Large-thickness low-cost analog solid rocket engine and forming method

Abstract

The present application relates to the technical field of simulation solid rocket engine, and particularly relates to a large-wall-thickness low-cost simulation solid rocket engine and a forming method, the simulation solid rocket engine comprises a cylinder body, a front skirt and a front head are arranged at the front end of the cylinder body, a rear skirt and a rear head are arranged at the rear end of the cylinder body, a first mounting hole and a second mounting hole are arranged on the cylinder wall of the cylinder body, the front head and the rear head are threadedly connected with the cylinder body through the first mounting hole, the front skirt and the rear skirt are respectively welded with the end faces of the two ends of the cylinder body, a sliding block is arranged on the outer wall of the cylinder body, the sliding block is threadedly connected with the cylinder body through the second mounting hole, and a counterweight nozzle is threadedly connected with the rear head. The present application can quickly design and produce the simulation solid rocket engine when needed, reduce the production cost and shorten the production cycle.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of simulation solid rocket engine, in particular to a large wall thickness low cost simulation solid rocket engine and forming method. BACKGROUND

[0002] In the development process of modern solid rocket engine, the main role of simulation solid rocket engine is to help the development personnel or operators to familiarize and master the performance and use method of the formal product, and improve the reliability and practicality of development.

[0003] Due to the high risk of formal product verification, in order to avoid risks during the research and development stage, some simulation solid rocket engine design and manufacturing will be carried out. The main purpose of designing simulation solid rocket engine during development is to enable ground personnel to master the use of solid rocket engine, rocket test method and test steps as soon as possible, to judge whether the technical parameters of the rocket meet the design requirements according to the test results, so as to further carry out technical iteration.

[0004] The simulation solid rocket engine should consider the authenticity, safety, training and economy of the product in the design process, and achieve the maximum use value with less cost. As a substitute for the real product, the simulation solid rocket engine should be basically the same as the real product in terms of appearance, mass, center of mass, structural layout and geometric size, the connection form between the cabin sections should be consistent with the real rocket, the connection form of the aerodynamic surface and the missile body should be consistent with the real rocket, the mechanical interface and electrical interface of the launching device should be the same as the real product, and the test signal and working time sequence consistent with the real solid rocket engine can be formed. SUMMARY

[0005] The purpose of the present application is to overcome the defects of the prior art, provide a large wall thickness low cost simulation solid rocket engine and forming method, which can quickly design and produce simulation solid rocket engine when needed, reduce production cost and shorten production cycle.

[0006] In order to solve the above technical problems, in the first aspect, the present application provides a large wall thickness low cost simulation solid rocket engine, comprising a cylinder body, a front skirt and a front head are arranged at the front end of the cylinder body, a rear skirt and a rear head are arranged at the rear end of the cylinder body, a first mounting hole and a second mounting hole are arranged on the cylinder wall of the cylinder body, the front head and the rear head are threadedly connected with the cylinder body through the first mounting hole, the front skirt and the rear skirt are respectively welded with the end faces of the two ends of the cylinder body, a sliding block is arranged on the outer wall of the cylinder body, the sliding block is threadedly connected with the cylinder body through the second mounting hole, and a counterweight nozzle is threadedly connected with the rear head.

[0007] Further, a reinforcing block is fixedly arranged on the inner wall of the cylinder body, the sliding block is connected with the cylinder body through a screw, and one end of the screw is threadedly connected with the reinforcing block.

[0008] Further, a centroid block is arranged on the inner wall of the cylinder body, and the centroid block is used for adjusting the centroid of the simulated solid rocket engine.

[0009] Further, the front head and the rear head are connected with the cylinder body through a plurality of weld seams.

[0010] Further, the front head, the rear head, the threaded connection between the sliding block and the cylinder body, and the threaded connection between the rear head and the counterweight nozzle are smeared with thread fastening glue.

[0011] In the second aspect, the application provides a forming method of a large-wall-thickness low-cost simulated solid rocket engine, comprising:

[0012] The front head, the rear head, the sliding block, the cylinder body, the front skirt, the rear skirt and the counterweight nozzle are manufactured in parts;

[0013] The front head and the rear head are threadedly connected with the cylinder wall close to the two ends of the cylinder body respectively, and are partially welded;

[0014] The front skirt and the rear skirt are welded with the end faces of the two ends of the cylinder body respectively;

[0015] The counterweight nozzle is threadedly connected with the rear head;

[0016] The sliding block is threadedly connected with the cylinder wall of the cylinder body.

[0017] Further, the cylinder body is formed by machining a large-wall-thickness steel pipe, so that the mass of the cylinder body is greater than the mass of the cylinder body of an actual solid rocket engine, and the front head, the rear head, the sliding block, the front skirt, the rear skirt and the counterweight nozzle are formed by machining steel materials;

[0018] After the front head, the rear head, the sliding block, the cylinder body, the front skirt, the rear skirt and the counterweight nozzle are assembled, the centroid of the simulated solid rocket engine is calculated, the inner wall of a local part of the cylinder body is machined to reduce the inner diameter of the local part of the cylinder body, the structural centroid is adjusted, and the mass of the simulated solid rocket engine is equal to the mass of the actual solid rocket engine.

[0019] Further, if the centroid of the simulated solid rocket engine cannot meet the requirements after the inner wall of the local part of the cylinder body is machined, a centroid block is welded on the inner wall of the cylinder body according to the centroid requirements of the solid rocket engine.

[0020] Further, the front head and the rear head are integrally machined from steel; the slider is integrally 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 integrally machined from a stainless steel forging.

[0021] Further, the method for threadedly connecting the slider and the cylinder wall comprises welding a reinforcing block on the inner wall of the cylinder at the fixed slider, and threadedly connecting the slider and the cylinder by a screw, one end of which is threadedly connected with the reinforcing block.

[0022] Further, all the threadedly connected parts are smeared with thread fastening glue before assembly.

[0023] The present application has the following beneficial effects:

[0024] 1. The present application has the following beneficial effects:

[0025] 2. The present application has the following beneficial effects:

[0026] 3. The present application has the following beneficial effects:

[0027] 4. The present application has the following beneficial effects:

[0028] 5. The present application has the following beneficial effects: BRIEF DESCRIPTION OF DRAWINGS

[0029] Figure 1 is an axonometric view of the present application.

[0030] Figure 2 is a sectional view of the present application;

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

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

[0033] Figure 5 is a structural schematic view of the slider of the present application;

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

[0035] Figure 7 This is a side view of the rear end cap of the present invention;

[0036] Figure 8 This is a schematic diagram of the structure of the cylinder body, front skirt, and rear skirt after welding according to the present invention;

[0037] Figure 9 This is a side view of the counterweight nozzle of the present invention;

[0038] Figure 10 This 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 end cap 4; rear end cap 5; slider 6; counterweight nozzle 7; reinforcing block 8. Detailed Implementation

[0040] To make the technical problems to be solved, the technical solutions, and the beneficial effects of the present invention clearer, the present invention will be further described in detail below with reference to 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 intended to limit the present invention.

[0041] like Figure 1 , 2 As shown, this invention provides a low-cost simulated solid rocket motor with a large wall thickness, including a cylinder 1. A front skirt 2 and a front end cap 4 are provided at the front end of the cylinder 1, and a rear skirt 3 and a rear end cap 5 are provided at the rear end of the cylinder 1. A first mounting hole 11 and a second mounting hole 12 are formed on the cylinder wall of the cylinder 1. The first mounting hole 11 is arranged near both ends of the cylinder 1, and both the first mounting hole 11 and the second mounting hole 12 are evenly spaced around the outer circumference of the cylinder 1. Figure 3 , 4 As shown in Figures 6 and 7, one end of the front end cap 4 and the rear end cap 5 is radially threaded with a hole corresponding to the first mounting hole 11. The front end cap 4 and the rear end cap 5 are threadedly connected to the cylinder 1 through the first mounting hole 11, that is, one end of the front end cap 4 and the rear end cap 5 extends into the cylinder 1 and is connected to the cylinder 1 by a screw that radially passes through the first mounting hole 11. Figure 8 As shown, the front skirt 2 and the rear skirt 3 are welded to the two end faces of the cylinder 1 respectively, forming a single unit with the cylinder 1. A slider 6 is installed on the outer wall of the cylinder 1, as shown... Figure 5 As shown, the slider 6 has an arc-shaped structure. 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 a screw passing through the second mounting hole 12. Figure 2 , 9As shown, the rear head 5 right end is provided with a counterweight nozzle 7, the left end face of the counterweight nozzle 7 is provided with a threaded hole, and the counterweight nozzle 7 is connected with the rear head 5 through a screw passing through the threaded hole.

[0042] It can be understood that the present application is manufactured by dividing 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, the front head 4 and the rear head 5 are directly connected with the cylinder 1 through threads, the front skirt 2 and the rear skirt 3 are directly welded with the cylinder 1, the slider 6 is directly connected with the cylinder 1 through threads, and the counterweight nozzle 7 is directly connected with the rear head 5 through threads, the connection between the parts is simple and reliable, the design and production of the simulated solid rocket engine can be quickly carried out when needed, the production cost is reduced, and the production cycle is shortened.

[0043] Further, the inner wall of the cylinder 1 is fixedly provided with a reinforcing block 8, the slider 6 is connected with the cylinder 1 through a screw, and one end of the screw is connected with the reinforcing block 8 through threads. By arranging the reinforcing block 8, the connection reliability of the slider 6 and the cylinder 1 is improved.

[0044] Further, a centroid block is arranged on the inner wall of the cylinder 1, and the centroid block is used for adjusting the centroid of the simulated solid rocket engine. By directly welding the centroid block on the inner wall of the cylinder 1, the centroid of the whole structure can be adjusted, so that the centroid position of the simulated solid rocket engine is consistent with the actual position.

[0045] Further, the front head 4 and the rear head 5 are connected with the cylinder 1 through a plurality of weld seams. By partially welding the front head 4 and the rear head 5 with the cylinder 1, screw loosening can be avoided.

[0046] Further, the threaded connection portions of the front head 4, the rear head 5, the slider 6 and the cylinder 1, and the threaded connection portion of the rear head 5 and the counterweight nozzle 7 are smeared with thread locking glue. The thread locking glue can improve the fastening of the threaded connection, and avoid screw loosening.

[0047] The present application provides a forming method of a large-wall-thickness 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 by dividing parts;

[0049] The front head 4 and the rear head 5 are respectively connected with the cylinder wall close to both ends of the cylinder 1 through threads, and are partially welded, that is, four 30° weld seams uniformly distributed in the circumference are arranged for anti-loosening;

[0050] The front skirt 2 and the rear skirt 3 are respectively welded with the end faces of the cylinder 1;

[0051] The counterweight nozzle 7 is connected with the rear head 5 through threads, and 12 M8 screws can be used for connection;

[0052] The sliding block 6 is threadedly connected with the barrel wall of the barrel 1.

[0053] Further, the barrel 1 adopts a large-wall-thickness steel pipe machining forming, so that the mass of the barrel 1 is greater than the mass of the barrel of the actual solid rocket engine, the front head 4, the rear head 5, the sliding block 6, the front skirt 2, the rear skirt 3 and the counterbalance nozzle 7 adopt steel machining forming;

[0054] After the front head 4, the rear head 5, the sliding block 6, the barrel 1, the front skirt 2, the rear skirt 3 and the counterbalance nozzle 7 are assembled, the mass center of the simulated solid rocket engine is calculated, the inner wall of the barrel 1 is machined locally to reduce the inner diameter of the barrel 1, the structural mass center is adjusted, and 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 large-wall-thickness steel pipe to process the barrel 1, the mass of the barrel 1 is greater than the mass of the barrel of the actual solid rocket engine, and by subsequently machining the inner wall of the barrel 1, the mass of the barrel 1 can be reduced, and the mass center of the simulated solid rocket engine can be adjusted, so that the mass and the mass center of the simulated solid rocket engine both meet the requirements.

[0056] Further, if the mass center of the simulated solid rocket engine cannot meet the requirements after the inner wall of the barrel 1 is machined locally, a mass center block is welded on the inner wall of the barrel 1 according to the mass center requirements of the solid rocket engine.

[0057] It can be understood that, as the last optimization measure, the mass center block can ensure that the mass center of the simulated solid rocket engine meets the requirements.

[0058] Further, the front head 4 and the rear head 5 adopt steel integral machining forming, which can adopt 35# steel integral machining forming and is allowed to be segmented and welded into a shape, the specific type of the steel is not limited, and low-cost structural steel is preferably adopted; the sliding block 6 adopts stainless steel forging machining forming; the barrel 1 adopts steel pipe integral machining forming; the front skirt 2 and the rear skirt 3 adopt steel bar machining forming; and the counterbalance nozzle 7 adopts stainless steel forging machining forming, and the counterbalance nozzle 7 can also adopt 35# steel to reduce the cost.

[0059] Further, the method for threadedly connecting the sliding block 6 with the barrel wall of the barrel 1 includes welding a reinforcing block 8 on the inner wall of the barrel 1 at the fixed position of the sliding block 6, threadedly connecting the sliding block 6 with the barrel 1 by using a screw, and threadedly connecting one end of the screw with the reinforcing block 8. Ten M12*50 screws can be adopted to connect the screw with the reinforcing block 8.

[0060] Further, all the threadedly connected parts are coated with thread fastening glue before assembly.

[0061] The above-described embodiments are only used to illustrate the technical solutions of the present application, and are not intended to limit the present application; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: it can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application, and should be included in the protection scope of the present application.

Claims

1. A method of forming a large wall thickness low cost simulated solid rocket engine, characterized by, The application relates to a simulation solid rocket engine. The front end cover (4), the rear end cover (5), the slider (6), the cylinder body (1), the front skirt (2), the rear skirt (3) and the counterweight nozzle (7) are manufactured in parts; The front end cover (4) and the rear end cover (5) are respectively threadedly connected with the cylinder wall of the cylinder body (1) near two ends and are partially welded; The front skirt (2) and the rear skirt (3) are respectively welded with the end faces of the two ends of the cylinder body (1); The counterweight nozzle (7) is threadedly connected with the rear end cover (5); The slider (6) is threadedly connected with the cylinder wall of the cylinder body (1); The cylinder body (1) is formed by machining a large-wall-thickness steel pipe, so that the mass of the cylinder body (1) is greater than that of the actual solid rocket engine; the front end cover (4), the rear end cover (5), the slider (6), the front skirt (2), the rear skirt (3) and the counterweight nozzle (7) are formed by machining steel pipes; After the front end cover (4), the rear end cover (5), the slider (6), the cylinder body (1), the front skirt (2), the rear skirt (3) and the counterweight nozzle (7) are assembled, the mass center of the simulation solid rocket engine is calculated and simulated; the inner wall of the cylinder body (1) is machined to reduce the mass of the cylinder body (1), the mass center of the simulation solid rocket engine is adjusted, and the mass of the simulation solid rocket engine is equal to that of the actual solid rocket engine.

2. The method of claim 1, wherein, If the mass center of the simulation solid rocket engine cannot meet the requirement after the inner wall of the cylinder body (1) is machined, a mass center block is welded on the inner wall of the cylinder body (1) according to the mass center requirement of the actual solid rocket engine. The threadedly connecting of the slider (6) with the cylinder wall of the cylinder body (1) comprises the following steps: welding a reinforcing block (8) on the inner wall of the cylinder body (1) where the slider (6) is fixed, and threadedly connecting the slider (6) with the cylinder body (1) by means of a screw, one end of the screw being threadedly connected with the reinforcing block (8).

3. The method of claim 1 or 2, wherein All the threadedly connecting is performed by applying thread fastening glue before assembly.

4. The forming method of a large-thickness low-cost simulated solid rocket engine according to claim 1 or 2, characterized in that, The application relates to a simulation solid rocket engine.

5. A large-thickness low-cost simulated solid rocket engine manufactured by the molding method of the large-thickness low-cost simulated solid rocket engine according to any one of claims 1 to 4, characterized by The application relates to a simulation solid rocket engine.

6. The low cost simulated solid rocket engine of thick walled construction of claim 5 wherein, The application relates to a simulation solid rocket engine.

7. The low cost simulated solid rocket engine of claim 5, wherein, The application relates to a simulation solid rocket engine.

8. A low cost simulated solid rocket engine of large wall thickness according to any one of claims 5 to 7, characterized in that, The application relates to a simulation solid rocket engine. The application relates to a simulation solid rocket engine. The application relates to a simulation solid rocket engine.

9. A low cost simulated solid rocket engine of thick-walled construction according to any one of claims 5 to 7, characterised in that, The front head (4), the rear head (5), the sliding block (6) and the threaded connection of the cylinder (1), and the threaded connection of the rear head (5) and the counterweight nozzle (7) are all coated with thread fastening glue.

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