Reusable Laval nozzle solid rocket engine

Abstract

The utility model discloses a reusable Laval nozzle solid rocket engine which comprises a shell assembly, a heat insulation outer pipe is fixedly connected to the interior of the shell assembly, a plurality of heat insulation inner pipes are fixedly connected to the interior of the heat insulation outer pipe, propellant filling pipes are fixedly connected to the interiors of the multiple heat insulation inner pipes, and propellant filling pipes are fixedly connected to the interiors of the propellant filling pipes. The reusable solid rocket engine with the Laval nozzle is divided into the shell assembly, the plug assembly, the nozzle assembly and the positioning assembly, propellant ignition program operation is carried out by a worker according to a standard process, at the moment, high-temperature and high-pressure gas generates effective thrust under rectification of the Laval nozzle, and the propellant is ignited through the positioning assembly. The whole system is ensured to be safe and reliable under the fastening of the nozzle fixing ring, after the test is finished, a tester only needs to clean and replace the Laval nozzle, the system experiment can be carried out again, the Laval nozzle does not need to be machined and manufactured again, the test efficiency is improved, and funds needed by the experiment are saved.

Description

Technical Field

[0001] The utility model relates to the technical field of rocket engine experiments, in particular to a reusable Laval nozzle solid rocket engine. Background Art

[0002] In actual engine experiments, staff are required to load the corresponding solid rocket engine propellant and assemble the entire engine in full accordance with engineering requirements. After assembly, the engine is activated to the ready-to-start state, and the actual working efficiency of the engine is calculated by testing the thrust. Currently, common solid rocket engine experimental devices are mainly composed of a Laval nozzle shell and a plug as well as solid propellant, of which the shell is the main pressure-bearing structure, and the Laval nozzle is used to transition the internal high-temperature and high-pressure airflow from the compossonic state to the supersonic state. The above common types of solid rocket engine experimental devices. In actual applications, there are still the following deficiencies:

[0003] The actual assembly of the engine requires manual labor, and the ignition process also requires manual control of the entire process. This makes the engine's working state prone to logical errors and large experimental errors.

[0004] After multiple engine tests, the nozzle was severely ablated, which would cause errors and have a significant impact on the experimental results. Remaking it would be time-consuming and costly, significantly increasing the R&D cycle. Utility Model Content

[0005] The purpose of the present utility model is to provide a reusable Laval nozzle solid rocket engine to solve the problem raised in the above-mentioned background technology that the actual assembly of the engine requires manual assembly by workers, and the entire process needs to be manually controlled during ignition, which makes the working state of the engine prone to logical errors and large experimental errors. After multiple engine experiments, the nozzle is severely ablated, which will cause errors and have a great impact on the experimental results. Re-production consumes time and money, greatly increasing the research and development cycle.

[0006] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a reusable Laval nozzle solid rocket engine, comprising a shell assembly, the interior of the shell assembly is fixedly connected to an insulating outer tube, the interior of the insulating outer tube is fixedly connected to a plurality of insulating inner tubes, the interiors of the plurality of insulating inner tubes are all fixedly connected to propellant filling tubes, one end of the shell assembly is provided with a plug assembly, and the plug assembly is concentric with the propellant filling tube, an insulating gasket is fixedly connected between the plug assembly and the propellant filling tube, the other end of the shell assembly is provided with a nozzle assembly, one end of the nozzle assembly is provided with a positioning assembly, and an insulating ring is fixedly connected between the insulating inner tube and the nozzle assembly.

[0007] Preferably, the shell assembly includes an outer shell, and a plurality of shell positioning threaded holes are opened on both sides of the outer shell surface, and a plurality of full-system positioning holes are opened on the surface of one end of the outer shell, which is conducive to igniting the propellant and withstanding the pressure generated thereby.

[0008] Preferably, the plug assembly includes a plugging head, a surface of one end of the plugging head is provided with a plurality of plugging screw holes, a surface of the plugging head is provided with a plurality of sealing grooves, the interiors of the plurality of sealing grooves are provided with sealing rings, and the interiors of the plurality of plugging screw holes are threadedly connected with plugging screws.

[0009] Preferably, the nozzle assembly includes a Laval nozzle, and a plurality of nozzle sealing grooves are provided on the surface of one end of the Laval nozzle. Sealing rings are provided inside the plurality of nozzle sealing grooves. This is beneficial because after the test is completed, the test personnel only need to clean and replace the Laval nozzle to conduct the system experiment again without reprocessing the Laval nozzle, thereby improving the test efficiency and saving the funds required for the experiment.

[0010] Preferably, the positioning assembly includes a nozzle positioning ring, and a plurality of positioning screw holes are opened on the surface of the nozzle positioning ring. The interiors of the plurality of positioning screw holes are all threadedly connected with positioning screws. The tightening of the nozzle fixing ring is conducive to the safety and reliability of the overall system.

[0011] Preferably, the plug screw hole is concentric with the housing positioning threaded hole, and the plugging head and the outer housing are fixedly connected by the plug screw.

[0012] Preferably, the Laval nozzle and the outer shell are fixedly connected by positioning screws, and the surface of the Laval nozzle is in contact with the inside of the nozzle positioning ring.

[0013] Compared with the existing technology, the beneficial effects of the present invention are: when the staff performs the propellant ignition procedure according to the standard process, the high-temperature and high-pressure gas generates effective thrust under the rectification of the Laval nozzle, and the safety and reliability of the overall system are ensured under the tightening of the nozzle fixing ring. After the test is completed, the test personnel only need to clean and replace the Laval nozzle to conduct the system experiment again, without the need to reprocess the Laval nozzle, thereby improving the test efficiency and saving the funds required for the experiment. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a structural diagram of the Laval nozzle solid rocket engine of the utility model;

[0015] Figure 2 This is a structural diagram of the Laval nozzle solid rocket motor casing assembly of the utility model;

[0016] Figure 3This is a structural diagram of the Laval nozzle solid rocket engine plug assembly of the utility model;

[0017] Figure 4 This is a structural diagram of the nozzle assembly of the Laval nozzle solid rocket engine of the utility model;

[0018] Figure 5 This is a structural diagram of the positioning assembly of the Laval nozzle solid rocket engine of the utility model;

[0019] Figure 6 This is the general assembly diagram of the Laval nozzle solid rocket engine of this utility model.

[0020] In the figure: 1. Insulated outer tube; 2. Shell assembly; 21. Outer shell; 22. Shell positioning threaded hole; 23. Whole system positioning hole; 3. Insulated inner tube; 4. Propellant filling tube; 5. Plug assembly; 51. Sealing head; 52. Plug screw hole; 53. Sealing groove; 54. Sealing ring; 55. Plug screw; 6. Insulated gasket; 7. Nozzle assembly; 71. Laval nozzle; 72. Nozzle sealing groove; 73. Sealing ring; 8. Positioning assembly; 81. Nozzle positioning ring; 82. Positioning screw hole; 83. Positioning screw; 9. Insulation ring. DETAILED DESCRIPTION

[0021] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the accompanying drawings in the embodiments of the present invention.

[0022] See also Figure 1-6 The utility model provides a reusable Laval nozzle solid rocket engine, including a shell assembly 2, an insulating outer tube 1 is fixedly connected to the interior of the shell assembly 2, a plurality of insulating inner tubes 3 are fixedly connected to the interior of the insulating outer tube 1, a propellant filling tube 4 is fixedly connected to the interior of the plurality of insulating inner tubes 3, a plug assembly 5 is provided at one end of the shell assembly 2, and the plug assembly 5 is concentric with the propellant filling tube 4, an insulating gasket 6 is fixedly connected between the plug assembly 5 and the propellant filling tube 4, a nozzle assembly 7 is provided at the other end of the shell assembly 2, a positioning assembly 8 is provided at one end of the nozzle assembly 7, and an insulating ring 9 is fixedly connected between the insulating inner tube 3 and the nozzle assembly 7.

[0023] See Figure 2-5, further, the shell assembly 2 includes an outer shell 21, and a plurality of shell positioning threaded holes 22 are opened on both sides of the surface of the outer shell 21, and a plurality of full-system positioning holes 23 are opened on the surface of one end of the outer shell 21; the plug assembly 5 includes a plugging head 51, and a plurality of plugging screw holes 52 are opened on the surface of one end of the plugging head 51; a plurality of sealing grooves 53 are opened on the surface of the plugging head 51, and a sealing ring 54 is provided inside the plurality of sealing grooves 53; the interiors of the plurality of plugging screw holes 52 are all threadedly connected with plugging screws 55; the nozzle assembly 7 includes a Laval nozzle 71, and a plurality of nozzle sealing grooves 72 are opened on the surface of one end of the Laval nozzle 71, and a sealing ring 73 is provided inside the plurality of nozzle sealing grooves 72; the positioning assembly 8 includes a nozzle positioning ring 81, and a plurality of positioning screw holes 82 are opened on the surface of the nozzle positioning ring 81, and the interiors of the plurality of positioning screw holes 82 are all threadedly connected with positioning screws 83;

[0024] During use, after the preset solid propellant is filled into the interior of the propellant filling tube 4, the designed ignition process is carried out. At this time, the propellant in the propellant filling tube 4 burns violently. Under the protection of the insulated inner tube 3 and the insulated outer tube 1, the outer shell 21 will not be damaged by high temperature. At this time, the outer shell 21 will bear most of the internal gas pressure, and the remaining heat will be borne by the insulating gasket 6 and the insulating ring 9, which play a role in protecting the plugging head 51. When the system is working, the subsonic airflow will be adjusted to a supersonic state by the Laval nozzle 71, which will generate great thrust. At this time, the nozzle positioning ring 81 will limit the Laval nozzle 71 to prevent it from being ejected from the system by high-temperature and high-pressure gas. The main parts that bear shear force in the system are the plug screw 55 and the positioning screw 83, as well as the corresponding plug screw hole 52 and the positioning screw hole 82. After the entire system test is completed, the staff will read the data and clean and reuse the entire components. The entire system is a reusable device, which can reduce the consumption of related consumables.

[0025] When the embodiment of the present application is in use: the plug assembly 5 is fixed to the screw holes at both ends of the outer shell 21 to ensure that the shell of the engine can withstand the high-temperature and high-pressure gas generated by the propellant during the experiment; the propellant filling tube 4 is fixedly arranged inside the thermally insulated inner tube 3 to provide a sticky attachment point for the propellant; the thermally insulating gasket 6 is installed between the propellant filling tube 4 and the plug assembly 5 to isolate the high-temperature gas and prevent the airflow from causing destructive ablation of the plug or sealing components; the Laval nozzle 71 is fixed through the shell positioning threaded hole 22 at the end of the outer shell 21 to ensure the fluid performance and reliability of the experimental system; the nozzle positioning ring 81 is fixed through the shell positioning threaded hole 22 at the end of the outer shell 21 to ensure the fluid performance and reliability of the experimental system; the Laval nozzle 71 is fastened to the outer shell 21 to avoid relative movement and thus ensure the safety and reliability of the test system; the thermal insulation ring 9 is placed between the thermally insulated inner tube 3 and the nozzle assembly 7, and the fastening force generated at both ends prevents the high-temperature airflow from damaging the outer shell 21; the sealing ring 54 and the sealing ring 73 act as sealing devices.

[0026] Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments, or make equivalent substitutions for some of the technical features therein. 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 reusable Laval nozzle solid rocket engine, comprising a housing assembly (2), characterized in that: The shell assembly (2) is fixedly connected to an insulating outer tube (1) inside, and a plurality of insulating inner tubes (3) are fixedly connected inside the insulating outer tube (1), and a propellant filling tube (4) is fixedly connected inside each of the plurality of insulating inner tubes (3). A plug assembly (5) is provided at one end of the shell assembly (2), and the plug assembly (5) is concentric with the propellant filling tube (4). A thermal insulation gasket (6) is fixedly connected between the plug assembly (5) and the propellant filling tube (4). The other end of the shell assembly (2) is provided with a nozzle assembly (7), and one end of the nozzle assembly (7) is provided with a positioning assembly (8). An insulating ring (9) is fixedly connected between the insulating inner tube (3) and the nozzle assembly (7).

2. The reusable Laval nozzle solid rocket engine according to claim 1, characterized in that: The housing assembly (2) comprises an outer housing (21), a plurality of housing positioning threaded holes (22) are provided on both sides of the surface of the outer housing (21), and a plurality of full-system positioning holes (23) are provided on the surface of one end of the outer housing (21).

3. The reusable Laval nozzle solid rocket engine according to claim 1, characterized in that: The plug assembly (5) comprises a plugging head (51), a surface of one end of the plugging head (51) is provided with a plurality of plugging screw holes (52), a surface of the plugging head (51) is provided with a plurality of sealing grooves (53), the interiors of the plurality of sealing grooves (53) are each provided with a sealing ring (54), and the interiors of the plurality of plugging screw holes (52) are each threadedly connected with a plugging screw (55).

4. The reusable Laval nozzle solid rocket engine according to claim 1, characterized in that: The nozzle assembly (7) comprises a Laval nozzle (71), a surface of one end of the Laval nozzle (71) is provided with a plurality of nozzle sealing grooves (72), and a sealing ring (73) is provided inside each of the plurality of nozzle sealing grooves (72).

5. The reusable Laval nozzle solid rocket engine according to claim 1, characterized in that: The positioning assembly (8) comprises a nozzle positioning ring (81), a surface of which is provided with a plurality of positioning screw holes (82), and the interiors of the plurality of positioning screw holes (82) are all threadedly connected with positioning screws (83).

6. The reusable Laval nozzle solid rocket engine according to claim 3, characterized in that: The plug screw hole (52) is concentric with the housing positioning threaded hole (22), and the plug head (51) and the outer housing (21) are fixedly connected via a plug screw (55).

7. The reusable Laval nozzle solid rocket motor according to claim 4, characterized in that: The Laval nozzle (71) and the outer shell (21) are fixedly connected by a positioning screw (83), and the surface of the Laval nozzle (71) is in contact with the inside of the nozzle positioning ring (81).

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