of the second filling cavity segment 131 and the second gas collecting cavity segment 132 are respectively provided with a second high-silicon oxide thermal insulation lining.

[0051] Through the above arrangement, the high temperature resistance of the oxygen-depleted fuel gas generator 12 and the oxygen-rich fuel gas generator 13 is effectively guaranteed, and the working stability of the present invention is effectively guaranteed.

[0052] like Figure 1 As shown, according to one embodiment of the present invention, the oxygen-depleted solid propellant 12b includes: a first solid propellant body and a first coating sleeve coated on the outside of the first solid propellant body; wherein the first solid propellant body is made of a typical oxygen-depleted propellant formula, wherein the mass fraction of boron is 36%, ammonium perchlorate is 30%, magnesium is 11%, and terminal hydroxyl polybutadiene is 23%; thus, the primary oxygen-depleted fuel gas 12a generated by the oxygen-depleted fuel gas generator 12 based on the oxygen-depleted solid propellant 12b includes combustible gas (such as hydrogen), combustible particles (boron particles, carbon particles), inert gas, inert particles and other substances.

[0053] like Figure 1 As shown, according to one embodiment of the present invention, the oxygen-enriched solid propellant 13b includes: a second solid propellant body and a second coating sleeve coated on the outside of the second solid propellant body; wherein the second solid propellant body is made of a typical oxygen-enriched propellant formula, wherein ammonium perchlorate>75%, and thus, the primary oxygen-enriched fuel gas 13a generated by the oxygen-enriched fuel gas generator 13 based on the oxygen-enriched solid propellant 13b includes an oxidizing gas (such as oxygen), oxidizing particles, inert gas, inert particles and other substances.

[0054] Combination Figure 1 and Figure 3 As shown, according to one embodiment of the present invention, the detonator tube 14 is connected to the tangential position of the detonation combustion chamber section 11b; wherein, the inner wall of the detonator tube 14 is designed with a coil spring 14a (called a shchelkin coil) for accelerating the DDT process with a hydrogen-oxygen flame to realize the transformation from deflagration to detonation, thereby generating a strong detonation jet.

[0055] like Figure 1 As shown, according to one embodiment of the present invention, the oxygen-depleted gas generator 12 blocks the pressure and gas flow in the chamber through the total area of ​​the nozzles of all the first channels 12c to prevent the influence of external pressure fluctuations.

[0056] like Figure 1 As shown, according to one embodiment of the present invention, the oxygen-enriched gas generator 13 blocks the pressure and gas flow in the chamber through the annular throat of the second channel 13c formed by the annular channel member 133 to prevent the influence of external pressure fluctuations.

[0057] In order to further illustrate this scheme, the working process of this scheme is further elaborated.

[0058] The oxygen-depleted solid propellant 12b in the oxygen-depleted gas generator 12 is ignited based on the ignition device to generate the primary oxygen-depleted gas 12a, and the oxygen-rich solid propellant 13b in the oxygen-rich gas generator 13 is ignited based on the ignition device; The primary oxygen-depleted gas 12a generated in the oxygen-depleted gas generator 12 is output to the second channel 13c of the oxygen-rich gas generator 13 based on the first channel 12c, so as to achieve mixing of the primary oxygen-depleted gas 12a with the primary oxygen-rich gas 13a generated in the oxygen-rich gas generator 13 to obtain premixed gas; in this embodiment, by designing the parameters of the oxygen-depleted solid propellant 12b and the oxygen-rich solid propellant 13b, the proper ratio of fuel and oxidant in the gas after the primary oxygen-depleted gas 12a and the primary oxygen-rich gas 13a are mixed, that is, the equivalence ratio is 1.

[0059] The detonator 14 is ignited and detonated in a controlled manner to generate a strong hot jet to detonate the premixed gas, forming a continuous rotating detonation wave in the detonation combustion chamber; The premixed gas releases energy through detonation combustion, and generates thrust after energy conversion through the tail nozzle 11c.

[0060] The above contents are merely examples of specific solutions of the present invention. For devices and structures not described in detail therein, it should be understood that they can be implemented by adopting general devices and general methods available in the art.

[0061] The above is only one solution of the present invention and is 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-gas generator solid rocket rotating detonation engine, characterized in that: include: A housing (11), an oxygen-depleted fuel gas generator (12) and an oxygen-rich fuel gas generator (13) installed in the housing (11), and a detonator (14) installed on the housing (11); The oxygen-depleted fuel gas generator (12) is provided with an oxygen-depleted solid propellant (12b) for generating a primary oxygen-depleted fuel gas (12a); The oxygen-enriched fuel gas generator (13) is provided with an oxygen-enriched solid propellant (13b) for generating a primary oxygen-enriched fuel gas (13a); The oxygen-depleted fuel gas generator (12) is provided with a first channel (12c) for outputting the primary oxygen-depleted fuel gas (12a); The oxygen-enriched fuel gas generator (13) is provided with a second channel (13c) for outputting the primary oxygen-enriched fuel gas (13a); The first channel (12c) is connected to the second channel (13c) so as to be used for mixing the primary oxygen-depleted fuel gas (12a) and the primary oxygen-rich fuel gas (13a) to form a premixed gas; The detonator (14) is used to detonate the premixed gas.

2. The dual-gas generator solid rocket rotating detonation engine according to claim 1, characterized in that: Along the output direction of the primary oxygen-enriched fuel gas (13a), the second channel (13c) comprises a contraction section (13c1) and an expansion section (13c2) which are connected in sequence; A gas outlet connected to the first channel (12c) is provided on the wall surface of the expansion section (13c2).

3. The dual-gas generator solid rocket rotating detonation engine according to claim 2, characterized in that: The primary oxygen-depleted fuel gas (12a) and the primary oxygen-rich fuel gas (13a) are mixed at a flow rate of an equivalence ratio of 1 to form the premixed gas.

4. The dual-gas generator solid rocket rotating detonation engine according to claim 3, characterized in that: The housing (11) comprises: a generator installation section (11a) for arranging the oxygen-depleted gas generator (12) and the oxygen-rich gas generator (13), a detonation combustion chamber section (11b) for constructing a detonation combustion chamber, and a tail nozzle (11c) for accelerating the expansion and discharge of combustion products; The generator installation section (11a), the detonation combustion chamber section (11b) and the tail nozzle (11c) are coaxially arranged in sequence; The oxygen-depleted fuel gas generator (12) and the oxygen-rich fuel gas generator (13) are coaxially installed in the generator installation section (11a); The second channel (13c) is arranged to communicate with the detonation combustion chamber; The detonator (14) is installed in the detonation combustion chamber section (11b).

5. The dual-gas generator solid rocket rotating detonation engine according to claim 4, characterized in that: The oxygen-depleted fuel gas generator (12) is a cylindrical generator; The oxygen-enriched fuel gas generator (13) is a ring-shaped generator; The oxygen-rich fuel gas generator (13) is disposed around the oxygen-depleted fuel gas generator (12).

6. The dual-gas generator solid rocket rotating detonation engine according to claim 5, characterized in that: The oxygen-depleted fuel gas generator (12) comprises: a first filling cavity section (121), a first gas collecting cavity section (122) and a central cone (123); The first filling cavity section (121) and the first gas collecting cavity section (122) are coaxially arranged to communicate with each other; The first filling cavity section (121) is a hollow cylinder with one end open and the other end closed; The first gas collecting chamber section (122) is a hollow cylinder with one end open and the other end closed; The open end of the first filling cavity section (121) is connected to the open end of the first gas collecting cavity section (122); The central cone (123) is arranged in the first gas collection chamber section (122), and the central cone (123) and the first gas collection chamber section (122) are coaxially fixed at the closed end of the first gas collection chamber section (122); The tip of the central cone (123) is opposite to the first filling cavity section (121); The first channel (12c) is arranged on a side wall of the first gas collecting chamber section (122), and the first channel (12c) is arranged adjacent to a closed end of the first gas collecting chamber section (122); The first channel (12c) is arranged to be inclined relative to the axial direction of the first gas collecting chamber section (122), and its inclination angle is consistent with the generatrix angle of the central cone (123).

7. The dual-gas generator solid rocket rotating detonation engine according to claim 6, characterized in that: The axial included angle between the first channel (12c) and the first gas collecting chamber section (122) is 45° to 60°; Along the axial direction of the first gas collecting cavity section (122), the first channel (12c) is adjacent to the large diameter end of the central cone (123), or a portion of the inner wall surface of the first channel (12c) is aligned with the outer side surface of the large diameter end of the central cone (123); A plurality of first channels (12c) are arranged at equal intervals along the circumference of the first gas collecting chamber section (122).

8. The dual-gas generator solid rocket rotating detonation engine according to claim 7, characterized in that: The oxygen-enriched fuel gas generator (13) comprises: a second filling chamber section (131), a second gas collecting chamber section (132), and an annular channel member (133) for forming the second channel (13c); The second filling cavity section (131) and the second gas collecting cavity section (132) are coaxially arranged to communicate with each other; The second filling cavity section (131) is a hollow annular cylinder with an opening at one end and a closed end at the other end; The second gas collecting chamber section (132) is a hollow annular cylinder with one end open at both ends; The open end of the second filling cavity section (131) is connected to the second gas collecting cavity section (132); The annular channel member (133) is arranged in the second gas collecting chamber segment (132), and the annular channel member (133) is coaxially fixed with the second gas collecting chamber segment (132) at an end away from the second filling chamber segment (131); The second channel (13c) and the second gas collecting chamber section (132) are coaxially arranged; The annular channel member (133) is provided with a transition channel for connecting the first channel (12c) and the gas outlet.

9. The dual-gas generator solid rocket rotating detonation engine according to claim 8, characterized in that: The second filling cavity segment (131) is coaxially arranged with the first filling cavity segment (121) on the outside of the first filling cavity segment (121), and the second gas collecting cavity segment (132) is coaxially arranged with the first gas collecting cavity segment (122) on the outside of the first gas collecting cavity segment (122); An end of the second gas collecting chamber segment (132) away from the second filling chamber segment (131) is arranged flush with an end of the first gas collecting chamber segment (122) away from the first filling chamber segment (121); or, The oxygen-enriched fuel gas generator (13) is coaxially arranged with the first gas collecting chamber section (122) and outside the first gas collecting chamber section (122); One end of the second gas collecting chamber segment (132) away from the second filling chamber segment (131) is arranged flush with one end of the first gas collecting chamber segment (122) away from the first filling chamber segment (121).

10. The dual-gas generator solid rocket rotating detonation engine according to claim 9, characterized in that: The inner side surfaces of the first filling cavity section (121) and the first gas collecting cavity section (122) are respectively provided with a first high-silicon-oxygen thermal insulation lining; The inner side surfaces of the second filling cavity section (131) and the second gas collecting cavity section (132) are respectively provided with a second high-silicon-oxygen thermal insulation lining; The oxygen-deficient solid propellant (12b) comprises: a first solid propellant body and a first coating sleeve coating the outside of the first solid propellant body; The oxygen-rich solid propellant (13b) comprises: a second solid propellant body and a second coating sleeve coating the outside of the second solid propellant body; The detonator tube (14) is connected to a tangential position of the detonation combustion chamber section (11b); The inner wall of the detonator tube (14) is provided with a coil spring (14a); The annular channel member (133) is a Laval nozzle and is made of piezoelectric ceramic material.

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