Solid rocket ramjet engine gas multi-angle coordinated impact mixing enhancement device

Abstract

The invention discloses a multi-angle coordinated impact mixing enhancement device for gas in a solid rocket ramjet engine, which belongs to the technical field of solid rocket ramjet engines. The invention adjusts the uniformity and stability of the gas and air distribution in the flow field by adjusting the angle of mutual impact between multiple gas streams and the deflection angle of the gas toward the inlet side, thereby achieving enhanced mixing of the gas and air. The invention also controls the distance between the multi-angle coordinated impact nozzle and the inlet of the afterburner chamber and the axial, radial, and circumferential orientations of the installation of the multi-angle coordinated impact nozzle by cooperating with the combustion chamber docking section and the nozzle base, thereby adjusting the flow field. The nozzle does not intrude into the afterburner chamber, thereby minimizing the total pressure loss and reducing the difficulty of thermal protection. The invention also controls the multi-angle gas nozzle hole, the axial, radial, and circumferential orientations of the installation of the multi-angle coordinated impact nozzle, and the distance between the multi-angle coordinated impact nozzle and the inlet of the afterburner chamber, thereby achieving multi-dimensional adjustment of the flow field.

Description

Technical Field

[0001] The present invention relates to a solid rocket ramjet engine combustion gas multi-angle coordinated impact mixing enhancement device, in particular to a solid rocket ramjet engine mixing enhancement technology, belonging to the technical field of solid rocket ramjet engines. Background Art

[0002] Hypersonic weapons are a strategic high ground in future global military competition. With the advancement of aerospace technology, higher requirements are being placed on their comprehensive performance and space access capabilities. These weapons typically require high energy density, rapid operational response, and easy storage, maintenance, and use. The solid rocket ramjet (SR-R) is a new missile propulsion system. As a fusion of ramjet and solid rocket technologies, it combines the advantages of both: high specific impulse, compact structure, high packing density, rapid operational response, and excellent maneuverability and safety. It is well-suited for high-speed cruise flight of hypersonic missiles. Furthermore, compared to solid-fuel ramjets, SR-Rs do not face ignition and flame stabilization issues, and their combustion chamber operating parameters are less affected by incoming flow parameters. These advantages have garnered widespread attention from scholars both domestically and internationally.

[0003] The afterburner is the primary site for fuel combustion and energy release in boron-containing solid rocket ramjet engines. Its combustion efficiency plays a decisive role in the overall performance of solid rocket ramjet engines. In practical applications, the primary fuel gas carries a large amount of boron particles into the afterburner for secondary combustion. Given the extremely short residence time of the fuel gas in the afterburner, achieving efficient secondary combustion within a very short period of time is a key development direction. Since the diffusion rate of fuel and air mixing has a significant impact on the combustion process, research on gas-air mixing enhancement is essential.

[0004] Currently, mixing enhancement technologies are categorized into passive and active approaches. Passive approaches include physical ramps, aerodynamic ramps, struts, and gas nozzles, while active approaches include pulsed jets, synthetic jets, and elastic excitation. Research has found that physical ramps typically intrude into the flow field, resulting in significant drag and total pressure losses. Furthermore, physical ramp surfaces generate high heat loads, placing high demands on the heat resistance of the material. In particular, the sharp edges of the ramps are susceptible to ablation in high-temperature environments. The mixing enhancement and flame stabilization effects of physical ramps are highly dependent on their geometry; if the geometry is damaged, the mixing enhancement effect is significantly diminished. Aerodynamic ramps provide better mixing performance in the near field than physical ramps, but inferior performance in the far field. As a mixing enhancement device inserted into the main flow, struts generate significant drag and total pressure losses. Furthermore, the thermal environment they face is quite harsh, and thermal protection is currently a major challenge. Active mixing enhancement methods are generally complex, expensive to research, and difficult to implement in practice.

[0005] As a relatively new passive mixing enhancement method, gas nozzles have received more attention from researchers. Summary of the Invention

[0006] In view of the shortcomings of the above-mentioned active / passive mixing enhancement technology, such as complex structure, intrusion into the flow field, easy to cause large total pressure loss, and difficulty in thermal protection, the main purpose of the present invention is to provide a solid rocket ramjet engine gas multi-angle coordinated impact mixing enhancement device, which can achieve the control of the gas self-impact position and the control of the gas and air mutual impact position by adjusting the angle of mutual impact between multiple gas streams and the deflection angle of the gas to the inlet side, and adjust the uniformity and stability of the gas and air distribution in the flow field to achieve the enhanced mixing of gas and air in the afterburner, thereby improving the combustion performance and increasing the combustion efficiency; through the cooperation of the combustion chamber docking section and the nozzle base, The distance between the multi-angle coordinated gas impact nozzle and the afterburner inlet, as well as its axial, radial, and circumferential orientation, can be controlled to regulate the flow field. Furthermore, the nozzle does not intrude into the afterburner or the flow field's physical structure, minimizing total pressure loss and reducing the difficulty of thermal protection. By controlling the multi-angle gas nozzle holes, the axial, radial, and circumferential orientation of the multi-angle coordinated gas impact nozzle, and the distance between the multi-angle coordinated gas impact nozzle and the afterburner inlet, the flow field can be regulated in multiple dimensions, significantly improving the maneuverability of the solid rocket ramjet engine. The gas in the flow field contains boron particles.

[0007] The purpose of the present invention is achieved through the following technical solutions.

[0008] The solid rocket ramjet engine gas multi-angle coordinated impact mixing enhancement device disclosed in the present invention is mainly composed of a combustion chamber docking section, a gas multi-angle coordinated impact nozzle, a threaded hole, a cylindrical pin, a semicircular limiting hole, a nozzle base, and a gas nozzle hole.

[0009] The multi-angle coordinated gas impact nozzle has gas nozzle holes for injecting primary gas from a solid rocket ramjet engine into the afterburner, generating a multi-angle coordinated impact effect. The nozzle holes are an even number and are divided into two groups. The two groups are symmetrically distributed along the nozzle centerline, with the centerlines of each group intersecting. Primary gas generated by the gas generator changes direction through the nozzle holes and enters the afterburner, generating two groups of self-impact gas. Two reference planes are defined for the multi-angle coordinated gas impact nozzle. These two reference planes are perpendicular to each other and pass through the centerline of the nozzle. One of these planes is parallel to the inlet duct outlet plane and is designated as plane 1. The other plane is designated as plane 2. The angle between the centerline of the gas nozzle hole and plane 2 is defined as the self-impact impact angle α. Taking into account the effect of the angle between the gas injection direction and the inlet duct on mixing, the angle between the centerline of each gas nozzle hole and the inlet duct outlet plane is defined as the mutual impact angle β. Adjusting this mutual impact angle β controls the deflection angle of the gas relative to the inlet duct. Because surface 1 is parallel to the intake duct outlet plane, the angle between the centerline of the gas nozzle and surface 1 is equal to the mutual impact angle β. Therefore, adjusting the angle between the centerline of the gas nozzle and surface 1 is equivalent to adjusting the mutual impact angle β. By collaboratively adjusting the self-impact collision angle α and the mutual impact collision angle β, the angles of mutual impact between multiple gas streams and the deflection angle of the gas toward the intake duct are adjusted, the gas self-impact position and the gas-air mutual impact position are controlled, the uniformity of the flow field distribution is improved, and the mixing of gas and air in the afterburner is enhanced, thereby improving combustion performance and increasing combustion efficiency. The collaborative control of the self-impact collision angle α and the mutual impact collision angle β is manifested as creating an angle θ between the centerline of the gas nozzle and the centerline of the gas multi-angle collaborative impact nozzle, and establishing an angular relationship between the angle θ and the self-impact collision angle α and the mutual impact collision angle β. Based on the relationship between the angle θ and α and β, the nozzle can be more conveniently optimized for different working conditions, improving the efficiency of nozzle design optimization under different working conditions, and facilitating the replacement of different nozzles to adapt to different working conditions.

[0010] The relationship between the angle θ between the center line of the gas nozzle and the center line of the gas multi-angle cooperative impact nozzle and the self-impact collision angle α and the mutual impact collision angle β is expressed as follows:

[0011] cosθ=cosα·cosβ

[0012] The nozzle base is provided with semicircular limiting holes for limiting the circumferential rotation of the multi-angle coordinated gas impact nozzle. Controlling the number and spacing of the semicircular limiting holes on the nozzle base enables various circumferential orientation designs of the multi-angle coordinated gas impact nozzle. The nozzle base has an inner diameter equal to the inner diameter of the multi-angle coordinated gas impact nozzle, and an outer diameter greater than the outer diameter of the multi-angle coordinated gas impact nozzle. A grooved section in the outer diameter of the nozzle base and the combustion chamber interface cooperate to limit the axial and radial movement of the multi-angle coordinated gas impact nozzle.

[0013] The small-diameter end of the combustion chamber docking section is provided with a groove for supporting the outer diameter of the nozzle base, thereby dividing the combustion chamber docking section into two parts: a grooved section and a non-grooved section. The inner diameter of the grooved section is the same as the outer diameter of the nozzle base, and the nozzle base and the grooved section of the combustion chamber docking section are assembled in a tolerance fit. The inner diameter of the non-grooved section of the combustion chamber docking section is the same as the outer diameter of the gas multi-angle coordinated impact nozzle, and the gas multi-angle coordinated impact nozzle is assembled in a tolerance fit. The groove is used to limit the axial and radial orientations of the gas multi-angle coordinated impact nozzle. Controlling the depth of the groove can control the distance between the gas multi-angle coordinated impact nozzle and the inlet of the afterburner, thereby affecting the flow field in the afterburner. The depth of the groove refers to the distance between the interface between the grooved section and the non-grooved section of the combustion chamber docking section and the end face of the small-diameter end of the combustion chamber docking section. The combustion chamber docking section has a grooved section with a semicircular stopper hole that mates with the semicircular stopper hole in the nozzle base. The semicircular stopper hole on the combustion chamber docking section and the semicircular stopper hole on the nozzle base are spliced ​​to form a circular hole. The interference fit of a cylindrical pin in the circular hole restricts the circumferential orientation of the multi-angle coordinated impact nozzle during installation, preventing circumferential rotation. The large and small diameter ends of the combustion chamber docking section each have threaded holes for threaded connections. The multi-angle coordinated impact nozzle is connected to the gas generator nozzle via the small diameter end of the combustion chamber docking section, using a threaded connection; the multi-angle coordinated impact nozzle is connected to the afterburner via the large diameter end of the combustion chamber docking section, using a threaded connection. The threaded connection of the combustion chamber docking section facilitates disassembly and replacement of different nozzles, adapting to the need to adjust the self-impact angle α and the mutual-impact angle β under different operating conditions. This facilitates ground-based direct connection experiments of solid rocket ramjet engines under different operating conditions and reduces costs.

[0014] The diameter of the cylindrical pin is adapted to the diameter of the semicircular limiting hole, and the adaptation refers to an interference fit between the cylindrical pin and the semicircular limiting hole. The pin connection between the cylindrical pin and the semicircular limiting hole controls the circumferential orientation of the multi-angle coordinated gas impact nozzle and the combustion chamber interface, preventing the nozzle from rotating circumferentially.

[0015] In existing passive mixing enhancement methods, the physical ramp usually invades the flow field, thus generating a large total pressure loss and resistance loss; secondly, the surface of the physical ramp will generate a very high heat load, which places high demands on the heat resistance of the material, especially the sharp edge of the ramp is easily ablated and damaged in a high temperature environment. The mixing enhancement and flame stabilization effect of the physical ramp is highly dependent on its geometric structure. Once the geometric structure is destroyed, its mixing enhancement effect will be greatly weakened. The mixing effect of the aerodynamic ramp in the near field is worse than that of the physical ramp, but the far field mixing effect is not as good as that of the physical ramp. As a mixing enhancement device inserted into the mainstream, the support plate will generate a large resistance loss and total pressure loss, and the thermal environment faced by the support plate is quite harsh, and its thermal protection is also a major problem at present. In order to minimize the total pressure loss of the flow field in the afterburner and reduce the difficulty of thermal protection, as a preferred embodiment, the multi-angle collaborative impact nozzle of the gas is placed at the entrance of the afterburner, so that collaborative impact can be achieved without invading the afterburner, thereby enhancing mixing.

[0016] To further improve combustion efficiency, the number of nozzles was studied. Numerical simulations revealed that in a contralaterally inlet solid rocket ramjet, when the primary fuel gas enters the afterburner through four nozzles, the particles in the fuel gas are more evenly dispersed. Preferably, the multi-angle coordinated impactor nozzle has four nozzles, divided into two groups. This contralaterally inlet solid rocket ramjet refers to a solid rocket ramjet with inlets symmetrically distributed on either side of the afterburner centerline.

[0017] In order to facilitate the regulation of multiple installation orientations of the multi-angle coordinated impact type gas nozzle, it is preferred that n threaded holes are opened at both ends of the large and small diameter ends of the combustion chamber docking section to achieve 360 / n degree installation angle changes of the multi-angle coordinated impact type gas nozzle, which is convenient for changing the installation orientation of the nozzle.

[0018] The solid rocket ramjet engine gas multi-angle coordinated impact mixing enhancement device can control the installation orientation of the gas multi-angle coordinated impact nozzle by the number of threaded holes in the combustion chamber docking section and the number and position of the semicircular limiting holes in the nozzle base. The coordinated control of the two can combine multiple orientation angles to meet the needs of multiple tests in one processing.

[0019] In order to achieve the reusability of the gas multi-angle coordinated impact nozzle, it is preferred that the gas multi-angle coordinated impact nozzle is processed using tungsten-infiltrated copper material. The tungsten-infiltrated copper material has the characteristics of high melting point and resistance to burning, and has the ability to withstand high temperature and high temperature airflow erosion.

[0020] In order to facilitate processing and ensure smoother flow in the outer flow field of the cylindrical structure, it is preferred that the multi-angle coordinated impact type gas nozzle is cylindrical.

[0021] In order to reduce the number of processing steps, it is preferred that the gas multi-angle coordinated impact nozzle and the nozzle base of the present invention are an integrated structure.

[0022] The working method of the solid rocket ramjet engine combustion gas multi-angle coordinated impact mixing enhancement device disclosed in the present invention is:

[0023] The present invention is used in a solid rocket ramjet engine, utilizing a combustion chamber docking section, a nozzle base, and a cylindrical pin to achieve the installation and fixation of a multi-angle coordinated gas impact nozzle. To reduce the number of processing steps, the multi-angle coordinated gas impact nozzle and nozzle base are integrated into a single structure. A groove is formed at the small-diameter end of the combustion chamber docking section to support the outer diameter of the nozzle base. The combustion chamber docking section is thus divided into two sections: a grooved section and a non-grooved section. The nozzle base is assembled with the grooved section of the combustion chamber docking section, utilizing a tolerance fit. The multi-angle coordinated gas impact nozzle is assembled with the non-grooved section of the combustion chamber docking section, utilizing a tolerance fit. The groove in the combustion chamber docking section constrains the axial and radial orientations of the multi-angle coordinated gas impact nozzle. The distance between the multi-angle coordinated gas impact nozzle and the afterburner inlet is controlled by controlling the depth of the groove. The groove depth refers to the distance between the interface between the grooved and non-grooved sections of the combustion chamber docking section and the end face of the small-diameter end of the combustion chamber docking section. The combustion chamber docking section has a groove section and a semicircular limiting hole on the nozzle base. The semicircular limiting hole on the combustion chamber docking section and the semicircular limiting hole on the nozzle base are spliced ​​to form a circular hole. A cylindrical pin is installed with an interference fit in the circular hole to limit the circumferential orientation of the multi-angle coordinated gas impact nozzle and prevent it from rotating circumferentially. The large and small diameter ends of the combustion chamber docking section each have a threaded hole for threaded connection. The multi-angle coordinated gas impact nozzle is connected to the gas generator nozzle through the small diameter end of the combustion chamber docking section by a threaded connection; the multi-angle coordinated gas impact nozzle is connected to the afterburner through the large diameter end of the combustion chamber docking section by a threaded connection. The threaded connection of the combustion chamber docking section makes it easy to disassemble the combustion chamber docking section and facilitate the replacement of different nozzles. It can meet the needs of adjusting the self-impact collision angle α and the mutual impact collision angle β under different operating conditions, facilitate ground direct connection experiments of solid rocket ramjet engines under different operating conditions, and reduce costs.

[0024] After installation, in actual use, the primary gas generated by the gas generator flows through the gas generator nozzle into the multi-angle coordinated gas impactor nozzle. This nozzle has an even number of gas nozzle holes, divided into two groups, with the centerlines of the gas nozzle holes in each group intersecting. Numerical simulations have shown that in a contralaterally inlet solid rocket ramjet engine, when the primary gas enters the afterburner through four gas nozzle holes, the gas multi-angle coordinated gas impactor nozzle has four gas nozzle holes, which can achieve a more uniform dispersion of gas particles. This contralaterally inlet solid rocket ramjet engine refers to a solid rocket ramjet engine with inlets symmetrically distributed on either side of the afterburner centerline. The primary gas changes direction through the gas nozzle. By collaboratively adjusting the self-impact collision angle α and the mutual impact collision angle β, the angle θ between the center line of the gas nozzle and the center line of the gas multi-angle collaborative impact nozzle is controlled. The mutual impact angle between multiple gas streams and the deflection angle of the gas toward the air inlet side are adjusted, the self-impact position of the gas and the mutual impact position of the gas and air are controlled, the uniformity of the flow field distribution is improved, and the mixing of the gas and air in the afterburner is enhanced, thereby improving the combustion performance and increasing the combustion efficiency.

[0025] The mixed combustion effect of gas and air is controlled from multiple dimensions through multi-angle control of the gas nozzle, control of the axial, radial and circumferential installation positions of the multi-angle coordinated gas impact nozzle and control of the distance between the multi-angle coordinated gas impact nozzle and the inlet of the afterburner.

[0026] Beneficial effects:

[0027] 1. The solid rocket ramjet engine gas multi-angle coordinated impact mixing enhancement device disclosed in the present invention controls the angle θ between the center line of the gas nozzle and the center line of the gas multi-angle coordinated impact nozzle by coordinated adjustment of the gas self-impact collision angle α and the mutual impact collision angle β, thereby achieving adjustment of the mutual impact angle between multiple gas streams and the deflection angle of the gas toward the inlet side, achieving control of the gas self-impact position and the gas-air mutual impact position, improving the uniformity of the flow field distribution, and achieving enhanced mixing of the gas and air in the afterburner, thereby improving combustion performance and increasing combustion efficiency.

[0028] 2. In existing passive mixing enhancement methods, physical ramps typically intrude into the flow field, resulting in significant total pressure and drag losses. Furthermore, the surface of the physical ramp generates a high heat load, placing high demands on the heat resistance of the material. In particular, the sharp edges of the ramp are easily damaged by ablation in high-temperature environments. The mixing enhancement and flame stabilization effects of the physical ramp are highly dependent on its geometric structure. Once the geometric structure is damaged, the mixing enhancement effect will be greatly weakened. Aerodynamic ramps have better mixing effects in the near field than physical ramps, but are less effective in the far field. As a mixing enhancement device inserted into the mainstream, the support plate generates significant drag and total pressure losses. Furthermore, the thermal environment faced by the support plate is quite harsh, and its thermal protection is currently a major challenge. In order to minimize the total pressure loss of the flow field within the afterburner and reduce the difficulty of thermal protection, the present invention discloses a multi-angle coordinated impact mixing enhancement device for solid rocket ramjet engines. The multi-angle coordinated impact nozzle for the gas is placed at the entrance of the afterburner, achieving coordinated impact and enhanced mixing without intruding into the afterburner.

[0029] 3. To reduce the number of processing steps, the solid rocket ramjet engine multi-angle coordinated impact gas mixing enhancement device disclosed in this invention has a multi-angle coordinated impact gas nozzle and nozzle base as an integrated structure, which facilitates the mating connection between the multi-angle coordinated impact gas nozzle and the combustion chamber docking section. Semicircular limiting holes are provided in the nozzle base to limit the circumferential position of the multi-angle coordinated impact gas nozzle during installation and prevent circumferential rotation. Controlling the number and position of the limiting holes enables multiple circumferential position control of the multi-angle coordinated impact gas nozzle and the combustion chamber docking section.

[0030] 4. The solid rocket ramjet engine gas multi-angle coordinated impact mixing enhancement device disclosed in the present invention has an inner diameter of the nozzle base equal to the inner diameter of the gas multi-angle coordinated impact nozzle, and an outer diameter of the nozzle base is larger than the outer diameter of the gas multi-angle coordinated impact nozzle. The outer diameter of the nozzle base cooperates with the combustion chamber docking section through a groove section to limit the axial and radial movement of the gas multi-angle coordinated impact nozzle.

[0031] 5. The solid rocket ramjet engine gas multi-angle coordinated impact mixing enhancement device disclosed in the present invention has a groove at the small diameter end of the combustion chamber docking section for supporting the outer diameter of the nozzle base, which can limit the axial orientation of the gas multi-angle coordinated impact nozzle; the combustion chamber docking section, the nozzle base and the gas multi-angle coordinated impact nozzle are installed with tolerance matching, which can limit the radial orientation of the gas multi-angle coordinated impact nozzle. Controlling the depth of the groove can control the distance between the gas multi-angle coordinated impact nozzle and the afterburner chamber entrance, affecting the flow field in the afterburner chamber. The groove section of the combustion chamber docking section is provided with a semicircular limiting hole that is adapted to the semicircular limiting hole of the nozzle base, and cooperates with the connection of the cylindrical pin to realize the limitation of the circumferential orientation of the gas multi-angle coordinated impact nozzle installation and prevent it from circumferential rotation.

[0032] 6. The solid rocket ramjet engine multi-angle coordinated impactor mixing enhancement device disclosed herein utilizes threaded holes at the large and small diameter ends of the combustion chamber docking section to achieve threaded connection, connecting the multi-angle coordinated impactor nozzle with the gas generator nozzle and afterburner chamber. To facilitate the adjustment of the multi-angle coordinated impactor nozzle's multiple installation orientations, n threaded holes are provided at each of the large and small diameter ends of the combustion chamber docking section, enabling the nozzle to be installed at 360 / n degrees, facilitating adjustments to the nozzle's installation orientation.

[0033] 7. In order to facilitate the ground direct connection experiment of solid rocket ramjet engines under different working conditions and reduce costs while conducting multiple tests, the solid rocket ramjet engine gas multi-angle coordinated impact mixing enhancement device disclosed in the present invention adopts a threaded connection in the combustion chamber docking section, which is convenient for disassembly and replacement of different nozzles. It is suitable for adjusting the self-impact collision angle α and the mutual impact collision angle β under different working conditions, and can realize a small range of parts replacement to carry out multiple groups of tests, saving test costs and being convenient and reliable.

[0034] 8. The solid rocket ramjet engine gas multi-angle coordinated impact mixing enhancement device disclosed in the present invention controls the installation orientation of the gas multi-angle coordinated impact nozzle by the number of threaded holes in the combustion chamber docking section and the number and position of the semicircular limiting holes in the nozzle base. The two are controlled in coordination to combine a variety of orientation angles, realizing the need for multiple tests in one processing. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 This is a schematic diagram of the assembly of the multi-angle coordinated impact mixing enhancement device for solid rocket ramjet engine combustion gas disclosed in the present invention;

[0036] Figure 2 The front view and top view of the integrated structure of the gas multi-angle coordinated impact nozzle and nozzle base of the present invention;

[0037] Figure 3 Schematic diagram of the self-impact collision angle α and the mutual-impact collision angle β according to the present invention;

[0038] Figure 4 Schematic diagram of the cross-sectional structure of the combustion chamber docking section of the present invention;

[0039] Figure 5 This is a schematic diagram of the assembly cross-sectional structure of the present invention;

[0040] Figure 6 This is the simulated total temperature cloud diagram of the solid rocket ramjet afterburner, where: Figure 6 (a) is the temperature scale of the total temperature cloud map; Figure 6 (b) is a simulated total temperature cloud diagram of the afterburning chamber of a solid rocket ramjet engine with the nozzle of the present invention; Figure 6 (c) is a simulated total temperature cloud diagram of the afterburning chamber of a solid rocket ramjet engine without the nozzle of the present invention;

[0041] Figure 7 This is a simulated particle motion trajectory diagram of the solid rocket ramjet afterburner, where: Figure 7 (a) Particle residence time scale of the particle motion trajectory diagram; Figure 7 (b) is a diagram showing the simulated particle motion trajectory in the afterburner of a solid rocket ramjet engine equipped with the nozzle of the present invention; Figure 7 (c) is a diagram showing the simulated particle motion trajectory of a solid rocket ramjet afterburner without the nozzle of the present invention.

[0042] Among them, 1 is the combustion chamber docking section, 2 is the gas multi-angle coordinated impact nozzle, 3 is the threaded hole, 4 is the cylindrical pin, 5 is the semicircular limiting hole, 6 is the nozzle base, and 7 is the gas nozzle hole. DETAILED DESCRIPTION

[0043] In order to better illustrate the purpose and advantages of the present invention, the present invention will be described in detail below with reference to relevant drawings.

[0044] like Figure 1 As shown, the solid rocket ramjet engine gas multi-angle coordinated impact mixing enhancement device disclosed in this embodiment includes a combustion chamber docking section 1, a gas multi-angle coordinated impact nozzle 2, a threaded hole 3, a cylindrical pin 4, a semicircular limiting hole 5, a nozzle base 6, and a gas nozzle 7; the gas multi-angle coordinated impact nozzle 2 is fixedly installed on the nozzle base 6.

[0045] like Figure 1 and Figure 2As shown, the number of gas nozzles 7 on the multi-angle coordinated gas impact nozzle 2 disclosed in this embodiment is four, and the four gas nozzles 7 are divided into two groups, and the center lines of the two gas nozzles 7 in each group intersect; the primary gas generated by the gas generator changes direction through the gas nozzles 7 and finally enters the afterburning chamber to generate two groups of self-impact gases.

[0046] like Figure 2 As shown, the nozzle base 6 is provided with a semicircular limiting hole 5 for limiting the circumferential rotation of the gas multi-angle coordinated impact nozzle 2. The semicircular limiting hole 5 cooperates with the groove section of the combustion chamber docking section 1 to form a circular hole. Through the interference fit between the cylindrical pin 4 and the circular hole, the circumferential installation orientation of the gas multi-angle coordinated impact nozzle 2 can be limited to prevent it from circumferential rotation. Controlling the number and position of the semicircular limiting holes 5 on the nozzle base 6 can achieve multiple circumferential orientation control of the gas multi-angle coordinated impact nozzle 2. The inner diameter of the nozzle base 6 is equal to the inner diameter of the gas multi-angle coordinated impact nozzle 2, and the outer diameter of the nozzle base 6 is larger than the outer diameter of the gas multi-angle coordinated impact nozzle 2. The outer diameter of the nozzle base 6 cooperates with the groove section of the combustion chamber docking section 1 to limit the axial and radial movement of the gas multi-angle coordinated impact nozzle 2.

[0047] like Figure 3As shown, two reference planes are defined for the multi-angle coordinated gas impact nozzle 2. These two reference planes are perpendicular to each other and pass through the centerline of the multi-angle coordinated gas impact nozzle 2. One of the planes is parallel to the inlet outlet plane and is designated as plane 1, while the other is designated as plane 2. The figure shows the centerline of the gas nozzle 7, the centerline of the multi-angle coordinated gas impact nozzle 2, projection line 1, projection line 2, plane 1, and plane 2. Projection line 1 is the projection of the centerline of the gas nozzle 7 onto plane 1, and projection line 2 is the projection of the centerline of the gas nozzle 7 onto plane 2. The angle between the centerline of the gas nozzle 7 and plane 2 is defined as the self-impact collision angle α. The angle between projection line 1 and the centerline of the multi-angle coordinated gas impact nozzle 2 is the angle between the centerline of the gas nozzle 7 and plane 2. Taking into account the impact of the angle between the gas injection direction and the intake duct on mixing, the angle between the centerline of each gas nozzle 7 and the intake duct outlet plane is defined as the mutual impact angle β. Because surface 1 is parallel to the intake duct outlet plane, the angle between the centerline of the gas nozzle 7 and surface 1 is equal to the mutual impact angle β. Therefore, adjusting the angle between the centerline of the gas nozzle 7 and surface 1 is equivalent to adjusting the mutual impact angle β. The angle between projection line 2 and the centerline of the multi-angle coordinated gas impact nozzle 2 is the angle between the centerline of the gas nozzle 7 and surface 1. By coordinating the self-impact angle α and the mutual impact angle β, the mutual impact angles between multiple gas streams and the gas deflection angle toward the intake duct can be adjusted, the gas self-impact position and the gas-air mutual impact position can be controlled, the uniformity of the flow field distribution is improved, and the mixing of gas and air in the afterburner is enhanced, thereby improving combustion efficiency. The coordinated control of the self-impact collision angle α and the mutual impact collision angle β is manifested as making the center line of the gas nozzle 7 and the center line of the gas multi-angle coordinated impact nozzle 2 form an angle θ. Obtaining the relationship between θ and α and β can more conveniently complete model building, which is convenient for nozzle design applied to different working conditions.

[0048] The relationship between the angle θ between the center line of the gas nozzle 7 and the center line of the gas multi-angle cooperative impact nozzle 2 and the self-impact collision angle α and the mutual impact collision angle β is expressed as follows:

[0049] cosθ=cosα·cosβ

[0050] like Figure 4 and Figure 5As shown, the small-diameter end of the combustion chamber docking section 1 is provided with a groove for supporting the outer diameter of the nozzle base 6. The combustion chamber docking section 1 can be divided into two parts, namely, the combustion chamber docking section 1 with the groove and the combustion chamber docking section 1 without the groove. The inner diameter of the combustion chamber docking section 1 with the groove is the same as the outer diameter of the nozzle base 6. The nozzle base 6 and the combustion chamber docking section with the groove are installed in a tolerance fit. The inner diameter of the combustion chamber docking section without the groove is the same as the outer diameter of the gas multi-angle coordinated impact nozzle 2. The gas multi-angle coordinated impact nozzle 2 and the combustion chamber docking section without the groove are installed in a tolerance fit. The groove is used to limit the axial and radial orientations of the gas multi-angle coordinated impact nozzle 2. Controlling the depth of the groove can control the distance between the gas multi-angle coordinated impact nozzle 2 and the afterburner inlet, thereby affecting the flow field in the afterburner. The depth of the groove refers to the distance between the interface between the grooved section of the combustion chamber docking section 1 and the non-grooved section of the combustion chamber docking section 1 and the end face of the small diameter end of the combustion chamber docking section 1. The grooved section of the combustion chamber docking section 1 is provided with a semicircular limiting hole 5 that matches the semicircular limiting hole 5 of the nozzle base 6. The large and small diameter ends of the combustion chamber docking section 1 are respectively provided with threaded holes 3 for realizing threaded connection. The multi-angle coordinated impact type nozzle 2 for gas is connected to the gas generator nozzle through the small diameter end of the combustion chamber docking section 1 by threaded connection; the multi-angle coordinated impact type nozzle 2 for gas is connected to the afterburner through the large diameter end of the combustion chamber docking section 1 by threaded connection. The threaded connection of the combustion chamber docking section 1 makes it easy to disassemble the combustion chamber docking section 1 and to replace different nozzles. It adapts to the need to adjust the self-impact collision angle α and the mutual impact collision angle β under different working conditions, facilitates the ground direct connection experiment of solid rocket ramjet engines under different working conditions, and reduces costs. In order to facilitate the regulation of multiple installation positions of the gas multi-angle coordinated impact nozzle 2, n threaded holes 3 are respectively opened at the large and small diameter ends of the combustion chamber docking section 1. The gas multi-angle coordinated impact nozzle 2 can achieve a 360 / n degree installation angle change, which is convenient for changing the installation position of the nozzle.

[0051] The present invention can control the installation orientation of the multi-angle collaborative impact nozzle 2 of the gas by the number of threaded holes 3 of the combustion chamber docking section 1 and the number and position of the semicircular limiting holes 5 of the nozzle base 6. The two are controlled in coordination to combine a variety of orientation angles to meet the needs of multiple tests in one processing.

[0052] like Figure 5 As shown, the diameter of the cylindrical pin 4 matches the diameter of the semicircular limiting hole 5. This matching means that the cylindrical pin 4 and the semicircular limiting hole 5 form an interference fit. The pin connection between the cylindrical pin 4 and the semicircular limiting hole 5 controls the circumferential orientation of the multi-angle coordinated gas impact nozzle 2 and the combustion chamber docking section 1, preventing the multi-angle coordinated gas impact nozzle 2 from circumferential rotation.

[0053] like Figure 6 As shown in (a), the change from blue to red indicates the change from low to high temperature. By comparing the total temperature, we can find that Figure 6 The high temperature area of ​​(b) is obviously larger than Figure 6 (c) is much larger. Not only is there a high-temperature area at the head of the afterburner, but high temperatures are also generated in the middle and rear parts of the afterburner. This shows that a large number of boron particles have chemically reacted with the air, causing the temperature of the afterburner to rise. This proves that the multi-angle coordinated impact nozzle 2 for gas designed by the present invention has a more obvious enhancing effect on the mixing effect of gas and air.

[0054] like Figure 7 As shown in (a), the change from blue to red indicates that the time the particles stay in the afterburner changes from short to long; Figure 7 (b) and (c) show that the use of the multi-angle coordinated impact nozzle 2 designed by the present invention can make the particles begin to disperse earlier, increase their contact area with the air, and be more conducive to the mixing of particles and air; and Figure 7 The self-impact angle of the multi-angle coordinated impact nozzle 2 for gas shown is only a special case. As the self-impact angle changes, the dispersion effect on the particles may become more obvious, and a recirculation zone of the flow field may also appear, which helps the particles to be sucked back to the head of the combustion chamber, which is more conducive to the dispersion and distribution of the particles and is conducive to mixed combustion.

[0055] In order to achieve the reusability of the gas multi-angle coordinated impact nozzle 2, the gas multi-angle coordinated impact nozzle 2 is processed using tungsten-infiltrated copper material. The tungsten-infiltrated copper material has the characteristics of high melting point and resistance to burning, and is resistant to high temperature and high temperature airflow erosion.

[0056] In order to facilitate processing and ensure smoother flow in the outer flow field of the cylindrical structure, the multi-angle coordinated impact type gas nozzle 2 is cylindrical.

[0057] In order to reduce the number of processing steps, the gas multi-angle coordinated impact nozzle 2 and the nozzle base 6 of the present invention are an integrated structure.

[0058] The working method of the multi-angle coordinated impact mixing enhancement device for solid rocket ramjet engine combustion gas disclosed in this embodiment is as follows:

[0059] This embodiment is used in a solid rocket ramjet engine, and the installation and fixation of the gas multi-angle coordinated impact nozzle 2 is achieved through the combustion chamber docking section 1, the cylindrical pin 4, and the nozzle base 6. In order to reduce the processing steps, the gas multi-angle coordinated impact nozzle 2 and the nozzle base 6 are an integrated structure. The small diameter end of the combustion chamber docking section 1 is provided with a groove for supporting the outer diameter of the nozzle base 6, so the combustion chamber docking section 1 is divided into two parts, namely the combustion chamber docking section 1 with groove section and the combustion chamber docking section 1 without groove section. The nozzle base 6 is installed in conjunction with the groove section of the combustion chamber docking section 1, and the said fitting is carried out by tolerance fitting; the gas multi-angle coordinated impact nozzle 2 is installed in conjunction with the non-groove section of the combustion chamber docking section 1, and the said fitting is carried out by tolerance fitting; the axial orientation and radial orientation of the gas multi-angle coordinated impact nozzle 2 are limited by the groove of the combustion chamber docking section 1. By controlling the depth of the groove, the distance between the multi-angle coordinated gas impact nozzle 2 and the inlet of the afterburner is controlled. The depth of the groove refers to the distance between the interface between the grooved section of the combustion chamber docking section 1 and the non-grooved section of the combustion chamber docking section 1 and the end face of the small diameter end of the combustion chamber docking section 1. Semicircular limiting holes 5 are respectively formed on the grooved section of the combustion chamber docking section 1 and the nozzle base 6. The semicircular limiting holes 5 on the combustion chamber docking section 1 and the semicircular limiting holes 5 on the nozzle base 6 are spliced ​​to form a circular hole. The cylindrical pin 4 is installed with an interference fit in the circular hole to limit the circumferential orientation of the multi-angle coordinated gas impact nozzle 2 and prevent it from rotating circumferentially. The large and small diameter ends of the combustion chamber docking section 1 are respectively provided with threaded holes 3 for threaded connection. The multi-angle coordinated gas impact nozzle 2 is connected to the gas generator nozzle through the small diameter end of the combustion chamber docking section 1 by threaded connection; the multi-angle coordinated gas impact nozzle 2 is connected to the afterburner through the large diameter end of the combustion chamber docking section 1 by threaded connection. The threaded connection of the combustion chamber docking section 1 makes it easy to disassemble the combustion chamber docking section 1 and replace different nozzles. It can adapt to the needs of adjusting the self-impact collision angle α and the mutual impact collision angle β under different working conditions, facilitate ground direct connection experiments of solid rocket ramjet engines under different working conditions, and reduce costs.

[0060] After installation, in actual use, the primary gas generated by the gas generator enters the multi-angle coordinated impactor nozzle 2 through the gas generator nozzle. The multi-angle coordinated impactor nozzle 2 is provided with an even number of gas nozzle holes 7, divided into two groups, with the centerlines of the gas nozzle holes 7 in each group intersecting. Numerical simulations have shown that in a contralaterally inlet solid rocket ramjet engine, when the primary gas enters the afterburner through four gas nozzle holes 7, the particles in the gas are more evenly dispersed. The multi-angle coordinated impactor nozzle 2 has four gas nozzle holes 7. This contralaterally inlet solid rocket ramjet engine refers to a solid rocket ramjet engine in which the inlets are symmetrically distributed on both sides of the afterburner centerline. The primary gas changes direction through the gas nozzle 7. By collaboratively adjusting the self-impact collision angle α and the mutual impact collision angle β, the angle θ between the center line of the gas nozzle 7 and the center line of the gas multi-angle collaborative impact nozzle 2 is controlled, thereby realizing the adjustment of the mutual impact angle between multiple gas streams and the deflection angle of the gas toward the air inlet side, realizing the control of the gas self-impact position and the control of the mutual impact position of the gas and air, improving the uniformity of the flow field distribution, realizing the enhanced mixing of the gas and air in the afterburner, thereby improving the combustion performance and improving the combustion efficiency.

[0061] By multi-angle control of the gas nozzle 7, control of the axial, radial, and circumferential installation positions of the multi-angle coordinated gas impact nozzle 2, and control of the distance between the multi-angle coordinated gas impact nozzle 2 and the inlet of the afterburner, the mixed combustion effect of the gas and air is controlled from multiple dimensions.

[0062] The above description further illustrates the objectives, technical solutions and advantages of the present invention in detail. It should be understood that the above description is only a specific embodiment of the present invention, which is used to explain the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A multi-angle coordinated impact mixing enhancement device for solid rocket ramjet engine combustion gas, characterized by: It mainly consists of a combustion chamber docking section, a gas multi-angle coordinated impact nozzle, a threaded hole, a cylindrical pin, a semicircular limiting hole, a nozzle base, and a gas nozzle hole. The multi-angle coordinated impact type gas nozzle is provided with gas nozzle holes for spraying the primary gas of the solid rocket ramjet engine into the afterburner and generating a multi-angle coordinated impact effect; the number of gas nozzle holes on the multi-angle coordinated impact type gas nozzle is an even number, and the gas nozzle holes are divided into two groups, the two groups of nozzle holes are symmetrically distributed along the center line of the nozzle, the center lines of the gas nozzle holes of each group intersect, the primary gas generated by the gas generator changes direction through the gas nozzle holes and enters the afterburner to generate two groups of self-impact gas; two reference planes of the multi-angle coordinated impact type gas nozzle are defined, the two reference planes are perpendicular to each other and pass through the center line of the multi-angle coordinated impact type gas nozzle, one of the planes is parallel to the plane of the air inlet outlet, named plane 1, and the other plane is named plane 2; the angle between the center line of the gas nozzle hole and plane 2 is defined as the self-impact collision angle α, and at the same time, considering the influence of the angle between the gas injection direction and the air inlet on the mixing, the angle between the center line of each gas nozzle hole and the air inlet outlet plane is defined as the mutual impact collision angle β, and the deflection angle of the gas relative to the air inlet is controlled by adjusting the mutual impact collision angle β. degree; because surface 1 is parallel to the plane of the air inlet duct outlet, the angle between the center line of the gas nozzle hole and surface 1 is equal to the mutual impact collision angle β, so adjusting the angle between the center line of the gas nozzle hole and surface 1 is to adjust the mutual impact collision angle β; by coordinating the self-impact collision angle α and the mutual impact collision angle β, the angles of mutual impact between multiple gas streams and the deflection angle of the gas toward the air inlet duct side are adjusted, the self-impact position of the gas and the mutual impact position of the gas and air are controlled, the uniformity of the flow field distribution is improved, and the afterburner is realized. The mixing of gas and air is enhanced, thereby improving combustion performance and increasing combustion efficiency; the coordinated control of the self-impact collision angle α and the mutual-impact collision angle β is manifested in that an angle θ is generated between the center line of the gas nozzle and the center line of the gas multi-angle coordinated impact nozzle, and an angular relationship between the angle θ and the self-impact collision angle α and the mutual-impact collision angle β is established. According to the relationship between the angle θ and α and β, the nozzles for different working conditions can be more conveniently optimized, the optimization efficiency of the nozzle design under different working conditions is improved, and different nozzles are easily replaced to adapt to different working conditions; The relationship between the angle θ between the center line of the gas nozzle and the center line of the gas multi-angle cooperative impact nozzle and the self-impact collision angle α and the mutual impact collision angle β is expressed as follows: cosθ=cosα·cosβ The nozzle base is provided with a semicircular limiting hole for limiting the circumferential rotation of the gas multi-angle coordinated impact nozzle. By controlling the number and spacing angles of the semicircular limiting holes on the nozzle base, various circumferential orientation designs of the gas multi-angle coordinated impact nozzle can be realized. The inner diameter of the nozzle base is equal to the inner diameter of the gas multi-angle coordinated impact nozzle, and the outer diameter of the nozzle base is larger than the outer diameter of the gas multi-angle coordinated impact nozzle. The outer diameter of the nozzle base cooperates with the combustion chamber docking section to form a groove section, thereby limiting the axial and radial movement of the gas multi-angle coordinated impact nozzle. The small diameter end of the combustion chamber docking section is provided with a groove for supporting the outer diameter of the nozzle base, so the combustion chamber docking section is divided into two parts, namely the combustion chamber docking section with a groove section and the combustion chamber docking section without a groove section; the inner diameter of the combustion chamber docking section with a groove section is the same as the outer diameter of the nozzle base, and the nozzle base and the combustion chamber docking section with a groove section are cooperated and installed, and the cooperation installation adopts tolerance fitting; the inner diameter of the combustion chamber docking section without a groove section is the same as the outer diameter of the gas multi-angle coordinated impact type nozzle, and the gas multi-angle coordinated impact type nozzle is cooperated and installed with the combustion chamber docking section without a groove section, and the cooperation installation adopts tolerance fitting; the groove is used to limit the axial and radial orientations of the gas multi-angle coordinated impact type nozzle; controlling the depth of the groove can control the distance between the gas multi-angle coordinated impact type nozzle and the inlet of the afterburner, thereby affecting the flow field in the afterburner; the depth of the groove refers to the interface distance between the combustion chamber docking section with a groove section and the combustion chamber docking section without a groove section The distance between the end faces of the small diameter ends of the sections; the combustion chamber docking section has a groove section provided with a semicircular limiting hole adapted to the semicircular limiting hole of the nozzle base, and the semicircular limiting hole on the combustion chamber docking section and the semicircular limiting hole on the nozzle base are spliced ​​to form a circular hole, and the circumferential orientation restriction of the multi-angle coordinated impact type nozzle of the gas is realized by the interference fit of the cylindrical pin and the circular hole, so as to prevent it from circumferential rotation; the large and small diameter ends of the combustion chamber docking section are respectively provided with threaded holes for realizing threaded connection, and the multi-angle coordinated impact type nozzle of the gas is connected to the gas generator nozzle through the small diameter end of the combustion chamber docking section by threaded connection; the multi-angle coordinated impact type nozzle of the gas is connected to the afterburner through the large diameter end of the combustion chamber docking section by threaded connection; the combustion chamber docking section adopts a threaded connection, which makes the combustion chamber docking section easy to disassemble and easy to replace different nozzles, adapting to the needs of adjusting the self-impact collision angle α and the mutual impact collision angle β under different working conditions, facilitating the ground direct connection experiment of the solid rocket ramjet engine under different working conditions, and reducing costs; The diameter of the cylindrical pin is adapted to the aperture of the semicircular limiting hole, and the adaptation refers to the interference fit between the cylindrical pin and the semicircular limiting hole; the circumferential orientation relationship between the multi-angle coordinated impact nozzle of the gas and the docking section of the combustion chamber is controlled by the pin connection between the cylindrical pin and the semicircular limiting hole to prevent the nozzle from circumferential rotation.

2. The solid rocket ramjet engine combustion gas multi-angle coordinated impact mixing enhancement device according to claim 1, characterized in that: The multi-angle coordinated impact type nozzle for the gas is placed at the entrance of the afterburning chamber, and can achieve coordinated impact without intruding into the afterburning chamber, thereby enhancing mixing.

3. The solid rocket ramjet engine combustion gas multi-angle coordinated impact mixing enhancement device according to claim 1, characterized in that: The number of gas spray holes on the multi-angle coordinated impact type gas nozzle is four, and the four gas spray holes are divided into two groups.

4. The solid rocket ramjet engine combustion gas multi-angle coordinated impact mixing enhancement device according to claim 1, characterized in that: There are n threaded holes at both ends of the large and small diameter ends of the combustion chamber docking section, so as to realize the 360 / n degree installation angle change of the multi-angle coordinated impact nozzle of the gas, and facilitate the change of the installation orientation of the nozzle.

5. The solid rocket ramjet engine combustion gas multi-angle coordinated impact mixing enhancement device according to claim 1, characterized in that: The installation orientation of the multi-angle coordinated impact nozzle of the gas is controlled by the number of threaded holes in the combustion chamber docking section and the number and position of the semicircular limiting holes in the nozzle base. The coordinated control of the two can combine a variety of orientation angles to meet the needs of multiple tests in one processing.

6. The solid rocket ramjet engine combustion gas multi-angle coordinated impact mixing enhancement device according to claim 1, characterized in that: The multi-angle coordinated gas impact nozzle is made of tungsten copper infiltrated material.

7. The solid rocket ramjet engine combustion gas multi-angle coordinated impact mixing enhancement device according to claim 1, characterized in that: The multi-angle coordinated impact type gas nozzle is cylindrical.

8. The solid rocket ramjet engine combustion gas multi-angle coordinated impact mixing enhancement device according to claim 1, characterized in that: The gas multi-angle coordinated impact nozzle and the nozzle base are an integrated structure.

9. The solid rocket ramjet engine combustion gas multi-angle coordinated impact mixing enhancement device according to any one of claims 1 to 8, characterized in that: The installation and fixation of the gas multi-angle coordinated impact nozzle are achieved through the combustion chamber docking section, the nozzle base and the cylindrical pin; in order to reduce the processing procedures, the gas multi-angle coordinated impact nozzle and the nozzle base are an integrated structure; the small diameter end of the combustion chamber docking section is provided with a groove for supporting the outer diameter of the nozzle base, so the combustion chamber docking section is divided into two parts, namely the combustion chamber docking section with a groove section and the combustion chamber docking section without a groove section; the nozzle base is installed in cooperation with the groove section of the combustion chamber docking section, and the installation is carried out with tolerance fit; the gas multi-angle coordinated impact nozzle is installed in cooperation with the non-grooved section of the combustion chamber docking section, and the installation is carried out with tolerance fit; the axial and radial positions of the gas multi-angle coordinated impact nozzle are limited by the groove of the combustion chamber docking section; the distance between the gas multi-angle coordinated impact nozzle and the inlet of the afterburner is controlled by controlling the depth of the groove, and the depth of the groove refers to the interface distance between the groove section of the combustion chamber docking section and the non-grooved section of the combustion chamber docking section The distance between the end faces of the small diameter end of the chamber docking section; the combustion chamber docking section has a groove section and a semicircular limiting hole on the nozzle base, and the semicircular limiting hole on the combustion chamber docking section and the semicircular limiting hole on the nozzle base are spliced ​​to form a circular hole, and the cylindrical pin is installed with an interference fit with the circular hole to limit the circumferential orientation of the gas multi-angle coordinated impact type nozzle and prevent it from circumferential rotation; the large and small diameter ends of the combustion chamber docking section are respectively provided with threaded holes for threaded connection, and the gas multi-angle coordinated impact type nozzle is connected to the gas generator nozzle through the small diameter end of the combustion chamber docking section by threaded connection; the gas multi-angle coordinated impact type nozzle is connected to the afterburner through the large diameter end of the combustion chamber docking section by threaded connection; the threaded connection of the combustion chamber docking section makes it easy to disassemble the combustion chamber docking section, convenient for replacing different nozzles, and adapts to the needs of adjusting the self-impact collision angle α and the mutual impact collision angle β under different working conditions, and is convenient for ground direct connection experiments of solid rocket ramjet engines under different working conditions, reducing costs; After the installation is completed, in actual application, the primary gas generated by the gas generator enters the gas multi-angle coordinated impact nozzle through the gas generator nozzle. The gas multi-angle coordinated impact nozzle is provided with an even number of gas nozzle holes, which are divided into two groups, and the center lines of the gas nozzle holes in each group intersect; through numerical simulation, it is found that in the solid rocket ramjet engine with opposite side intake, when the primary gas enters the afterburner through four gas nozzle holes, it can produce the effect of making the particles in the gas more evenly dispersed. The number of gas nozzle holes on the gas multi-angle coordinated impact nozzle is four; the solid rocket ramjet engine with opposite side intake The engine refers to a solid rocket ramjet engine with air inlets symmetrically distributed on both sides of the center line of the afterburner; the primary gas changes direction through the gas nozzle, and by cooperatively adjusting the self-impact collision angle α and the mutual impact collision angle β, the angle θ between the center line of the gas nozzle and the center line of the gas multi-angle cooperative impact nozzle is controlled, so as to adjust the mutual impact angle between multiple gas streams and the deflection angle of the gas toward the air inlet side, realize the control of the gas self-impact position and the gas-air mutual impact position, improve the uniformity of the flow field distribution, realize the enhanced mixing of gas and air in the afterburner, thereby improving the combustion performance and increasing the combustion efficiency; The mixed combustion effect of gas and air is controlled from multiple dimensions through multi-angle control of the gas nozzle, control of the axial, radial and circumferential installation positions of the multi-angle coordinated gas impact nozzle and control of the distance between the multi-angle coordinated gas impact nozzle and the inlet of the afterburner.

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