Large-wall-thickness low-cost simulated solid rocket engine and forming method

Abstract

The invention relates to the technical field of simulated solid rocket engines, in particular to a large-wall-thickness low-cost simulated solid rocket engine and a forming method.The simulated solid rocket engine comprises a barrel, a front skirt and a front sealing head are arranged at the front end of the barrel, and a rear skirt and a rear sealing head are arranged at the rear end of the barrel; a first mounting hole and a second mounting hole are formed in the cylinder wall of the cylinder body, the front sealing head and the rear sealing head are in threaded connection with the cylinder body through the first mounting hole, the front skirt and the rear skirt are welded to the end faces of the two ends of the cylinder body respectively, a sliding block is arranged on the outer wall of the cylinder body, and the sliding block is in threaded connection with the cylinder body through the second mounting hole. And the rear sealing head is in threaded connection with a counterweight spray pipe. According to the method, the design, production and manufacturing of the simulated solid rocket engine can be rapidly carried out according to the method when development needs, the production cost is reduced, and the production period is shortened.

Description

Technical Field

[0001] The invention relates to the technical field of simulated solid rocket engines, and in particular to a large-wall-thickness, low-cost simulated solid rocket engine and a molding method thereof. Background Art

[0002] In the development process of modern solid rocket engines, the main purpose of simulating solid rocket engines is to help developers or operators become familiar with and master the performance and usage of their formal products, and to improve the reliability and practicality of development.

[0003] Since formal product verification is very dangerous, in order to avoid risks during the scientific research and development stage, some simulated solid rocket engines will be designed and manufactured. The main purpose of designing simulated solid rocket engines during the development period is to enable ground crews to quickly master the use of solid rocket engines, rocket testing methods and test steps, and to determine whether the rocket's technical parameters meet the design requirements based on the test results, so as to further carry out technical iterations.

[0004] The design process of simulated solid rocket engines should consider the authenticity, safety, training and economy of the product, so as to achieve the maximum use value at a relatively low cost. As a substitute for the real product, the simulated solid rocket engine should be basically the same as the real product in terms of physical parameters such as appearance, mass, center of mass, structural layout and geometric dimensions. The connection form between the compartments should be consistent with that of the real rocket, the connection form between the aerodynamic surface and the body should be consistent with that of the real rocket, and the mechanical and electrical interfaces of the launch device should be the same as those of the real product, so as to be able to generate test signals and working sequences consistent with those of the real solid rocket engine. Summary of the invention

[0005] The purpose of the present invention is to address the defects of the prior art and provide a large-walled, low-cost simulated solid rocket engine and a molding method, which can be used as a reference to quickly design and produce simulated solid rocket engines when needed, thereby reducing production costs and shortening production cycles.

[0006] In order to solve the above technical problems, in the first aspect, the present invention provides a large-wall-thickness, low-cost simulated solid rocket engine, including a cylinder, a front skirt and a front head are arranged at the front end of the cylinder, a rear skirt and a rear head are arranged at the rear end of the cylinder, a first mounting hole and a second mounting hole are opened on the cylinder wall of the cylinder, the front head and the rear head are threadedly connected to the cylinder through the first mounting hole, the front skirt and the rear skirt are respectively welded to the two end faces of the cylinder, a slider is arranged on the outer wall of the cylinder, the slider is threadedly connected to the cylinder through the second mounting hole, and a counterweight nozzle is threadedly connected to the rear head.

[0007] Furthermore, a reinforcement block is fixedly arranged on the inner wall of the cylinder, the sliding block is connected to the cylinder via a screw, and one end of the screw is threadedly connected to the reinforcement block.

[0008] Furthermore, a center of mass block is arranged on the inner wall of the cylinder, and the center of mass block is used to adjust the center of mass of the simulated solid rocket engine.

[0009] Furthermore, the front head and the rear head are connected to the cylinder body through a plurality of welds.

[0010] Furthermore, thread fastening glue is applied to the threaded connections between the front head, the rear head, the slider and the cylinder, and the threaded connection between the rear head and the counterweight nozzle.

[0011] In a second aspect, the present invention provides a method for forming a large-wall-thick, low-cost simulated solid rocket engine, comprising:

[0012] The front head, rear head, slider, cylinder, front skirt, rear skirt and counterweight nozzle are manufactured in parts;

[0013] The front head and the rear head are respectively connected to the cylinder wall near the two ends of the cylinder by threads, and partially welded;

[0014] Weld the front skirt and the rear skirt to the two end faces of the cylinder respectively;

[0015] Connect the weighted nozzle to the rear head threadedly;

[0016] The slider is threadedly connected to the cylinder wall of the cylinder.

[0017] Furthermore, the barrel is machined from a thick steel pipe, so that the mass of the barrel is greater than the mass of the barrel of an actual solid rocket engine, and the front head, rear head, slider, front skirt, rear skirt, and counterweight nozzle are machined from steel;

[0018] After the front head, rear head, slider, barrel, front skirt, rear skirt, and counterweight nozzle are assembled, the center of mass of the simulated solid rocket engine is calculated, and the center of mass of the structure is adjusted by machining the local inner wall of the barrel to reduce the local inner diameter of the barrel, so that the mass of the simulated solid rocket engine is equal to the mass of the actual solid rocket engine.

[0019] Furthermore, it includes: if the center of mass of the simulated solid rocket engine cannot meet the requirements after machining the local inner wall of the cylinder, a center of mass block is welded on the inner wall of the cylinder according to the center of mass requirements of the solid rocket engine.

[0020] Furthermore, the front head and the rear head are integrally machined from steel; the slider is machined from a stainless steel forging; the cylinder is integrally machined from a steel pipe; the front skirt and the rear skirt are machined from a steel bar; and the counterweight nozzle is machined from a stainless steel forging.

[0021] Furthermore, the method of threading the slider to the cylinder wall includes: welding a reinforcement block to the inner wall of the cylinder where the slider is fixed, threading the slider to the cylinder with a screw, and threading one end of the screw to the reinforcement block.

[0022] Furthermore, all threaded connections are coated with thread locking glue before assembly.

[0023] The beneficial effects of the present invention are:

[0024] 1. The present invention manufactures the front head, the rear head, the slider, the barrel, the front skirt, the rear skirt and the counterweight nozzle in parts. The front head and the rear head are directly threadedly connected to the barrel, the front skirt and the rear skirt are directly welded to the barrel, the slider is directly threadedly connected to the barrel, and the counterweight nozzle is directly threadedly connected to the rear head. The connection between the parts is simple and reliable. The method can be referred to when research and development is needed to quickly design and manufacture simulated solid rocket engines, reduce production costs, and shorten production cycles.

[0025] 2. The present invention is beneficial to improving the connection reliability between the slider and the cylinder by providing a reinforcement block.

[0026] 3. The present invention welds the front head and the rear head to the cylinder part, which can prevent the screws from loosening.

[0027] 4. The present invention can improve the fastening of threaded connections and prevent screws from loosening by applying thread fastening glue to all threaded connections.

[0028] 5. The present invention can adjust the center of mass of the entire structure by directly welding the center of mass block on the inner wall of the cylinder, so that the center of mass position of the simulated solid rocket engine is consistent with the actual one. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is an axonometric drawing of the present invention.

[0030] Figure 2 is a cross-sectional view of the present invention;

[0031] Figure 3 This is a front view of the front head of the present invention;

[0032] Figure 4 It is a side view of the front head of the present invention;

[0033] Figure 5 It is a structural schematic diagram of the slider of the present invention;

[0034] Figure 6 This is a front view of the rear end cover of the present invention;

[0035] Figure 7 It is a side view of the rear head of the present invention;

[0036] Figure 8 It is a schematic diagram of the structure after the cylinder body, the front skirt and the rear skirt are welded;

[0037] Fig. 9 It is a side view of the counterweight nozzle of the present invention;

[0038] Fig.10 It is a schematic diagram of the installation of the slider of the present invention.

[0039] Reference numerals: cylinder 1; first mounting hole 11; second mounting hole 12; front skirt 2; rear skirt 3; front head 4; rear head 5; slider 6; counterweight nozzle 7; reinforcement block 8. DETAILED DESCRIPTION

[0040] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0041] like Figure 1 , 2 As shown, the present invention provides a large-wall-thickness, low-cost simulated solid rocket engine, comprising a barrel 1, a front skirt 2 and a front head 4 are arranged at the front end of the barrel 1, a rear skirt 3 and a rear head 5 are arranged at the rear end of the barrel 1, a first mounting hole 11 and a second mounting hole 12 are opened on the barrel wall of the barrel 1, the first mounting hole 11 is arranged near the two ends of the barrel 1, and the first mounting hole 11 and the second mounting hole 12 are evenly spaced around the outer circumference of the barrel 1, as shown in FIG. Figure 3 , 4 As shown in FIGS. 6 and 7 , one end of the front head 4 and the rear head 5 are radially provided with threaded holes corresponding to the first mounting holes 11, and the front head 4 and the rear head 5 are threadedly connected to the cylinder 1 through the first mounting holes 11, that is, one end of the front head 4 and the rear head 5 extends into the cylinder 1 and is connected to the cylinder 1 by screws radially passing through the first mounting holes 11, as shown in FIGS. Figure 8 As shown, the front skirt 2 and the rear skirt 3 are respectively welded to the end faces of the cylinder 1 at both ends and connected to the cylinder 1 as a whole. A slider 6 is arranged on the outer wall of the cylinder 1. Figure 5 As shown, the slider 6 is in an arc-shaped structure, and the slider 6 is threadedly connected to the cylinder 1 through the second mounting hole 12, that is, the slider 6 is fixed to the outer wall of the cylinder 1 by screws passing through the second mounting hole 12, as shown in FIG. Figure 2 , 9As shown, a counterweight nozzle 7 is provided at the right end of the rear head 5, a threaded hole is provided at the left end face of the counterweight nozzle 7, and the counterweight nozzle 7 is connected to the rear head 5 by means of screws passing through the threaded hole.

[0042] It can be understood that the present invention manufactures the front head 4, the rear head 5, the slider 6, the barrel 1, the front skirt 2, the rear skirt 3, and the counterweight nozzle 7 in parts. The front head 4 and the rear head 5 are directly threadedly connected to the barrel 1, the front skirt 2 and the rear skirt 3 are directly welded to the barrel 1, the slider 6 is directly threadedly connected to the barrel 1, and the counterweight nozzle 7 is directly threadedly connected to the rear head 5. The connection between the various parts is simple and reliable. When research and development needs, the method can be used as a reference to quickly simulate the design and production of solid rocket engines, thereby reducing production costs and shortening production cycles.

[0043] Further, a reinforcing block 8 is fixedly arranged on the inner wall of the cylinder 1, and the slider 6 is connected to the cylinder 1 by a screw, and one end of the screw is threadedly connected to the reinforcing block 8. The reinforcing block 8 is arranged to help improve the connection reliability between the slider 6 and the cylinder 1.

[0044] Furthermore, a mass center block is provided on the inner wall of the cylinder 1, and the mass center block is used to adjust the mass center of the simulated solid rocket engine. By directly welding the mass center block on the inner wall of the cylinder 1, the mass center of the entire structure can be adjusted so that the mass center position of the simulated solid rocket engine is consistent with the actual one.

[0045] Furthermore, the front head 4 and the rear head 5 are connected to the cylinder 1 by a plurality of welds. The front head 4 and the rear head 5 are partially welded to the cylinder 1 to prevent the screws from loosening.

[0046] Furthermore, thread fastening glue is applied to the threaded connections between the front head 4, the rear head 5, the slider 6 and the cylinder 1, and the threaded connection between the rear head 5 and the counterweight nozzle 7. The thread fastening glue can improve the tightness of the threaded connection and prevent the screws from loosening.

[0047] The present invention provides a molding method for a large-wall-thick and low-cost simulated solid rocket engine, comprising:

[0048] The front head 4, the rear head 5, the slider 6, the cylinder 1, the front skirt 2, the rear skirt 3, and the counterweight nozzle 7 are manufactured in parts;

[0049] The front head 4 and the rear head 5 are respectively connected to the cylinder wall near the two ends of the cylinder 1 by threads, and partially welded, that is, four 30° welds evenly distributed around the circumference are set to prevent loosening;

[0050] Weld the front skirt 2 and the rear skirt 3 to the end faces of the cylinder 1 respectively;

[0051] The counterweight nozzle 7 is threadedly connected to the rear head 5, and 12 M8 screws may be used for connection;

[0052] The slide block 6 is threadedly connected to the cylinder wall of the cylinder body 1.

[0053] Furthermore, the barrel 1 is machined from a thick steel pipe, so that the mass of the barrel 1 is greater than the mass of the barrel of an actual solid rocket engine, and the front head 4, the rear head 5, the slider 6, the front skirt 2, the rear skirt 3, and the counterweight nozzle 7 are machined from steel;

[0054] After the front head 4, the rear head 5, the slider 6, the barrel 1, the front skirt 2, the rear skirt 3, and the counterweight nozzle 7 are assembled, the center of mass of the simulated solid rocket engine is calculated, and the inner diameter of the local part of the barrel 1 is reduced by machining the inner wall of the barrel 1, and the center of mass of the structure is adjusted, so that the mass of the simulated solid rocket engine is equal to the mass of the actual solid rocket engine.

[0055] It can be understood that by using a thick-walled steel pipe to process the cylinder 1, the mass of the cylinder 1 is made greater than the mass of the cylinder of an actual solid rocket engine. By subsequently machining the inner wall of the cylinder 1, the mass of the cylinder 1 can be reduced, and at the same time, the center of mass of the simulated solid rocket engine can be adjusted so that both the mass and center of mass of the simulated solid rocket engine meet the requirements.

[0056] Furthermore, it includes: if the center of mass of the simulated solid rocket engine cannot meet the requirements after machining the local inner wall of the cylinder 1, a center of mass block is welded on the inner wall of the cylinder 1 according to the center of mass requirements of the solid rocket engine.

[0057] It can be understood that the center of mass block is used as the final optimization measure to ensure that the center of mass of the simulated solid rocket motor meets the requirements.

[0058] Furthermore, the front head 4 and the rear head 5 are integrally machined from steel, and 35# steel can be integrally machined. Segmental welding is allowed, and the specific type of steel is not limited. Low-cost structural steel is used as much as possible; the slider 6 is machined from stainless steel forgings; the cylinder 1 is integrally machined from a steel pipe; the front skirt 2 and the rear skirt 3 are machined from steel bars; the counterweight nozzle 7 is machined from stainless steel forgings, and 35# steel can also be used for the counterweight nozzle 7 to reduce costs.

[0059] Furthermore, the method of threading the slider 6 to the cylinder wall of the cylinder 1 includes: welding a reinforcing block 8 to the inner wall of the cylinder 1 where the slider 6 is fixed, threading the slider 6 to the cylinder 1 with a screw, and threading one end of the screw to the reinforcing block 8. Ten M12×50 screws can be used to ensure that the screws are connected to the reinforcing block 8.

[0060] Furthermore, all threaded connections are coated with thread locking glue before assembly.

[0061] The embodiments described above are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. Such modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention, and should all be included in the protection scope of the present invention.

Claims

1. A method for forming a thick-walled, low-cost simulated solid rocket engine, characterized in that: include: The front head (4), the rear head (5), the slider (6), the cylinder (1), the front skirt (2), the rear skirt (3), and the counterweight nozzle (7) are manufactured in parts; The front end cap (4) and the rear end cap (5) are respectively connected to the cylinder wall near the two ends of the cylinder body (1) by threaded connection, and partially welded; The front skirt (2) and the rear skirt (3) are respectively welded to the end faces of both ends of the cylinder (1); The counterweight nozzle (7) is threadably connected to the rear end cover (5); The slider (6) is threadably connected to the wall of the cylinder (1).

2. The molding method of a large-wall-thick, low-cost simulated solid rocket engine according to claim 1, characterized in that: The barrel (1) is machined from a thick steel pipe, so that the mass of the barrel (1) is greater than the mass of the barrel of an actual solid rocket engine. The front head (4), the rear head (5), the slider (6), the front skirt (2), the rear skirt (3), and the counterweight nozzle (7) are machined from steel. After the front head (4), the rear head (5), the slider (6), the barrel (1), the front skirt (2), the rear skirt (3), and the counterweight nozzle (7) are assembled, the center of mass of the simulated solid rocket engine is calculated, and the inner diameter of the local part of the barrel (1) is reduced by machining the inner wall of the barrel (1), so as to adjust the center of mass of the structure and make the mass of the simulated solid rocket engine equal to the mass of the actual solid rocket engine.

3. The molding method of a large-wall-thick, low-cost simulated solid rocket engine according to claim 2, characterized in that: include: If the center of mass of the simulated solid rocket engine cannot meet the requirements after machining the local inner wall of the cylinder (1), a center of mass block is welded on the inner wall of the cylinder (1) according to the center of mass requirements of the actual solid rocket engine.

4. The molding method of a large-wall-thickness, low-cost simulated solid rocket engine according to any one of claims 1 to 3, characterized in that: The method for threading a slider (6) to the wall of a cylinder (1) comprises: welding a reinforcing block (8) to the inner wall of the cylinder (1) where the slider (6) is fixed, threading the slider (6) to the cylinder (1) using a screw, and threading one end of the screw to the reinforcing block (8).

5. The molding method of a large-wall-thickness, low-cost simulated solid rocket engine according to any one of claims 1 to 3, characterized in that: All threaded connections should be coated with thread locking glue before assembly.

6. A method for forming a large-walled, low-cost simulated solid rocket engine according to any one of claims 1 to 5, characterized in that: The invention comprises a cylinder (1), wherein a front skirt (2) and a front end cap (4) are arranged at the front end of the cylinder (1), and a rear skirt (3) and a rear end cap (5) are arranged at the rear end of the cylinder (1); a first mounting hole (11) and a second mounting hole (12) are provided on the cylinder wall of the cylinder (1); the front end cap (4) and the rear end cap (5) are threadedly connected to the cylinder (1) through the first mounting hole (11); the front skirt (2) and the rear skirt (3) are respectively welded to the end faces of both ends of the cylinder (1); a slider (6) is arranged on the outer wall of the cylinder (1); the slider (6) is threadedly connected to the cylinder (1) through the second mounting hole (12); and a counterweight nozzle (7) is threadedly connected to the rear end cap (5).

7. The thick-walled, low-cost simulated solid rocket engine according to claim 6, characterized in that: A reinforcing block (8) is fixedly arranged on the inner wall of the cylinder (1), and the sliding block (6) is connected to the cylinder (1) via a screw, one end of the screw being threadedly connected to the reinforcing block (8).

8. The thick-walled, low-cost simulated solid rocket engine according to claim 6, characterized in that: A center of mass block is arranged on the inner wall of the cylinder (1), and the center of mass block is used to adjust the center of mass of the simulated solid rocket engine.

9. The thick-walled, low-cost simulated solid rocket engine according to any one of claims 6 to 8, characterized in that: The front head (4) and the rear head (5) are connected to the cylinder (1) via a plurality of welds.

10. The thick-walled, low-cost simulated solid rocket engine according to any one of claims 6 to 8, characterized in that: The threaded connections between the front head (4), the rear head (5), the slider (6) and the cylinder (1), as well as the threaded connection between the rear head (5) and the counterweight nozzle (7) are all coated with thread fastening glue.

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