Solid-liquid rocket that can be mass-produced industrially

Abstract

The application discloses a solid-liquid rocket which can be produced in an industrialized manner, and comprises, from top to bottom, a fairing, a load cabin, an oxidant storage tank, a Laval nozzle, a starting assembly and a filling pipe. The rocket is disassembled into standardized modules of the fairing, the load cabin, the oxidant storage tank, the Laval nozzle, the starting assembly and the filling pipe, the modules can be produced in parallel, and mature industrialized processes are adopted in all processing links, so that the period of rocket assembly is greatly shortened, and the efficiency of mass production is improved. The load cabin, the oxidant storage tank, the Laval nozzle and the filling pipe are made of stainless steel, and the starting assembly is made of brass, so that the material cost, the processing cost and the assembly cost are greatly reduced; the core structure of the rocket can be produced in an industrialized manner, so that the manufacturing cost of a single rocket is fundamentally reduced, efficient mass production and rapid assembly design are realized, the launch preparation period is shortened, and the operation cost is reduced.

Description

Technical Field

[0001] This invention specifically relates to solid-liquid rockets. Background Technology

[0002] Currently, there is an urgent need in the space sector for a low-cost launch vehicle to increase the number of launches and improve space transportation capabilities.

[0003] Solid-liquid rocket engines are a new type of rocket propulsion system that uses a combination of liquid oxidizer and solid fuel as propellants. Because the fuel and oxidizer are stored separately, solid-liquid engines possess unique characteristics that distinguish them from solid or liquid engines, offering advantages such as good economy, safety, environmental friendliness, and easy thrust adjustment. However, existing solid-liquid rockets mostly employ a customized production model, resulting in complex structures, cumbersome assembly processes, and poor component interchangeability. This leads to long production cycles and high costs, making it difficult to meet the "high-frequency, low-cost" launch requirements of commercial spaceflight.

[0004] The present invention aims to provide a mass-producible solid-liquid engine rocket through technological improvements, thereby fundamentally reducing the manufacturing and launch costs of solid-liquid engine rockets through mass production. Summary of the Invention

[0005] To overcome the shortcomings mentioned above, the present invention aims to provide a technical solution that can solve the above problems.

[0006] A solid-liquid rocket that can be mass-produced industrially includes: a fairing, a payload compartment, an oxidizer tank, and a Laval nozzle arranged sequentially from top to bottom; it also includes an initiation assembly and a refueling pipe.

[0007] The oxidant tank consists of an upper head, an arrow body, a lower head, and an injector; both the upper head and the lower head are hemispherical, and the top and bottom surfaces of the arrow body are fixedly welded to the periphery of the upper head and the periphery of the lower head, respectively.

[0008] The injector is a cylindrical shape with a closed top. A limiting ring is provided on the outer side of the middle section. An installation hole is provided at the center of the lower end cap. The injector is installed in the installation hole. The upper end face of the limiting ring is fixedly welded to the lower end face of the lower end cap. The upper end of the injector is also provided with multiple tangential holes, which are located inside the oxidant storage tank.

[0009] The top of the filling tube is provided with a mounting head, which is connected to the liquid outlet of the injector by a Teflon gasket. The outer diameter of the filling tube is smaller than the outer diameter of its mounting head.

[0010] The starting assembly is a cylindrical shape with a closed bottom and a stepped surface on its inner wall. A through hole is opened in the center of the closed bottom surface of the starting assembly. The filling pipe extends through the through hole in the direction of the Laval nozzle. The stepped surface abuts against the lower end face of the mounting head. The upper end of the starting assembly is welded to the outside of the injector.

[0011] Preferably, an air inlet pipe is provided at the center of the upper end cap, which is used to introduce high-pressure gas into the oxidant storage tank;

[0012] Preferably, the starting component is made of brass and has an internal cavity for receiving starting gunpowder. An annular stress groove is formed on the outer wall of the middle part of the starting component.

[0013] Preferably, the bottom closed surface of the starting component is further provided with a wire hole;

[0014] Preferably, the industrially mass-producible solid-liquid rocket further includes a high-pressure gas cylinder, which is installed inside the payload compartment close to the upper end cap and is connected to the air inlet pipe via an electromagnetic valve.

[0015] Preferably, the mass production process of the industrially producible solid-liquid rocket includes: oxidizer tank molding, Laval nozzle manufacturing, fairing molding, start-up component processing, performance testing of each component, and rocket assembly.

[0016] Preferably, the method for forming the oxidant storage tank is as follows:

[0017] The injector is formed by turning and has a limiting ring; the injector is drilled with a tangential hole.

[0018] The upper end cap and the lower end cap are formed by hot stamping;

[0019] The upper end cap is pre-drilled with an air inlet hole by CNC drilling, one end of the air inlet pipe is inserted into the air inlet hole and the circumferential seam is sealed by welding;

[0020] The lower end cap is pre-drilled with a CNC drilling machine to create a mounting hole. The upper end of the injector is then inserted into the mounting hole so that the limiting ring fits against the lower end cap and the sealing ring seam is welded.

[0021] The arrow body is formed by rolling and then laser welding the longitudinal seams.

[0022] Align the upper and lower ends of the arrow body with the circumferential bevels of the upper and lower end caps respectively, and fix them with circumferential welding fixtures.

[0023] The welded oxidant tank was then placed in a heat treatment furnace for solution treatment, and the formed oxidant tank underwent a hydrostatic test.

[0024] Preferably, the method for manufacturing the Laval nozzle is as follows:

[0025] Stainless steel bar is selected, and its upper end is machined into a cylindrical combustion chamber with an inner cavity. Its lower end is machined into a nozzle with a converging section, a throat, and a diverging section, so that the Laval nozzle is initially machined into shape.

[0026] The formed Laval nozzle is subjected to contour scanning and aerodynamic performance testing, and then further precision turning.

[0027] Preferably, the method for processing the startup component is as follows:

[0028] The cylindrical structure with a closed bottom, stepped inner wall, a central through hole at the bottom, and a wire hole at the bottom is produced by turning brass bars.

[0029] An annular stress groove is formed by machining the outer wall of the middle part of the starting component.

[0030] Preferably, the method for assembling the rocket is as follows:

[0031] S1. Hoist the Laval nozzle to the support fixture and fix it vertically, then install and fix the solid propellant charge into the combustion chamber at the upper end of the Laval nozzle.

[0032] S2. Hoist the oxidizer tank to the top of the Laval nozzle of the supporting fixture, assemble the starting explosive in the starting assembly, and connect the fuse through the wire hole to the starting explosive. Pass the filling pipe through the through hole of the starting explosive and the starting assembly from top to bottom, and make the mounting head of the filling pipe abut against the stepped surface of the inner wall of the starting assembly. Place a Teflon gasket on the mounting head, and thread the starting assembly containing the starting explosive to the injector.

[0033] S3. The oxidant tank is slowly lowered through the lifting mechanism of the supporting fixture, and the injection pipe is lowered vertically along the axis of the central through hole of the propellant column. The oxidant tank is precisely connected to the Laval nozzle and the circumferential weld is performed.

[0034] S4. Hoist the high-pressure gas cylinder to the top of the upper end cap, connect the gas cylinder group to the storage tank inlet pipe with a stainless steel gas guide pipe, connect the valve, sensor and flow regulating valve in series and complete the sealing test.

[0035] S5. Install and connect the control system, hoist the load chamber onto the top of the head, and weld it in place;

[0036] S6. Hoist the load onto the mounting frame inside the load compartment, align it with the separation mechanism interface, tighten the fixing bolts, and install the fairing above the load compartment.

[0037] Compared with the prior art, the advantages of the present invention are:

[0038] The industrially mass-producible solid-liquid rocket of this invention achieves high reliability, high efficiency, and low cost through structural optimization and process innovation.

[0039] This invention disassembles the rocket into standardized modules such as fairing, payload compartment, oxidizer tank, Laval nozzle, start-up assembly, and refueling pipe. Each module can be produced in parallel, and all processing steps adopt mature industrial processes, which greatly shortens the rocket assembly cycle and improves the efficiency of mass production.

[0040] The core structure of this invention, including the load chamber, oxidant tank, Laval nozzle, and filling pipe, is made of stainless steel, while the starting components are made of brass, which significantly reduces material costs, processing costs, and assembly costs.

[0041] The core structure of the rocket can be industrially mass-produced, thereby fundamentally reducing the manufacturing cost of a single rocket. Efficient mass production and rapid assembly design shorten the launch preparation cycle, thereby reducing operating costs.

[0042] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0043] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0044] Figure 1 This is a schematic diagram of the overall structure of the present invention.

[0045] Figure 2 This is an enlarged schematic diagram of the connection between the payload compartment, the upper head, and the rocket body.

[0046] Figure 3 This is an enlarged schematic diagram of the connection between the rocket body, lower end cap, and Laval nozzle.

[0047] Figure 4 This is an enlarged view of the connection between the injector and the starting assembly.

[0048] Figure 5 This is a diagram illustrating the working principle of the rocket injector after ignition.

[0049] Figure 6 It is an exploded structural diagram of the injector, Teflon gasket, filling pipe, and starting assembly. Detailed Implementation

[0050] The technical solutions in the embodiments of the present invention will be clearly and completely described below. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0051] In the description of this invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0052] Furthermore, in the description of this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components; they can refer to a wireless connection or a wired connection. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0053] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0054] Please see Figures 1-6 In this embodiment of the invention, a solid-liquid rocket that can be mass-produced industrially includes a fairing 1, a payload compartment 2, an oxidizer tank 3, and a Laval nozzle 4 arranged sequentially from top to bottom, and also includes a starting assembly 5 and a refueling pipe 6.

[0055] This embodiment of the industrially mass-producible solid-liquid rocket, through structural optimization and process innovation, enables the core structure of the rocket to be industrially mass-produced, achieving high reliability, high efficiency, and low cost. The rocket's electronic control system uses mature, industrially mass-produced standardized products such as MCUs, power supplies, signal acquisition, ignition drive, pressure detection, valve control, and separation control. Through customized circuit integration, the procurement, assembly, maintenance, and inventory costs of the electronic control system are reduced, achieving economic efficiency. This, in turn, significantly reduces the overall cost of rocket assembly and ultimately improves the rocket's carrying capacity.

[0056] Specifically, the fairing 1 can be integrally molded from carbon fiber reinforced composite material, or it can be made of other materials more suitable for industrial mass production.

[0057] Specifically, the load chamber 2 is a cylindrical shell made of stainless steel, and it contains a load mounting frame and a separation mechanism. The separation mechanism adopts a spring-type separation design.

[0058] Specifically, the oxidizer tank 3 serves as the main body of the rocket body 32, and consists of an upper end cap 31, the rocket body 32, a lower end cap 33, and an injector 34.

[0059] Both the upper end cap 31 and the lower end cap 33 are made of hemispherical stainless steel and are formed by hot stamping.

[0060] The upper end cap 31 is pre-drilled with an air inlet hole by CNC drilling, and one end of the air inlet pipe 311 is inserted into the air inlet hole and sealed with argon arc welding.

[0061] The lower end cap 33 is machined with pre-drilled mounting holes using CNC drilling;

[0062] The top and bottom surfaces of the rocket body 32 are fixedly welded to the periphery of the upper end cap 31 and the periphery of the lower end cap 33, respectively.

[0063] The injector 34 is a cylindrical shape with a closed top and is made of stainless steel. A limiting ring 342 is provided on the outer side of its middle section. Multiple tangential holes 341 are also provided at the upper end of the injector 34, and the tangential holes 341 are located inside the oxidant storage tank 3.

[0064] Insert the upper end of the injector 34 into the mounting hole so that the limiting ring 342 fits against the lower end cap 33, and use argon arc welding to seal the circumferential seam.

[0065] Align the upper and lower ends of the rocket body 32 with the circumferential bevels of the upper end cap 31 and the lower end cap 33 respectively, fix them with circumferential welding fixtures, and perform submerged arc welding.

[0066] Specifically, the filling tube 6 is made of 316L stainless steel, and its top is equipped with a mounting head 61. The mounting head 61 and the liquid outlet end of the injector 34 are connected by a Teflon gasket 7. The outer diameter of the filling tube 6 is smaller than the outer diameter of its mounting head 61.

[0067] Specifically, the starting component 5 is made of brass and is a cylindrical structure with a closed bottom. Its interior is a cavity for receiving starting gunpowder. The inner wall of the starting component 5 is provided with a stepped surface 52, and a through hole 53 is opened in the center of its closed bottom surface. An annular stress groove 51 is opened on its outer wall, and a wire hole 54 is also opened on its closed bottom surface.

[0068] Specifically, the solid-liquid rockets that can be mass-produced industrially also include high-pressure gas cylinders (not shown in the attached diagram). The high-pressure gas cylinders are made of 316L stainless steel and typically operate at a pressure of 10MPa. They are installed inside the payload compartment 2 near the upper end cap 31 and are connected to the air inlet pipe 311 via a solenoid valve.

[0069] In this embodiment, the filling tube 6 extends through the through hole 53 in the spray direction of the Laval nozzle 4, the stepped surface 52 abuts against the lower end face of the mounting head 61, and the upper end of the starting component 5 is welded to the outside of the injector 34.

[0070] During ignition, the control system sends an ignition signal to the ignition circuit of the solenoid valve and the starting component 5. The fuse instantly ignites the starting propellant inside the starting component 5. The combustion of the starting propellant generates high-temperature and high-pressure gas, which acts on the bottom closed surface of the starting component 5. Since the outer wall in the middle is provided with an annular stress groove 51, after the gas pressure exceeds the structural strength threshold at the stress groove 51, the starting component 5 breaks along the stress groove 51. After the breakage, the lower section of the starting component 5 and the injection pipe 6 are completely separated from the injector 34 and discharged downward with the gas flow.

[0071] At the same time, high-pressure nitrogen gas of at least 10 MPa is introduced into the oxidant storage tank 3 through a solenoid valve (not shown in the attached figure). Under the action of nitrogen pressure, the liquid oxidant is ejected at high speed through multiple tangential holes 341 of the injector 34 to form a rotating jet. The chemical combustion produced by the mixing of the rotating jet and the combustion of the propellant column causes the pressure in the combustion chamber 41 to continue to increase. Finally, the gas is accelerated to several Mach through the Laval nozzle 4, which propels the rocket into the air.

[0072] In this embodiment, the liquid oxidant is ejected at high speed through multiple tangential holes 341 of the injector 34 to form a rotating jet. When the rotating jet is sprayed into the combustion chamber, it spreads rapidly and cools the inner wall of the Laval nozzle.

[0073] In the structure of this invention, in addition to the electronic control system, an auxiliary engine can be added or air can be extracted from the combustion chamber 41 to adjust the rocket's flight direction. This is prior art and will not be described in detail here.

[0074] The mass production process of solid-liquid rockets that can be industrially mass-produced includes: oxidizer tank 3 molding, Laval nozzle 4 manufacturing, fairing 1 molding, start-up assembly 5 processing, performance testing of each component, and rocket assembly.

[0075] In this embodiment of the invention, the method for forming the oxidant storage tank 3 is as follows:

[0076] The stainless steel bar of the injector 34 is machined into shape by CNC lathe and the limiting ring 342 is machined. Multiple tangential holes 341 are drilled by four-axis CNC machining center to form the injector 34.

[0077] The upper end cap 31 and the lower end cap 33 are formed by hot stamping of 304L stainless steel plate, with a heating temperature of 1000℃ and a stamping pressure of about 6000KN.

[0078] The upper end cap 31 is pre-drilled with an air inlet hole by CNC drilling, and one end of the air inlet pipe 311 is inserted into the air inlet hole and sealed with argon arc welding.

[0079] The lower head 33 is pre-drilled with CNC drilling to make a reserved installation hole. The upper end of the injector 34 is embedded into the installation hole so that the limiting ring 342 fits the lower head 33. The circumferential seam is sealed by argon arc welding.

[0080] The rocket body 32 is made of 304L stainless steel coils rolled into a circle by a three-roll plate rolling machine, and the longitudinal seams are laser welded.

[0081] Align the upper and lower ends of the arrow body 32 with the circumferential bevels of the upper end cap 31 and the lower end cap 33 respectively, and fix them with circumferential welding fixtures.

[0082] The welded oxidant storage tank 3 is placed in a heat treatment furnace for solution treatment, and the formed oxidant storage tank 3 is subjected to a water pressure test.

[0083] In this embodiment of the invention, the method for manufacturing the Laval nozzle 4 is as follows:

[0084] 310S stainless steel bar is selected and machined by CNC lathe. The upper end is machined into a cylindrical combustion chamber 41 with an inner cavity, and the lower end is machined into a converging section, throat and expansion section, which is initially machined into shape.

[0085] A laser profile scanner was used to scan the profile of the formed Laval nozzle 4, and combined with aerodynamic performance testing, precision turning correction was performed.

[0086] In this embodiment of the invention, the method for forming the fairing 1 is as follows:

[0087] It is manufactured using carbon fiber reinforced epoxy resin composite material through compression molding process;

[0088] After the fairing 1 is formed, it is trimmed and polished, and then fitted with hinges and locking mechanisms.

[0089] In this embodiment of the invention, the method for initiating the processing of component 5 is as follows:

[0090] Brass bars are selected and machined into a cylindrical structure with a closed bottom, a stepped inner wall surface 52, a through hole 53 in the center of the bottom, and a wire hole 54 at the bottom by CNC lathe.

[0091] An annular stress groove 51 is formed by machining the outer wall of the middle part of the starting component 5.

[0092] In this embodiment of the invention, the performance testing of each component includes:

[0093] Water pressure test of oxidant storage tank 3;

[0094] Aerodynamic performance testing of Laval nozzle 4;

[0095] High-pressure cylinder pressure resistance test;

[0096] Functional testing of the separation mechanism;

[0097] Control system integration and testing.

[0098] In this embodiment of the invention, the method for rocket assembly is as follows:

[0099] S1. Hoist the Laval nozzle 4 to the support fixture and fix it vertically, then install and fix the solid propellant into the combustion chamber 41 at the upper end of the Laval nozzle 4.

[0100] S2. Hoist the oxidizer tank 3 above the Laval nozzle 4 of the supporting fixture, assemble the starting explosive in the starting assembly 5, and connect the fuse through the wire hole 54 to the starting explosive. Pass the filling pipe 6 through the through hole 53 of the starting explosive and the starting assembly 5 from top to bottom, and make the mounting head 61 of the filling pipe 6 abut against the stepped surface 52 of the inner wall of the starting assembly 5. Place the Teflon gasket 7 above the mounting head 61, and thread the starting assembly 5 containing the starting explosive to the injector 34.

[0101] S3. The oxidant tank 3 is slowly lowered through the lifting mechanism of the supporting fixture, and the filling pipe 6 is lowered vertically along the central axis hole of the propellant column. The oxidant tank 3 is precisely connected to the Laval nozzle 4 and circumferentially welded.

[0102] S4. Hoist the high-pressure gas cylinder to the top of the upper end cap 31, connect the gas cylinder group to the storage tank inlet pipe 311 with a stainless steel gas guide pipe, connect the valve, sensor and flow regulating valve in series and complete the sealing test.

[0103] S5. Install and connect the control system, hoist the load chamber 2 onto the top of the head 31, and weld it in place;

[0104] S6. Hoist the load onto the mounting bracket inside the load compartment 2, align it with the separation mechanism interface, tighten the fixing bolts, and install the fairing 1 above the load compartment 2.

[0105] In another embodiment, a chuck may be provided at the top of the Laval nozzle 4, and the oxidant tank 3 and the Laval nozzle 4 may be fixedly connected by the chuck.

[0106] This invention disassembles the rocket into standardized modules such as fairing 1, payload compartment 2, oxidizer tank 3, Laval nozzle 4, start-up assembly 5, and refueling pipe 6. Each module can be produced in parallel, and all processing steps adopt mature industrial processes, which greatly shortens the rocket assembly cycle and improves the efficiency of mass production.

[0107] The core structures of this invention, namely the load chamber 2, oxidant tank 3, Laval nozzle 4, and filling pipe 6, are all made of stainless steel, while the starting assembly 5 is made of brass, which greatly reduces material costs, processing costs, and assembly costs.

[0108] The core structure of the rocket is modular, enabling mass production in the industry. The electronic control system uses mature industrially manufactured electronic control modules and solenoid valves, which fundamentally reduces the manufacturing cost of a single rocket. The efficient mass production and rapid assembly design shorten the launch preparation cycle, thereby reducing operating costs.

[0109] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within the present invention.

Claims

1. A solid-liquid rocket that can be mass-produced industrially, characterized in that, include: The fairing, load chamber, oxidizer tank, and Laval nozzle are arranged sequentially from top to bottom, and also include a start-up assembly and a refueling pipe; The oxidant tank consists of an upper head, an arrow body, a lower head, and an injector; both the upper head and the lower head are hemispherical, and the top and bottom surfaces of the arrow body are fixedly welded to the periphery of the upper head and the periphery of the lower head, respectively. The injector is a cylindrical shape with a closed top. A limiting ring is provided on the outer side of the middle section. An installation hole is provided at the center of the lower end cap. The injector is installed in the installation hole. The upper end face of the limiting ring is fixedly welded to the lower end face of the lower end cap. The upper end of the injector is also provided with multiple tangential holes, which are located inside the oxidant storage tank. The top of the filling tube is provided with a mounting head, which is connected to the liquid outlet of the injector by a Teflon gasket. The outer diameter of the filling tube is smaller than the outer diameter of its mounting head. The starting assembly is a cylindrical shape with a closed bottom and a stepped surface on its inner wall. A through hole is opened in the center of the closed bottom surface of the starting assembly. The injection pipe extends through the through hole in the direction of the Laval nozzle. The stepped surface abuts against the lower end face of the mounting head. The upper end of the starting assembly is welded to the outside of the injector.

2. The industrially mass-producible solid-liquid rocket according to claim 1, characterized in that, An air inlet pipe is provided at the center of the upper end cap, which is used to introduce high-pressure gas into the oxidant storage tank.

3. The industrially mass-producible solid-liquid rocket according to claim 2, characterized in that, The starting component is made of brass and has an internal cavity for receiving the starting gunpowder. An annular stress groove is formed on the outer wall of the middle part of the starting component.

4. The industrially mass-producible solid-liquid rocket according to claim 3, characterized in that, The bottom closed surface of the starting component also has a wire hole.

5. The industrially mass-producible solid-liquid rocket according to claim 4, characterized in that, It also includes a high-pressure gas cylinder, which is installed inside the load chamber close to the upper end cap and is connected to the air inlet pipe via a solenoid valve.

6. The industrially mass-producible solid-liquid rocket according to claim 5, characterized in that, The mass production process of the solid-liquid rocket that can be industrially mass-produced includes: oxidizer tank molding, Laval nozzle manufacturing, fairing molding, start-up component processing, performance testing of each component, and rocket assembly.

7. The industrially mass-producible solid-liquid rocket according to claim 6, characterized in that, The method for forming the oxidant storage tank: The injector is formed by turning and has a limiting ring; the injector is drilled with a tangential hole. The upper end cap and the lower end cap are formed by hot stamping; The upper end cap is pre-drilled with an air inlet hole by CNC drilling, one end of the air inlet pipe is inserted into the air inlet hole and the circumferential seam is sealed by welding; The lower end cap is pre-drilled with a CNC drilling machine to create a mounting hole. The upper end of the injector is then inserted into the mounting hole so that the limiting ring fits against the lower end cap and the sealing ring seam is welded. The arrow body is formed by rolling and then laser welding the longitudinal seams. Align the upper and lower ends of the arrow body with the circumferential bevels of the upper and lower end caps respectively, and fix them with circumferential welding fixtures. The welded oxidant tank was then placed in a heat treatment furnace for solution treatment, and the formed oxidant tank underwent a hydrostatic test.

8. The industrially mass-producible solid-liquid rocket according to claim 6, characterized in that, The method for manufacturing the Laval nozzle: Stainless steel bar is selected, and its upper end is machined into a cylindrical combustion chamber with an inner cavity. Its lower end is machined into a nozzle with a converging section, a throat, and a diverging section, so that the Laval nozzle is initially machined into shape. The formed Laval nozzle is subjected to contour scanning and aerodynamic performance testing, and then further precision turning.

9. The industrially mass-producible solid-liquid rocket according to claim 6, characterized in that, The method for processing the startup component is as follows: The cylindrical structure with a closed bottom, stepped inner wall, a central through hole at the bottom, and a wire hole at the bottom is produced by turning brass bars. An annular stress groove is formed by machining the outer wall of the middle part of the starting component.

10. The industrially mass-producible solid-liquid rocket according to claim 6, characterized in that, The method for assembling the rocket is as follows: S1. Hoist the Laval nozzle to the support fixture and fix it vertically, then install and fix the solid propellant charge into the combustion chamber at the upper end of the Laval nozzle. S2. Hoist the oxidizer tank to the top of the Laval nozzle of the supporting fixture, assemble the starting explosive in the starting assembly, and connect the fuse through the wire hole to the starting explosive. Pass the filling pipe through the through hole of the starting explosive and the starting assembly from top to bottom, and make the installation head of the filling pipe abut against the stepped surface of the inner wall of the starting assembly. Place a Teflon gasket on the top of the installation head, and weld the starting assembly containing the starting explosive to the outside of the injector. S3. The oxidant tank is slowly lowered through the lifting mechanism of the supporting fixture, and the injection pipe is lowered vertically along the axis of the central through hole of the propellant column. The oxidant tank is precisely connected to the Laval nozzle and the circumferential weld is performed. S4. Hoist the high-pressure gas cylinder to the top of the upper end cap, connect the high-pressure gas cylinder group to the inlet pipe of the oxidant storage tank with a stainless steel gas guide pipe, connect the solenoid valve, sensor and flow regulating valve in series and complete the sealing test. S5. Install and connect the control system, hoist the load chamber onto the top of the head, and weld it in place; S6. Hoist the load onto the mounting frame inside the load compartment, align it with the separation mechanism interface, tighten the fixing bolts, and install the fairing above the load compartment.

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