Isolation assembly and double-pulse rocket engine

Abstract

The invention relates to the technical field of solid rocket engines, and particularly provides an isolation assembly and a double-pulse rocket engine, the isolation assembly comprises: a housing which is provided with a first cavity, one end of which is provided with a first opening communicated with the first cavity, and the other end of which is provided with a second opening communicated with the first cavity; the shell is used for being installed in a spray pipe of the double-pulse solid rocket engine and located between every two adjacent charging cavities. The valve body is movably mounted in the first cavity and can do reciprocating motion in the axial direction of the shell; the valve body can be complementarily matched with the first opening so as to prevent the first cavity from communicating with the outside; the sealing element is arranged at the mutual matching part of the valve body and the first opening; and the locking piece is arranged on the valve body and / or the shell and used for restraining the movement of the valve body. The problems that in the prior art, a metal diaphragm of an isolation assembly is prone to falling off, and then a spray pipe is blocked and an engine breaks down are effectively solved.

Description

Technical Field

[0001] The present invention relates to the technical field of solid rocket engines, and in particular provides an isolation component and a dual-pulse rocket engine. Background Art

[0002] A dual-pulse solid rocket engine uses an isolation assembly to separate the combustion chambers, creating two propellant combustion chambers that share a common nozzle. Separate ignition systems control the combustion of the propellant in each chamber, delivering thrust at different times. The isolation assembly is a core component of the dual-pulse engine. It must withstand the operating pressure of the first pulse combustion chamber and remain reliably open during operation of the second pulse engine, providing a fuel gas flow path.

[0003] Currently, most isolation components use a metal diaphragm type. The main disadvantage of this method is that the metal diaphragm can easily separate from the main body, forming a free object, moving in the first-stage combustion chamber, blocking the nozzle, and causing engine failure. Summary of the Invention

[0004] The present invention provides an isolation component and a dual-pulse rocket engine, which solve the problem in the prior art that the metal diaphragm of the isolation component is easy to fall off, thereby causing nozzle blockage and engine failure.

[0005] In a first aspect, the present invention provides an isolation assembly comprising:

[0006] A shell is formed with a first cavity, has a first opening communicating with the first cavity at one end, and has a second opening communicating with the first cavity at the other end; the shell is used to be installed in the nozzle of a dual-pulse solid rocket motor and is located between two adjacent charge cavities;

[0007] a valve body movably mounted in the first cavity and capable of reciprocating along the axial direction of the housing; the valve body being capable of complementarily cooperating with the first opening to block communication between the first cavity and the outside;

[0008] a sealing member, disposed at a position where the valve body and the first opening cooperate with each other;

[0009] A locking member is provided on the valve body and / or the housing and is used to restrict the movement of the valve body.

[0010] According to the isolation assembly provided by the present invention, there are multiple second openings, which are respectively opened on the outer wall of the shell; the first opening is opened on the bottom of the shell, and the diameter of the first opening is larger than that of the second opening.

[0011] According to the isolation assembly provided by the present invention, the housing includes a base and a cover, and the cover is mounted on the base;

[0012] The first opening is formed on the base, and the cavity of the first opening is a closed-end type extending from the inner cavity of the shell to the outside;

[0013] The second openings are evenly distributed on the side wall of the cover body.

[0014] According to the isolation assembly provided by the present invention, the cavity shape of the first opening is truncated cone.

[0015] According to the isolation assembly provided by the present invention, the cavity shape of the first opening is a plurality of coaxially arranged cylinders, and the diameters of the plurality of cylinders are different and are arranged in decreasing order in the direction extending from the inner cavity of the shell to the outside.

[0016] According to the isolation assembly provided by the present invention, the valve body includes a valve stem and a valve head, the valve stem is fixedly connected to the valve head, and the valve stem is slidingly connected to the shell; the sealing member is arranged on the valve head and at the contact surface between the valve head and the first opening.

[0017] According to the isolation assembly provided by the present invention, the sealing member is a sealing ring.

[0018] According to the isolation assembly provided by the present invention, the locking member includes a pin, and when the valve body and the first opening cooperate with each other, the pin partially extends into the housing and partially extends into the valve body.

[0019] In a second aspect, the present invention also provides a dual-pulse rocket engine, comprising the isolation assembly described in the first aspect, and a dual-pulse rocket engine body, wherein the isolation assembly is installed in the nozzle of the dual-pulse rocket engine body and is located between two adjacent charge chambers.

[0020] The present invention provides a dual-pulse rocket engine isolation component. By arranging the isolation component in the nozzle of a dual-pulse solid rocket engine, adjacent charge chambers can be isolated to achieve sequential combustion in the two combustion chambers without affecting each other, thereby outputting thrust at different time periods.

[0021] By respectively providing a first opening and a second opening at both ends of the shell, and both being connected to the first cavity of the shell, a gas flow channel is formed, so that after the charge in the first pulse charge cavity is completely burned, the gas in the second pulse charge cavity can enter the first pulse charge cavity through this channel and continue to burn; by movably mounting the valve body on the shell, it can be achieved that when the first pulse charge is burning, due to the force of the high-pressure gas, the valve body can be tightly pressed against the first opening, thereby blocking the influence of the second pulse charge; when the first pulse charge is completely burned, the second pulse charge system is ignited, and the second pulse charge cavity generates high-pressure gas, which pushes the valve body to open, thereby opening the gas flow channel.

[0022] In this way, problems such as nozzle blockage and engine failure caused by traditional metal diaphragm isolation devices are solved.

[0023] Additional aspects and advantages of the present invention will be set forth in part in the description which follows and, in part, will be obvious from the description which follows, or may be learned by practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the present invention or the prior art, a brief introduction will be given below to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0025] Figure 1 1 is a schematic diagram of the longitudinal cross-sectional structure of the isolation assembly provided by the present invention in a closed state;

[0026] Figure 2 1 is a schematic diagram of the longitudinal cross-sectional structure of the isolation assembly provided by the present invention in an open state;

[0027] Figure 3 This is one of the three-dimensional structural diagrams of the isolation assembly provided by the present invention;

[0028] Figure 4 This is the second schematic diagram of the three-dimensional structure of the isolation component provided by the present invention;

[0029] Figure 5 This is a schematic diagram of the three-dimensional structure of another opening method of the second opening of the isolation assembly provided by the present invention;

[0030] Figure 6 This is a schematic longitudinal cross-sectional view of a first structure of the isolation assembly valve body provided by the present invention;

[0031] Figure 7 This is a schematic longitudinal cross-sectional view of a second structure of the isolation assembly valve body provided by the present invention;

[0032] Figure 8 This is a schematic diagram of a three-dimensional longitudinal section of a second structure of the isolation assembly valve body provided by the present invention;

[0033] Figure 9 This is a schematic structural diagram of the locking member of the isolation assembly provided by the present invention;

[0034] Figure 10 It is a schematic structural diagram of the dual-pulse rocket engine provided by the present invention.

[0035] Reference numerals:

[0036] 1. Shell; 101. First cavity; 102. First opening; 103. Second opening; 104. Base; 105. Cover; 2. Valve body; 201. Valve stem; 202. Valve head; 3. Seal; 301. Sealing ring; 4. Locking member; 401. Pin; 5. Rocket engine; 501. First pulse charge chamber; 502. Second pulse charge chamber. DETAILED DESCRIPTION

[0037] To make the objectives, technical solutions, and advantages of the present invention more clear, the technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0038] In the description of the embodiments of the present invention, it should be noted that the terms "upper," "lower," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended only to facilitate the description of the embodiments of the present invention and to simplify the description. They do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of the present invention. Furthermore, the terms "first," "second," etc., etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0039] In the description of the embodiments of the present invention, it should be noted that, unless otherwise specified or limited, the terms "connected" and "connection" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; mechanical connections, electrical connections; and direct connections or indirect connections through an intermediary. Those skilled in the art will understand the specific meanings of the above terms in the embodiments of the present invention based on the specific circumstances.

[0040] In the embodiments of the present invention, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediate medium. Furthermore, a first feature being "above," "above," or "above" a second feature may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. A first feature being "below," "below," or "below" a second feature may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0041] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the embodiments of the present invention. In this specification, the schematic expressions of the above terms do not refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and the features of different embodiments or examples without contradiction.

[0042] The following combination Figures 1 to 9 The embodiment shown describes the technical solution of the present invention:

[0043] An embodiment of the present invention provides an isolation component, such as Figures 1 to 4 As shown, it includes: a housing 1, a valve body 2, a sealing member 3 and a locking member 4;

[0044] Among them, the shell 1 is formed with a first cavity 101, one end of which has a first opening 102 connected to the first cavity 101, and the other end of which has a second opening 103 connected to the first cavity 101; the shell 1 is used to be installed in the nozzle of the dual-pulse solid rocket engine 5, and is located between two adjacent charge chambers; the valve body 2 is movably installed in the first cavity 101, and can reciprocate along the axial direction of the shell 1; the valve body 2 can complement the first opening 102 to block the communication between the first cavity 101 and the outside; the sealing member 3 is arranged at the mutual cooperation between the valve body 2 and the first opening 102; the locking member 4 is arranged on the valve body 2 and / or the shell 1, and is used to constrain the movement of the valve body 2.

[0045] In some embodiments, the housing 1 may be cylindrical or truncated cone-shaped, etc., and may be installed in the nozzle of a dual-pulse solid rocket engine 5 and located between two adjacent charge chambers. The sealing member 3 may be a graphite packing, a sealing plate, a sealant, or a mechanical seal, etc., and may ensure a tight connection between the valve body 2 and the housing 1, and may ensure that the charge chambers do not affect each other when operating in sequence.

[0046] In this embodiment, Figure 4 As shown, the shell 1 is truncated cone-shaped and is installed in the nozzle of the dual-pulse solid rocket engine 5, and is located between the first pulse charge cavity 501 and the second pulse charge cavity 502. A first cavity 101 is formed in the middle of the shell 1. One end of the shell 1 has a first opening 102 communicating with the first cavity 101, and the other end has a second opening 103 communicating with the first cavity 101.

[0047] The high-pressure gas generated by the second pulse charge in the second pulse charge cavity 502 enters the first cavity 101 of the shell 1 through the first opening 102 and then enters the first pulse charge cavity 501 through the second opening 103 to burn.

[0048] The valve body 2 is movably installed in the first cavity 101 and reciprocates along the axial direction of the shell 1. The first pulse charge in the first pulse charge cavity 501 reacts with the chemical substance to generate high-pressure gas, which is squeezed downward and discharged through the nozzle opened on the surface of the first pulse charge cavity 501, and enters the shell 1 through the second opening 103, acting on the valve body 2, so that the valve body 2 moves downward, thereby being tightly connected with the shell 1, so that the first opening 102 is closed. At this time, the high-pressure gas generated in the first pulse charge cavity 501 will not enter the second pulse charge cavity 502, and the charge cavities work in conjunction with each other. No interference; before the first pulse charge in the first pulse charge chamber 501 is almost consumed, the second pulse charge chamber 502 is activated, so that the second pulse charge inside it reacts with the oxidant to generate high-pressure gas, which is squeezed and discharged upward through the nozzle opened on the surface of the second pulse charge chamber 502. The thrust generated acts on the bottom of the valve body 2, pushing the valve body 2 upward and opening the first opening 102. At this time, the high-pressure gas generated in the second pulse charge chamber 502 flows into the shell 1 through the first opening 102, and flows into the first pulse charge chamber 501 through the second opening 103 to continue burning;

[0049] Due to the setting of the sealing member 3, when the first pulse charge chamber 501 burns, the high-pressure gas generated flows out from the nozzle on the surface of the first pulse charge chamber 501, and the thrust generated acts on the shell 1, so that the shell 1 and the valve body 2 fit tightly together. The sealing member 3 further seals the fitting part, preventing the high-pressure gas from entering the second pulse charge chamber 502 through the first opening 102 on the shell 1, ensuring that the charge chambers do not interfere with each other during operation.

[0050] The locking member 4 is provided to constrain the initial state of the valve body 2 and ensure that the valve body 2 does not move during the initial non-working motion.

[0051] An embodiment of the present invention provides a dual-pulse rocket engine isolation component. By arranging the isolation component in the nozzle of a dual-pulse solid rocket engine 5, adjacent charge chambers can be isolated to achieve sequential combustion in the two combustion chambers without affecting each other, thereby outputting thrust at different time periods.

[0052] By respectively opening a first opening 102 and a second opening 103 at both ends of the shell 1 and both being connected to the first cavity 101 of the shell 1, a gas flow channel is formed, so that after the charge in the first pulse charge cavity 501 is completely burned, the gas in the second pulse charge cavity 502 can enter the first pulse charge cavity 501 through this channel and continue to burn; by movably mounting the valve body 2 on the shell 1, it can be achieved that when the first pulse charge is burning, due to the force of the high-pressure gas, the valve body 2 can be tightly pressed against the first opening 102, thereby blocking the influence of the second pulse charge; when the first pulse charge is completely burned, the second pulse charge system is ignited, and the second pulse charge cavity 502 generates high-pressure gas, which pushes the valve body 2 to open, thereby opening the gas flow channel.

[0053] In this way, problems such as nozzle blockage and engine failure caused by traditional metal diaphragm isolation devices are solved.

[0054] According to an embodiment of the present invention, an isolation component is provided, such as Figures 1 to 5 As shown, there are multiple second openings 103 , which are respectively opened on the outer wall of the housing 1 ; the first opening 102 is opened on the bottom of the housing 1 , and the diameter of the first opening 102 is larger than that of the second opening 103 .

[0055] In some embodiments, as Figure 5 As shown, there are multiple second openings 103 opened at the top of the shell 1 to ensure that the high-pressure gas generated in the second pulse charge cavity 502 can flow into the first opening 102 opened at the bottom of the shell 1 and then flow out through the second openings 103 opened on the surface of the shell 1 to enter the first pulse charge cavity 501 for combustion;

[0056] In this embodiment, Figure 4 As shown, there are multiple second openings 103 opened on the outer wall of the shell 1. Compared with directly opening the second opening 103 on the top of the shell 1, the high-pressure gas generated in the second pulse charge cavity 502 takes a slightly longer time to enter the first pulse charge cavity 501, so that the high-pressure gas initially entering the first pulse charge cavity 501 can be fully burned, thereby improving the fuel utilization rate; at the same time, the diameter of the first opening 102 is larger than the second opening 103, which can enable the high-pressure gas generated by the second pulse charge cavity 502 to continuously enter the shell 1, and then enter the first pulse charge cavity 501 through the second opening 103, that is, the gas flow rate in the shell 1 keeps the inflow greater than the outflow, thereby ensuring that the rocket engine 5 can have sufficient fuel, avoiding the problem of fuel shortage, which causes problems to the rocket operation.

[0057] According to an embodiment of the present invention, an isolation component is provided, such as Figure 1 and Figure 4As shown, the housing 1 includes a base 104 and a cover 105 , and the cover 105 is mounted on the base 104 ;

[0058] The first opening 102 is formed on the base 104 and has a cavity shape extending from the inner cavity of the housing 1 to the outside.

[0059] The second openings 103 are evenly distributed on the sidewall of the cover body 105 .

[0060] In some embodiments, the housing 1 is a cylindrical structure directly mounted in the rocket engine 5 to isolate the first pulse charge cavity 501 from the second pulse charge cavity 502. At the same time, the first opening 102 can also be a circular hole directly opened on the surface of the base 104 of the housing 1 to allow the high-pressure gas generated in the second pulse charge cavity 502 to enter the housing 1 through the first opening 102. However, it is necessary to ensure that the size of the first opening 102 and the valve body 2 are closely fitted. Under the action of the seal 3, the high-pressure gas flowing into the housing 1 through the second opening 103 cannot enter the second pulse charge cavity 502 through the first opening 102.

[0061] In this embodiment, Figure 4 As shown, the housing 1 includes a base 104 and a cover 105. The base 104 is provided so that the first opening 102 is a deep, closed cavity. Compared to a circular hole-shaped first opening 102 directly opened at the bottom of the housing 1, the first opening 102 in this embodiment allows the high-pressure gas generated in the second pulse charge cavity 502 to enter the housing 1 slightly slower, allowing the gas initially entering the first pulse charge cavity 501 to be fully utilized, thereby improving fuel efficiency.

[0062] The second openings 103 are evenly distributed on the side wall of the cover body 105, which can make the high-pressure gas entering the shell 1 flow out evenly to the surroundings, so that the gas flow rate entering the first pulse charge cavity 501 is constant, ensuring the normal operation of the rocket engine 5.

[0063] According to an embodiment of the present invention, an isolation component is provided, such as Figure 6 As shown, the cavity shape of the first opening 102 is a truncated cone.

[0064] In this embodiment, the cavity shape of the first opening 102 is truncated cone-shaped. The truncated cone-shaped cavity ensures the flow stability of the high-pressure gas generated in the second pulse charge cavity 502 during the process of entering the shell 1 at the first opening 102. At the same time, the inclined surface of the truncated cone-shaped cavity can ensure that the pressure distribution of the high-pressure gas in the shell 1 is relatively uniform, and will not cause an excessively large pressure difference between the inside and outside of the shell 1, thereby damaging the shell 1 or even causing malfunction of the rocket engine 5.

[0065] According to an embodiment of the present invention, an isolation component is provided, such as Figure 7 and Figure 8 As shown, the cavity shape of the first opening 102 is a plurality of coaxially arranged cylinders, and the diameters of the plurality of cylinders are different, and are arranged in decreasing order in the direction extending from the inner cavity of the housing 1 to the outside.

[0066] In this embodiment, a new cavity type of the first opening 102 is added, which is composed of a plurality of coaxially arranged cylinders whose diameters are gradually reduced from the inner cavity of the shell 1 to the outside. Compared with the direct truncated cone cavity type, this cylindrical cavity type is simpler in the initial production. At the same time, it is simpler to set the sealing member 3 between the cylinders with gradually reduced diameters.

[0067] Between the large cylinder and the smaller cylinder, the sealing shape of the seal 3 is better at this time. At the same time, because this type of cavity is simple to make, it is more convenient to replace the shell 1 when encountering an emergency. At the same time, in the initial state, the valve body 2 is more fully abutted against the first opening 102. During the transportation of the rocket, the valve body 2 can always abut against the shell 1 to ensure that the first pulse charge cavity 501 and the second pulse charge cavity 502 do not interfere with each other.

[0068] According to an embodiment of the present invention, an isolation component is provided, such as Figure 7 As shown, the valve body 2 includes a valve stem 201 and a valve head 202 , the valve stem 201 is fixedly connected to the valve head 202 , and the valve stem 201 is slidably connected to the housing 1 ; the sealing member 3 is arranged on the valve head 202 and at the contact surface between the valve head 202 and the first opening 102 .

[0069] In this embodiment, the valve body 2 is composed of a valve stem 201 and a valve head 202, wherein the valve stem 201 is fixedly connected to the valve head 202. Initially, the locking member 4 connects and fixes the valve stem 201 to the cover 105 of the shell 1, so that the valve body 2 is fixed in the first cavity 101 in the shell 1, ensuring that the valve body 2 is relatively stationary during non-working motion. When the rocket engine 5 is working, the high-pressure gas generated in the first pulse charge cavity 501 flows out from the nozzle on the first pulse charge cavity 501 and flows into the isolation assembly, while the valve stem 201 is slidably connected to the shell 1. At this time, the high-pressure gas enters the shell 1. , acting on the valve head 202, causing the valve head 202 to drive the valve stem 201 to move downward and tightly abut against the base 104 of the housing 1. Although the valve body 2 is tightly connected to the base 104 of the housing 1, they are not the same mechanical parts. The fixed connection may still allow part of the high-pressure gas generated in the first pulse charge chamber 501 to enter the second pulse charge chamber 502 through the first opening 102, affecting the second pulse charge therein. Therefore, a sealing member 3 is required to fully close the contact surface between the valve head 202 and the first opening 102 to ensure that the high-pressure gas does not enter the second pulse charge chamber 502;

[0070] Before the first pulse charge in the first pulse charge cavity 501 is fully burned out, the second pulse charge in the second pulse charge cavity 502 is started to generate high-pressure gas, which flows out through the nozzle on the second pulse charge cavity 502, pushing the valve head 202 to move upward, so that the valve body 2 is away from the first opening 102 on the surface of the shell 1. At this time, the high-pressure gas generated by the second pulse charge cavity 502 can flow into the shell 1 through the first opening 102 at the bottom of the shell 1, and then flow out through the second opening 103 on the surface of the shell 1, and enter the first pulse charge cavity 501 through the nozzle on the surface of the first pulse charge cavity 501, thereby continuously providing fuel for the rocket engine 5.

[0071] According to an embodiment of the present invention, an isolation component is provided, such as Figure 2 As shown, the sealing member 3 is a sealing ring 301 .

[0072] In this embodiment, the sealing member 3 is preferably a sealing ring 301. Within the working pressure and a certain temperature range, the sealing ring 301 has good sealing performance. As the high-pressure gas in the first pulse charge chamber 501 enters the shell 1 through the second opening 103, the pressure on the base 104 of the shell 1 gradually increases, and the sealing ring 301 can also automatically improve its sealing performance; and the sealing ring 301 has good corrosion resistance and durability. When the fuel gas is in the shell 1, its corrosion resistance increases its service life and better protects the rocket engine 5; compared with ordinary mechanical seals, the sealing ring 301 has a simpler structure, is more convenient to replace and has lower maintenance costs, and has low power loss without the need for frequent adjustment of the compression; at the same time, the sealing ring 301 has good high and low temperature resistance, and can maintain elasticity when the rocket engine 5 is under various extreme temperature conditions, ensuring normal operation in various harsh environments.

[0073] According to an embodiment of the present invention, an isolation component is provided, such as Figure 7 and Figure 9 As shown, the locking member 4 includes a pin 401 . When the valve body 2 and the first opening 102 cooperate with each other, the pin 401 partially extends into the housing 1 and partially extends into the valve body 2 .

[0074] In some embodiments, as Figure 9As shown, the locking member 4 includes an oblique pin and a spring, one end of the spring is connected to the cover 105 of the housing 1, and the oblique pin is fixed to the other end of the spring, wherein the oblique pin part extends into the valve stem 201 of the valve body 2. Initially, the valve body 2 is relatively fixed by setting a part of the oblique pin in the valve stem 201 and a part in the cover 105. When the high-pressure gas generated in the first pulse charging chamber 501 flows out from the nozzle of the first pulse charging chamber 501, the high-pressure gas enters the housing 1 from the second opening 103, and is sprayed on the valve head 202, driving the valve stem 201 to move downward, so that the valve head 202 abuts against the first opening 102, thereby closing the first opening 102, which is used to isolate the high-pressure gas and ensure that it does not enter the second pulse charging chamber. In the powder cavity 502; before the first pulse charge in the first pulse charge cavity 501 is completely burned, the second pulse charge cavity 502 is started, and the high-pressure gas generated therein flows out through the nozzle on the surface of the second pulse charge cavity 502, acts on the valve head 202, and pushes the valve stem 201 to move upward. At this time, the inclined surface of the inclined pin contacts the valve stem 201. Under the upward thrust, the inclined pin retracts the compression spring, and the inclined pin moves away from the valve body 2. The valve body 2 moves upward under the thrust of the high-pressure gas, thereby opening the first opening 102, allowing the high-pressure gas to enter the interior of the shell 1 through the first opening 102 at the bottom of the shell 1, and then flow out of the shell 1 through the second opening 103 on the surface of the shell 1, and then enter the first pulse charge cavity 501 to continue burning;

[0075] In this embodiment, the locking member 4 is preferably a pin 401. When the valve body 2 is engaged with the first opening 102, a portion of the pin 401 extends into the housing 1, and a portion extends into the valve body 2. At this time, the valve head 202 of the valve body 2 fully abuts the first opening 102, actuating the first pulse charge chamber 501. The first pulse charge therein fully contacts and reacts with the chemical substance, generating high-pressure gas that drives the rocket engine 5 to operate. Simultaneously, the high-pressure gas acts on the valve head 202, causing the valve body 2 to move downward and further abut against the first opening 102. The sealing ring 301 further seals the mating point between the first opening 102 and the housing 1.

[0076] Before the first pulse charge in the first pulse charge chamber 501 is completely burned out, the second pulse charge chamber 502 is activated. The second pulse charge in the second pulse charge chamber 502 contacts and reacts with the chemical substance to generate high-pressure gas, which then flows out from the nozzle on the surface of the second pulse charge chamber 502. The high-pressure gas expands and abuts against the valve head 202, pushing it to move upward. Since the valve stem 201 is slidably connected to the housing 1, the valve stem 201 moves upward under the action of the high-pressure gas, thereby breaking the pin 401. A portion of the broken pin 401 is located in the pin hole provided on the surface of the housing 1 for mounting the pin 401. A part of it is inside the valve stem 201 and will not fall into the second pulse charge cavity 502, thus avoiding the problem of clogging the nozzle and causing a malfunction of the rocket engine 5; and the valve stem 201 drives the valve head 202 away from the first opening 102, so that the high-pressure gas generated in the second pulse charge cavity 502 enters the interior of the shell 1 through the first opening 102 at the bottom of the shell 1, and then flows out of the shell 1 through the second opening 103 opened on the surface of the shell 1, and enters the first pulse charge cavity 501 through the nozzle on the surface of the first pulse charge cavity 501, so that the rocket engine 5 continues to work.

[0077] According to an embodiment of the present invention, a dual-pulse rocket engine is provided. Figure 1 and Figure 10 As shown, it includes the isolation component as described above and also includes a dual-pulse rocket engine 5 body. The isolation component is installed in the nozzle of the dual-pulse rocket engine 5 body and is located between two adjacent charge chambers.

[0078] In this embodiment, a rocket engine 5 is installed in a rocket. The rocket engine 5 includes a first pulse charge chamber 501, a second pulse charge chamber 502, and an isolation assembly. The isolation assembly is arranged between the first pulse charge chamber 501 and the second pulse charge chamber 502. In the rocket engine 5, the isolation assembly initially constrains the position of the valve body 2 with a pin 401, so that it abuts against the first opening 102. During operation, the first pulse charge chamber 501 is activated, and the first pulse charge therein reacts with the chemical substance to generate high-pressure gas, which is squeezed and discharged by the nozzle on the first pulse charge chamber 501 and enters the shell 1 through the second opening 103 on the surface of the shell 1. The gas acts on the valve head 202 of the valve body 2 in the first cavity 101, causing the valve body 2 to fit tightly with the shell 1, fully blocking the first opening 102. The provided seal 3 further fits the matching portion between the valve body 2 and the first opening 102, so that the high-pressure gas does not pass through the first opening 102.

[0079] Before the first pulse charge in the first pulse charge chamber 501 is completely burned, the second pulse charge chamber 502 is started, so that the second pulse charge inside it contacts the chemical substance to generate high-pressure gas. The generated high-pressure gas is squeezed and discharged by the nozzle on the surface of the second pulse charge chamber 502, squeezing the valve head 202 of the valve body 2 at the first opening 102. Since the valve body 2 is slidably connected to the shell 1 and the valve head 202 is fixed to the valve stem 201, the high-pressure gas squeezes the valve head 202 to move it upward, driving the valve stem 201 to move upward. During the upward movement of the valve stem 201, the pin 40 is pressed. 1 is broken, and the pin 401 is partially inside the valve stem 201 and partially in the pin hole on the surface of the shell 1. No falling objects will cause blockage of the nozzle, ensuring the normal operation of the rocket engine 5. Due to the upward movement of the valve body 2, the first opening 102 is opened, and the high-pressure gas generated by the second pulse charge chamber 502 can enter the interior of the shell 1 through the first opening 102 at the bottom of the shell 1, and then flow out through the second opening 103 opened on the surface of the shell 1. The high-pressure gas then enters the first pulse charge chamber 501 through the nozzle on the surface of the first pulse charge chamber 501, so that the rocket engine 5 keeps working.

[0080] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. An isolation component, characterized in that: include: a housing, forming a first cavity, having a first opening at one end communicating with the first cavity, and having a second opening at the other end communicating with the first cavity; The housing is used to be installed in the nozzle of a dual-pulse solid rocket engine and is located between two adjacent charge chambers; a valve body movably mounted in the first cavity and capable of reciprocating along the axial direction of the housing; the valve body being capable of complementarily cooperating with the first opening to block communication between the first cavity and the outside; a sealing member, disposed at a position where the valve body and the first opening cooperate with each other; A locking member is provided on the valve body and / or the housing and is used to restrict the movement of the valve body.

2. The isolation assembly according to claim 1, wherein: There are a plurality of second openings, which are respectively opened on the outer wall of the shell; the first opening is opened on the bottom of the shell, and the diameter of the first opening is larger than that of the second opening.

3. The isolation assembly according to claim 2, wherein: The housing includes a base and a cover, and the cover is mounted on the base; The first opening is formed on the base, and the cavity of the first opening is a closed-end type extending from the inner cavity of the shell to the outside; The second openings are evenly distributed on the side wall of the cover body.

4. The isolation assembly according to claim 3, characterized in that The cavity shape of the first opening is truncated cone.

5. The isolation assembly according to claim 3, wherein: The cavity shape of the first opening is a plurality of coaxially arranged cylinders, and the diameters of the plurality of cylinders are different, and are arranged in decreasing order in a direction extending from the inner cavity of the shell to the outside.

6. The isolation assembly according to claim 1, wherein: The valve body includes a valve stem and a valve head, the valve stem is fixedly connected to the valve head, and the valve stem is slidably connected to the housing; the sealing member is arranged on the valve head and at the contact surface between the valve head and the first opening.

7. The isolation assembly according to claim 6, wherein: The sealing member is a sealing ring.

8. The isolation assembly according to claim 1, wherein: The locking member includes a pin, and when the valve body and the first opening cooperate with each other, the pin partially extends into the housing and partially extends into the valve body.

9. A dual-pulse rocket engine, characterized in that: It comprises the isolation assembly as described in any one of claims 1-8, and also comprises a dual-pulse rocket engine body, wherein the isolation assembly is installed in the nozzle of the dual-pulse rocket engine body and is located between two adjacent charge chambers.

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