Reusable solid rocket engine fast pressure relief and flameout device and method

Abstract

This invention relates to the field of solid rocket motor technology, and discloses a reusable solid rocket motor rapid depressurization and shutdown device and method. This device enables rapid depressurization and shutdown of a solid rocket motor without structural damage during the depressurization process. Through the movement between the outer shell and the moving body, and the annular cavity formed between them, filled with fluid, the movement of the moving body within the outer shell is controlled by the fluid, thereby achieving rapid depressurization and shutdown of the solid rocket motor. After depressurization and shutdown, the device can be reset by filling or removing fluid from the annular cavity through fluid passages, without affecting the restart of the engine after shutdown. Therefore, multiple repetitive rapid depressurization, shutdown, and restart of the solid rocket motor are possible. The use of several circumferentially arranged exhaust holes increases the additional gas flow area, resulting in a high combustion chamber depressurization rate and enabling rapid depressurization of the combustion chamber.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of solid rocket engine, in particular to a reusable solid rocket engine rapid pressure relief and flameout device and method. BACKGROUND

[0002] In the working process of solid rocket engine, rapid pressure relief is the main technical approach to realize engine flameout and thrust termination. In order to realize the rapid pressure relief and flameout of solid rocket engine, there are two main methods at present. One is to use energy cutting and other means to make the local structure of the combustion chamber instantaneously destroyed, forming an additional rapid opening gas release channel, at this time the pressure in the combustion chamber rapidly decreases, thereby destroying the stable combustion condition of the solid propellant in the combustion chamber, achieving the purpose of engine flameout and thrust termination. The other method is to install a high-pressure gas valve on the engine, and make the combustion chamber pressure rapidly decrease by controlling the opening of the valve, resulting in engine flameout. In the above methods, the combustion chamber of the engine will inevitably be damaged while achieving rapid pressure relief in the former method, so it can only realize one-time flameout of the engine, and the engine cannot be restarted after flameout. In the latter method, the structure of the high-pressure gas valve is complex, large in size and heavy in weight due to the requirement of the valve having a large enough diameter area to make the engine rapidly release pressure, so it is only limited to application in some experimental devices and is difficult to apply in actual solid rocket engines. SUMMARY

[0003] In order to overcome the defects of the prior art, the purpose of the present application is to provide a reusable solid rocket engine rapid pressure relief and flameout device and method, so as to solve the technical problems that the combustion chamber of the engine is easily damaged during pressure relief in the prior art, and can only realize one-time flameout, and the structure of the rapid pressure relief device is complex and difficult to apply.

[0004] The present application is achieved by the following technical solutions:

[0005] A reusable solid rocket engine rapid pressure relief and flameout device, comprising an outer shell and a moving body; the outer shell is a cylindrical cavity body with two open ends; one end is a large opening end, the end face of the large opening end is sealingly connected at the engine combustion chamber shell, the other end is a small opening end, and the small opening end is communicated with the nozzle; the moving body is a cylindrical cavity body with two open ends, the moving body is coaxially sleeved in the outer shell, and an annular cavity is formed between the moving body and the small opening end of the outer shell, the annular cavity is filled with fluid, a plurality of fluid through holes are arranged on the small opening end in the axial direction, the fluid through holes are communicated with the annular cavity, and are used for pumping away or filling the fluid in the annular cavity; the moving body moves axially along the large opening end and the small opening end by pumping away or filling the fluid in the annular cavity, and a plurality of exhaust holes are arranged on the side wall of the large opening end in the circumferential direction, when the moving body moves close to the small opening end, the gas flow of the engine combustion chamber flows to the plurality of exhaust holes.

[0006] Preferably, the small opening end has a smaller caliber than the large opening end, and the inner wall of the small opening end is stepped with the inner wall of the large opening end, and the annular cavity is formed between the small opening end and the outer shell.

[0007] Preferably, a plurality of guide pins are arranged between the small opening end and the moving body, and a plurality of guide pin fixing holes parallel to the axis are arranged on the small opening end, and a guide hole is arranged on the moving body corresponding to the guide pin fixing hole, and one end of the guide pin extends into the guide pin fixing hole and the other end extends into the guide hole.

[0008] Preferably, a plurality of first sealing grooves are arranged on the inner wall surface of the small opening end along the circumference; and a plurality of housing sealing rings are correspondingly arranged in the first sealing grooves, and the housing sealing rings are distributed between the housing sealing rings and the outer wall surface of the moving body.

[0009] Preferably, a boss is arranged on the moving body, and the boss is in contact with the sidewall of the large opening end, and one side of the boss is sealingly connected to the engine combustion chamber housing, and the other side of the boss forms an annular cavity with the small opening end, and the top of the boss is in contact with a plurality of exhaust holes.

[0010] Further, a plurality of second sealing grooves are arranged on the top surface of the boss along the circumference, and a plurality of moving body sealing rings are arranged in the second sealing grooves, and the moving body sealing rings are located between the sidewall of the large opening end and the boss.

[0011] Further, the length of the inside of the large opening end is greater than the length of the boss.

[0012] Further, the length of the boss is greater than the caliber of the exhaust hole.

[0013] Preferably, an insulating layer is attached to the inner wall of the moving body, and the insulating layer is made of rubber or high-silicon phenolic resin composite material.

[0014] A reusable solid rocket engine rapid pressure relief and extinguishing method based on the above-mentioned reusable solid rocket engine rapid pressure relief and extinguishing device, comprising the following steps:

[0015] In the normal working state of the solid engine, the quick pressure relief and extinguishing device is in the closed state, the moving body moves close to the combustion chamber side, and the gap between the boss of the moving body and the small opening end of the outer shell forms a closed annular cavity, at this time, the annular cavity is filled with high-pressure fluid medium, and the annular cavity limits the movement of the moving body under the action of the high-pressure fluid; when the solid rocket engine needs to be quickly pressure relieved and extinguished, the quick pressure relief and extinguishing device is opened, the fluid in the annular cavity flows out through the fluid through hole of the outer shell, under the action of the internal pressure of the combustion chamber gas, the moving body quickly moves to the small opening end, at this time, the gas can be discharged through the exhaust hole, and due to the large flow area of the exhaust hole, the pressure in the combustion chamber of the engine is rapidly reduced, so that the engine is extinguished; after the solid rocket engine is extinguished, the high-pressure fluid reenters the annular cavity through the driving fluid through hole, and under the action of the driving fluid pressure, the moving body moves to the large opening end side, and the quick pressure relief and extinguishing device is in the closed state again, at this time, the engine can be ignited and started again.

[0016] Compared with the prior art, the present application has the following beneficial technical effects:

[0017] The present application provides a reusable solid rocket engine quick pressure relief and extinguishing device, which can realize the quick pressure relief and extinguishing of the solid rocket engine, and the structure is not damaged during the pressure relief process. Through the movement cooperation between the outer shell and the moving body, and the annular cavity formed between the outer shell and the moving body, the annular cavity is filled with fluid, and the movement of the moving body in the outer shell is realized by controlling the fluid, so as to realize the quick pressure relief and extinguishing of the solid rocket engine. After the pressure relief and extinguishing are completed, the device can be reset by filling or removing the fluid in the annular cavity through the fluid through hole, without affecting the restart of the engine after extinguishing. Therefore, the quick pressure relief and extinguishing and restart of the solid rocket engine can be repeated multiple times. By arranging a plurality of exhaust holes in the circumferential direction, the additional gas flow area is greatly increased, the pressure reduction rate of the combustion chamber is high, and the quick pressure relief of the combustion chamber can be realized.

[0018] Further, the diameter of the small opening end is smaller than that of the large opening end, the inner walls of the small opening end and the large opening end are stepped, and the annular cavity is formed between the moving body and the small opening end in the outer shell. It is convenient to form an annular cavity between the small opening end and the moving body, and it is convenient to realize the displacement between the outer shell and the moving body by controlling the fluid in the annular cavity, so as to realize the quick pressure relief and extinguishing and restart of the solid rocket engine multiple times.

[0019] Further, a plurality of guide pins are arranged between the small opening end and the moving body, a plurality of guide pin fixing holes parallel to the axis are arranged at the small opening end, and guide holes corresponding to the guide pin fixing holes are arranged on the moving body. One end of the guide pin extends into the guide pin fixing hole, and the other end extends into the guide hole, so as to facilitate the horizontal movement between the moving body and the small opening end.

[0020] Further, the inner wall surface of the small opening end is provided with a plurality of first sealing grooves along the circumference; a plurality of housing sealing rings are correspondingly sleeved in the first sealing grooves, and the housing sealing rings are distributed between the housing sealing rings and the outer wall surface of the moving body, so that the sealing property between the outer housing and the moving body is improved, and gas leakage is avoided.

[0021] Further, the moving body is provided with a boss, the boss is in contact with the sidewall of the large opening end, one side of the boss is sealingly connected to the engine combustion chamber housing, the other side of the boss forms an annular cavity with the small opening end, the top of the boss is in contact with the plurality of exhaust holes, and the boss is moved at the large opening end to control the opening and closing of the plurality of exhaust holes, so that the solid rocket engine can be repeatedly and quickly depressurized and extinguished and restarted.

[0022] Further, the inner wall of the moving body is attached with a heat insulation layer to reduce the heat transfer of high-temperature gas to the moving body 2.

[0023] The application also provides a reusable solid rocket engine rapid depressurization and extinguishing method, which uses a small amount of high-pressure fluid and combustion chamber high-pressure gas as the driving source for opening and closing the device, has fast response control, simple driving control, high working reliability, uses the circumferentially arranged exhaust holes to greatly increase the additional gas flow area, makes the combustion chamber have a high depressurization rate, and can realize rapid depressurization of the combustion chamber. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 FIG. 1 is a structural schematic view of a reusable solid rocket engine rapid depressurization and extinguishing device in the application;

[0025] Figure 2 FIG. 2 is a schematic view of the A direction of FIG. 1; Figure 1

[0026] Figure 3 FIG. 3 is a structural schematic view of an outer housing in the application;

[0027] Figure 4 FIG. 4 is a structural schematic view of a moving body in the application;

[0028] Figure 5 FIG. 5 is a schematic view of the opening state of a rapid depressurization device in the application.

[0029] In the figure: 1 is an outer housing, 11 is an exhaust hole, 12 is a fluid through hole, 13 is a first sealing groove, 14 is a guide pin fixing hole; 2 is a moving body, 21 is a guide hole, 22 is a second sealing groove, 23 is a boss, 3 is a guide pin, 4 is a heat insulation layer, 5 is an annular cavity, 6 is a moving body sealing ring, and 7 is a housing sealing ring. DETAILED DESCRIPTION

[0030] ​To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. 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 should fall within the scope of protection of the present invention.

[0031] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0032] The present invention will now be described in further detail with reference to the accompanying drawings:

[0033] The purpose of this invention is to provide a reusable solid rocket engine rapid depressurization and shutdown device and method to solve the technical problems in the prior art where the engine combustion chamber is easily damaged during engine depressurization, and the rapid depressurization device can only achieve one-time shutdown and has a complex structure that is difficult to apply.

[0034] Specifically, the reusable solid rocket engine rapid depressurization and shutdown device is installed between the engine's combustion chamber and nozzle. It features a simple and compact structure and can achieve multiple rapid depressurization and reset, meeting the requirements for multiple shutdowns and repeated restarts of the solid rocket engine.

[0035] according to Figures 1 to 4 As shown, the reusable solid rocket motor rapid depressurization and shutdown device includes an outer shell 1, a moving body 2, a guide pin 3, an insulation layer 4, a moving body sealing ring 6, and an outer shell sealing ring 7.

[0036] The outer casing 1 is a cylindrical cavity with openings at both ends, divided into a large opening section and a small opening section. The front end of the large opening section is sealed to the engine combustion chamber housing by a flange, and several exhaust holes 11 are provided on the wall surface of the large opening section near the front end face 18. The exhaust holes 11 are radially distributed through holes on the circumferential surface of the large opening section wall, and the size and number of through holes are designed according to the engine's pressure reduction rate requirements. The small opening section has three guide pin fixing threaded holes 14 evenly distributed along the circumference and parallel to the axis for installing guide pins 3. The inner wall surface of the small opening section of the outer casing 1 has two radial sealing grooves 13. The small opening section of the outer casing 1 also has three fluid through holes 12 evenly distributed along the circumference and along the axial direction.

[0037] The moving body 2 is a cylindrical cavity with openings at both ends, coaxially fitted inside the outer shell 1, and capable of axial movement. Its rear end face is sealed to the engine nozzle structure. The outer wall of the moving body 2 has a boss 23 near its front end, the top surface of which fits tightly against the inner wall of the large opening section of the outer shell 1. Two radial sealing grooves 22 are spaced at intervals on the top surface of the boss 23, the distance between the two grooves being greater than the diameter of the exhaust port. Three circumferentially evenly distributed, axially oriented guide holes 21 are provided on the cylindrical boss. These guide holes 21 are blind holes of a certain depth extending forward from the rear end face of the boss 23.

[0038] The guide pin 3 is a cylinder, with one end fixedly installed in the guide pin positioning hole 14 of the outer shell 1 by a thread, and the other end fitted into the guide hole 21 of the moving body 2. The guide pin 3 can move back and forth in the guide hole 21.

[0039] The heat insulation layer 4 is disposed on the inner surface of the moving body 2 and is made of rubber or high-silica phenolic resin composite material and is bonded to the inner cavity surface of the moving body 2 to reduce the heat transfer of high-temperature gas to the moving body 2.

[0040] Specifically, the length of the large opening section of the outer shell 1 is greater than the length of the cylindrical boss of the moving body 2, and the length of the cylindrical boss of the moving body 2 is greater than the diameter of the exhaust port 11 of the outer shell 1.

[0041] Specifically, when the moving body 2 approaches the combustion chamber, the protrusion 23 of the moving body 2 completely blocks the exhaust port 11 of the outer shell 1. When the moving body 2 approaches the small opening end, the protrusion 23 of the moving body 2 is in a position where it does not block the exhaust port 11 of the outer shell 1.

[0042] This invention also provides a rapid depressurization and flameout method for a reusable solid rocket engine, based on the aforementioned rapid depressurization and flameout device for a reusable solid rocket engine, comprising the following steps:

[0043] Under normal operating conditions of the solid rocket motor, the rapid pressure relief and flameout device is in the closed position, and the moving part 2 moves closer to the combustion chamber side, such as... Figure 1 As shown, the gap between the boss 23 of the moving body 2 and the small opening end of the outer shell forms a closed annular cavity 5. At this time, the annular cavity 5 is filled with a high-pressure fluid medium. Under the action of the high-pressure fluid, the annular cavity 5 restricts the movement of the moving body 2. When the solid rocket engine needs to be quickly depressurized and shut down, the rapid depressurization and shutdown device is activated. By controlling the fluid in the annular cavity 5 to flow out through the fluid passage 12 of the outer shell, under the action of the internal pressure of the combustion chamber gas, the moving body 2 moves rapidly towards the small opening end. At this time, the gas can be discharged through the exhaust port 11. Figure 5 As shown, due to the large flow area of ​​the exhaust port, the engine combustion chamber is rapidly depressurized, causing the engine to shut down. After the solid rocket engine shuts down, the high-pressure fluid is controlled to re-enter the annular cavity 5 through the driving fluid through-hole 12. Under the action of the driving fluid pressure, the moving body 2 moves forward to the large opening end, and the rapid depressurization and shutdown device is closed again. At this time, the engine can be restarted.

[0044] In summary, this invention provides a reusable solid rocket motor rapid depressurization and shutdown device and method. By controlling a small amount of fluid medium, it can drive the moving body to block or open the additional outer shell radial gas passage. By setting numerous radial exhaust holes, it can achieve rapid depressurization of the solid rocket motor combustion chamber, offering advantages such as rapid response and stable and reliable control. Furthermore, after the engine shuts down, the device can be reset, allowing for multiple engine shutdowns and restarts. This embodiment does not produce splashing explosive fragments during operation, does not damage the solid rocket motor, has minimal thrust disturbance, and features a simple structure that is easy to integrate with the engine. It is particularly suitable for small- to medium-diameter solid rocket motors.

[0045] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the specific implementation of the present invention. Any modifications or equivalent substitutions that do not depart from the spirit and scope of the present invention should be covered within the scope of protection of the claims of the present invention.

Claims

1. A reusable solid rocket motor rapid depressurization and flameout device, characterized in that, It includes an outer shell (1) and a moving body (2); the outer shell (1) is a cylindrical cavity with openings at both ends; one end is a large opening end, the end face of which is sealed and connected to the combustion chamber housing of the engine, and the other end is a small opening end, which is connected to the nozzle; the moving body (2) is a cylindrical cavity with openings at both ends, the moving body (2) is coaxially sleeved inside the outer shell (1), and an annular cavity (5) is formed between the moving body (2) and the small opening end of the outer shell (1), and the annular cavity (5) is filled with fluid. The body has several axial fluid through holes (12) at the small opening end, which are connected to the annular cavity (5) for extracting or filling fluid in the annular cavity (5). The moving body (2) moves axially between the large opening end and the small opening end by extracting or filling fluid in the annular cavity (5). Several exhaust holes (11) are provided circumferentially on the side wall of the large opening end. When the moving body (2) moves close to the small opening end, the gas in the generator combustion chamber flows to the exhaust holes (11).

2. The reusable solid rocket motor rapid depressurization and flameout device according to claim 1, characterized in that, The diameter of the small opening end is smaller than that of the large opening end, wherein the inner walls of the small opening end and the large opening end are stepped, and the moving body (2) forms an annular cavity (5) between the outer shell (1) and the small opening end.

3. The reusable solid rocket motor rapid depressurization and flameout device according to claim 1, characterized in that, Several guide pins (3) are provided between the small opening end and the moving body (2). Several guide pin fixing holes (14) parallel to the axis are provided at the small opening end, and guide holes (21) are provided on the moving body (2) corresponding to the guide pin fixing holes (14). One end of the guide pin (3) extends into the guide pin fixing hole (14), and the other end extends into the guide hole (21).

4. A rapid depressurization and flameout device for a reusable solid rocket motor according to claim 1, characterized in that, The inner wall surface of the small opening end is provided with a plurality of first sealing grooves (13) along the circumferential direction; a shell sealing ring (7) is correspondingly fitted in the plurality of first sealing grooves (13), and the shell sealing ring (7) is distributed between the shell sealing ring (7) and the outer wall surface of the moving body (2).

5. A rapid depressurization and flameout device for a reusable solid rocket motor according to claim 1, characterized in that, The moving body (2) is provided with a boss (23), which is in contact with the side wall of the large opening end. One side wall of the boss (23) is sealed to the engine combustion chamber housing, and the other side wall forms an annular cavity (5) between the small opening end and the boss (23). The top of the boss (23) is in contact with several exhaust holes (11).

6. A rapid depressurization and flameout device for a reusable solid rocket motor according to claim 5, characterized in that, The top surface of the boss (23) is provided with a plurality of second sealing grooves (22) along the circumferential direction. A moving body sealing ring (6) is fitted inside the second sealing groove (22). The moving body sealing ring (6) is located between the side wall of the large opening end and the boss (23).

7. A rapid depressurization and flameout device for a reusable solid rocket motor according to claim 5, characterized in that, The length of the inner side of the large opening end is greater than the length of the boss (23).

8. A rapid depressurization and flameout device for a reusable solid rocket motor according to claim 5, characterized in that, The length of the boss (23) is greater than the diameter of the vent hole (11).

9. A rapid depressurization and flameout device for a reusable solid rocket motor according to claim 1, characterized in that, The inner wall of the moving body (2) is attached with a heat insulation layer (4), which is made of rubber or high-silica phenolic resin composite material.

10. A method for rapid depressurization and flameout of a reusable solid rocket motor, based on the rapid depressurization and flameout device for a reusable solid rocket motor as described in any one of claims 1-8, characterized in that, Includes the following steps: Under normal operating conditions of the solid rocket motor, the rapid pressure relief and shutdown device is in the closed state. The moving body (2) moves closer to the combustion chamber side. The gap between the boss (23) of the moving body (2) and the small opening end of the outer shell forms a closed annular cavity (5). At this time, the annular cavity (5) is filled with high-pressure fluid medium. Under the action of the high-pressure fluid, the annular cavity (5) restricts the movement of the moving body (2). When the solid rocket engine needs to be quickly depressurized and shut down, the quick depressurization and shutdown device is activated. By controlling the fluid in the annular cavity (5) to flow out through the fluid passage (12) of the outer shell, the moving body (2) moves quickly towards the small opening end under the action of the internal pressure of the combustion chamber gas. At this time, the gas can be discharged through the exhaust hole (11). Due to the large flow area of ​​the exhaust hole, the engine combustion chamber is rapidly depressurized, causing the engine to shut down. After the solid rocket engine is shut down, the high-pressure fluid is controlled to re-enter the annular cavity (5) through the driving fluid passage (12). Under the action of the driving fluid pressure, the moving body (2) moves towards the large opening end. The quick depressurization and shutdown device is closed again. At this time, the engine can be restarted.

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