Diaphragm assembly, starter of rocket power system and rocket power system

Abstract

The invention provides a diaphragm assembly, a starter of a rocket power system and the rocket power system. The diaphragm assembly is applied to a starter of a rocket power system, and comprises a mounting seat which at least partially stretches into and is hermetically connected to a nozzle orifice of the starter along the axial direction; the mounting seat comprises a first part and a second part which are distributed along the axial direction; the first part is provided with a plurality of hollow-out parts along the axial direction; the second part is provided with a concave structure with an opening away from the first part; the outer peripheral wall of the diaphragm is connected with the inner peripheral wall of the sunken structure; and the hollow part is communicated between the space in the spray pipe and the diaphragm. The connection between the diaphragm assembly and the nozzle orifice is high in reliability, good in sealing performance and convenient to replace, and the reusability and economical efficiency of the starter of the rocket power system can be improved.

Description

Technical Field

[0001] The present application relates to the technical field of rocket propulsion systems of launch vehicles. Specifically, the present application relates to a diaphragm assembly, a starter of a rocket propulsion system, and a rocket propulsion system. Background Art

[0002] In the rocket propulsion system of a launch vehicle, a starter is often required to provide initial kinetic energy for the turbo pump of the rocket propulsion system to start spinning. With the rapid development of application technologies such as rocket trajectory change, rocket precise orbit insertion, and rocket recovery, the multiple starting technology of liquid rocket propulsion systems has become the key.

[0003] The rocket propulsion system needs to be started multiple times, and multiple gunpowder starters are required. Each time it is started, at least one starter is used to generate energy to drive the turbopump, which in turn drives the turbopump to transport the propellant into the engine combustion chamber and burn it to generate thrust. Taking the secondary start as an example, each start uses a starter, and the starter corresponding to the secondary start needs to isolate the high-temperature and high-pressure gas caused by the combustion of the propellant after the primary start, to avoid the rocket propulsion system working abnormally due to the false start of the secondary starter caused by the continuous impact of the gas.

[0004] In the related art, the diaphragm of the starter is easily affected by the high-temperature and high-pressure combustion gas generated by the previous start-up and may fall off or break, thereby causing the starter to work abnormally and resulting in the failure of the launch of the carrier rocket. Summary of the invention

[0005] In view of the shortcomings of the existing methods, the present application proposes a diaphragm assembly, a starter for a rocket power system and a rocket power system, so as to solve the technical problem in the related art that the diaphragm of the starter is easily affected by the high-temperature and high-pressure combustion gas generated by the previous start-up and thus falls off or breaks.

[0006] In a first aspect, an embodiment of the present application provides a diaphragm assembly, which is applied to a starter of a rocket power system, comprising: The mounting seat at least partially penetrates into the nozzle of the starter along the axial direction and is sealed and connected to the nozzle of the starter; the mounting seat comprises a first part and a second part distributed along the axial direction; the first part has a plurality of hollows along the axial direction; the second part has a concave structure with an opening facing away from the first part; The diaphragm has an outer peripheral wall connected to the inner peripheral wall of the recessed structure; The hollowing is connected between the space in the nozzle and the diaphragm.

[0007] In some possible embodiments, one side of the diaphragm contacts or abuts against the first portion to seal the hollowing.

[0008] In some possible embodiments, an outer diameter of at least a portion of the second portion is greater than an outer diameter of the first portion.

[0009] In some possible embodiments, along the radial direction, the peripheral wall of the outermost hollow and recessed structure and the outer peripheral wall of the first part are successively away from the axial direction.

[0010] In some possible embodiments, the diaphragm includes a plane portion and an edge portion connected to an outer peripheral wall of the plane portion; The edge portion is flush with the side of the planar portion facing the first portion, the edge portion extends in an axial direction away from the first portion, and gradually becomes thicker in a radial direction away from the planar portion.

[0011] In some possible embodiments, the first portion is recessed toward one side inside the nozzle, and the center of the first portion is recessed the deepest.

[0012] In some possible embodiments, a side of the membrane away from the first portion has a plurality of strip-shaped notches; The midpoints of the multiple notches intersect and are located at the center of the diaphragm; The center position of the first portion coincides with the midpoint where the plurality of notches intersect along the axial direction.

[0013] In some possible embodiments, the recessed structure includes a first recessed section and a second recessed section distributed along an axial direction away from the first portion; The radial dimension of the first recessed section is smaller than the radial dimension of the second recessed section; The outer peripheral wall of the diaphragm is connected to the inner peripheral wall of the first recessed section.

[0014] In a second aspect, an embodiment of the present application further provides a starter for a rocket power system, comprising: a starting combustion chamber, a nozzle, and any diaphragm assembly provided in the first aspect above; One end of the nozzle is connected to the starting combustion chamber, and the nozzle opening at the other end faces away from the starting combustion chamber; The diaphragm assembly at least partially penetrates into the nozzle opening in the axial direction and is sealingly connected to the nozzle opening.

[0015] In some possible embodiments, the starter further includes: a sealing ring; The sealing ring is arranged outside the first part of the partial diaphragm assembly and is sealed and connected with the nozzle opening.

[0016] In a third aspect, an embodiment of the present application further provides a rocket propulsion system, comprising: a turbo pump and any starter provided in the second aspect above; The turbo pump is connected to the other end of the starter nozzle.

[0017] The beneficial technical effects brought about by the technical solution provided by the embodiment of the present application include: 1. The embodiment of the present application uses a mounting seat to indirectly mount the diaphragm on the nozzle mouth. Compared with the diaphragm, the mounting seat has higher thickness and strength, higher connection reliability with the nozzle mouth, good sealing, and is easy to replace, which can improve the reusability and economy of the starter of the rocket power system.

[0018] 2. The diaphragm assembly provided by the present application at least partially protrudes into the nozzle orifice and can be installed from the outside of the nozzle orifice to the inside. Compared with the technical solution in the related art that the diaphragm needs to be installed in the nozzle orifice first, and then the nozzle is installed at one end of the starter combustion chamber of the starter, the embodiment of the present application has no restrictions on the installation sequence of the starter and the nozzle. After the starter is ignited, the mounting seat can be removed from the nozzle of the starter, so that the starter combustion chamber and the nozzle of the starter can be reused.

[0019] 3. Different from the technical solution in the related art that can only weld the diaphragm to the nozzle by brazing in the nozzle due to the limited installation space in the nozzle, in the embodiment of the present application, the diaphragm and the mounting seat can be assembled and welded before being installed at the nozzle mouth, and the welding is less affected by the environment. A welding method with higher reliability than brazing can be used before installation in the nozzle, thereby improving the connection reliability between the diaphragm and the mounting seat, improving the working reliability of the starter, and facilitating the normal launch of the carrier rocket.

[0020] Additional aspects and advantages of the present application will be partially given in the following description, which will become apparent from the following description, or will be understood through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which: Figure 1 A schematic structural diagram of an axial cross section of a diaphragm assembly provided in an embodiment of the present application and arranged at a nozzle port of a starter; Figure 2 A schematic diagram of the side structure of a diaphragm assembly provided in an embodiment of the present application; Figure 3 for Figure 2 Schematic diagram of the cross section at the AA section; Figure 4 A schematic diagram of the structure of a diaphragm of a diaphragm assembly provided in an embodiment of the present application; Figure 5 A schematic structural diagram of a mounting base for a diaphragm assembly provided in an embodiment of the present application.

[0022] Reference numerals: 10- diaphragm assembly; 11-mounting seat; 111-first part; 1110-hollowing; 112-second part; 1120-recessed structure; 1121-first recessed section; 1122-second recessed section; 12-diaphragm; 121-plane portion; 122-edge portion; 123-notch; 20-nozzle; 21-nozzle opening; 30-Sealing ring. DETAILED DESCRIPTION

[0023] The embodiments of the present application are described below in conjunction with the drawings in the present application. It should be understood that the implementation methods described below in conjunction with the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0024] Those skilled in the art will appreciate that, unless expressly stated, the "said" and "the" used herein may also include plural forms. It should be further understood that the term "including" used in the specification of the present application refers to the presence of the features, integers, elements and / or components, but does not exclude the implementation of other features, information, data, operations, elements, components and / or combinations thereof supported by the technical field. The term "and / or" used herein refers to at least one of the items defined by the term, for example, "A and / or B" may be implemented as "A", or as "B", or as "A and B".

[0025] In order to make the objectives, technical solutions and advantages of the present application clearer, the implementation methods of the present application will be further described in detail below with reference to the accompanying drawings.

[0026] First, the nouns involved in this application are introduced and explained: Starter: A device used to ignite a rocket's propulsion system. It provides initial power to the engine and its outlet is connected to the engine's turbopump.

[0027] Diaphragm assembly: A partitioning device installed at the outlet of the starter. It ruptures after being impacted, allowing the energy generated by the starter to be transmitted from the outlet to the turbine pump, thereby starting the turbine.

[0028] The rocket propulsion system needs to be started multiple times with multiple gunpowder starters. Each time it is started, at least one starter is used to generate energy to drive the turbo pump, which then drives the turbo pump to transport the propellant to the engine combustion chamber and burn it to generate thrust. Taking the secondary start as an example, each start uses a starter. The starter corresponding to the secondary start needs to isolate the high-temperature and high-pressure gas caused by the combustion of the propellant after the primary start to avoid the secondary starter's false start caused by the continuous impact of the gas, which may cause the rocket propulsion system to work abnormally.

[0029] In the related art, a nozzle is provided at the outlet of the starter, and a diaphragm assembly of the starter is provided at the nozzle mouth, isolating the interior of the starter from the turbo pump, and further isolating the interior of the starter from the combustion chamber of the engine. Moreover, since the nozzle has a larger opening at one end close to the starting combustion chamber inside the starter, and the nozzle opening away from the starting combustion chamber and close to the turbo pump is smaller, the diaphragm needs to first pass through the end with a larger opening and be installed in the nozzle mouth, and then the nozzle is installed at one end of the starting combustion chamber of the starter. Therefore, in the narrow space inside the nozzle, the diaphragm and the nozzle are mostly fixed by brazing. The inherent characteristics of brazing result in poor connection strength and poor heat resistance.

[0030] Moreover, since the diaphragm is welded inside the nozzle, the nozzle fails after the starter is started, making it difficult to reuse.

[0031] Moreover, the diaphragm needs to be easy to break and is very thin. This makes the connection strength between the diaphragm and the nozzle mouth poor, making the diaphragm easily broken or even detached from the nozzle mouth by the impact of high-temperature and high-pressure combustion gas generated from the engine combustion chamber during the previous start-up, thereby causing the starter to work abnormally and leading to the failure of the carrier rocket launch.

[0032] The diaphragm assembly, rocket power system starter and rocket power system provided in this application are intended to solve the above technical problems of related technologies.

[0033] The following is a detailed description of the technical solution of the present application and how the technical solution of the present application solves the above technical problems with specific embodiments. It should be noted that the following implementations can refer to, draw on or combine with each other, and the same terms, similar features and similar implementation steps in different implementations will not be described repeatedly.

[0034] The present application embodiment provides a diaphragm assembly 10, which is applied to a starter of a rocket power system. Please refer to Figure 1-Figure 3 The diaphragm assembly 10 includes a mounting seat 11 and a diaphragm 12 .

[0035] The mounting seat 11 at least partially penetrates into the nozzle port 21 of the starter along the axial direction and is sealed and connected to the nozzle port 21 of the starter; the mounting seat 11 includes a first portion 111 and a second portion 112 distributed along the axial direction; the first portion 111 has a plurality of axial hollows 1110; the second portion 112 has a recessed structure 1120 with an opening facing away from the first portion 111.

[0036] The outer peripheral wall of the diaphragm 12 is connected to the inner peripheral wall of the recessed structure 1120 .

[0037] The hollow 1110 communicates between the space in the nozzle 20 and the diaphragm 12 .

[0038] In this embodiment, the mounting seat 11 is arranged at the nozzle mouth 21, and the diaphragm 12 is arranged in the recessed structure 1120 on one side of the mounting seat 11. The side of the mounting seat 11 facing the nozzle 20 has a hollow 1110, so that the high-pressure gas ejected from the nozzle 20 can break through the diaphragm 12 through the hollow 1110, and then be conducted into the turbo pump, thereby starting the turbo pump. The embodiment of the present application uses the mounting seat 11 to indirectly mount the diaphragm 12 on the nozzle mouth 21. Compared with the diaphragm 12, the mounting seat 11 has a higher thickness and strength, a higher connection reliability with the nozzle mouth 21, good sealing, and is easy to replace, which can improve the reusability and economy of the starter of the rocket power system.

[0039] Moreover, the diaphragm assembly 10 provided by the present application at least partially penetrates into the nozzle mouth 21, and can be installed from the outside of the nozzle mouth 21 to the inside. Compared with the technical solution in the related art that the diaphragm 12 needs to be installed in the nozzle mouth 21 first, and then the nozzle 20 is installed at one end of the starter combustion chamber of the starter, the embodiment of the present application has no restriction on the installation sequence of the starter and the nozzle 20. After the starter is ignited, the mounting seat 11 can be removed from the nozzle 20 of the starter, so that the starter combustion chamber and the nozzle 20 of the starter can be reused.

[0040] In addition, unlike the technical solution in the related art that is limited by the small installation space in the nozzle 20 and can only use brazing to weld the diaphragm 12 to the nozzle 20, the diaphragm 12 and the mounting seat 11 can be assembled and welded before being installed in the nozzle mouth 21. The welding is less affected by the environment, and a welding method with higher reliability than brazing can be used before being installed in the nozzle 20. This can improve the connection reliability between the diaphragm 12 and the mounting seat 11, improve the working reliability of the starter, and facilitate the normal launch of the carrier rocket.

[0041] It should be noted that, in the embodiment of the present application, the inward end (one side) refers to the end (one side) facing the inside of the nozzle 20, and the outward end (one side) refers to the end (one side) facing the outside of the nozzle 20 and toward the turbine pump.

[0042] In some possible embodiments, vacuum electron beam welding is used between the outer peripheral wall of the diaphragm 12 and the inner peripheral wall of the recessed structure 1120, which can increase the strength of the weld and improve the heat resistance and precision of the weld.

[0043] In some possible embodiments, Figure 3 As shown, one side of the diaphragm 12 contacts or abuts against the first portion 111 to seal the hollow 1110 .

[0044] In this embodiment, the diaphragm 12 contacts or abuts against the first portion 111, thereby minimizing the possibility of a gap between the diaphragm 12 and the first portion 111. When subjected to impact from the turbo pump (i.e., impact force from outside the nozzle 20), the side of the diaphragm 12 facing the inside of the nozzle 20 can be supported by the first portion 111, thereby minimizing the degree of deformation of the diaphragm 12, thereby reducing the possibility of the diaphragm 12 being ruptured by the impact from the turbo pump.

[0045] For some possible embodiments, please refer to Figure 5 , the outer diameter of at least part of the second portion 112 is greater than the outer diameter of the first portion 111 .

[0046] In this embodiment, the outer diameter of at least part of the second portion 112 is greater than the outer diameter of the first portion 111, so that a first step surface is formed between the outer peripheries of the first portion 111 and the second portion 112 of the mounting seat 11, and the inner wall at the nozzle mouth 21 also has a second step surface. When the mounting seat 11 is inserted into the nozzle mouth 21, the first step surface on the outer periphery of the mounting seat 11 abuts against the second step surface in the nozzle mouth 21, which can effectively prevent the mounting seat 11 from sliding into the nozzle 20.

[0047] Moreover, when the nozzle 20 of the starter is mounted on the turbo pump, the turbo pump can abut against the mounting seat 11. Therefore, the inward side of the mounting seat 11 is abutted by the second step surface of the nozzle 20, and the outward side of the mounting seat 11 is abutted by the turbo pump, so that the mounting seat 11 can be fixed at the nozzle port 21, and there is no need to use other fixing methods such as welding between the mounting seat 11 and the nozzle 20, which can reduce the installation difficulty and installation cost of the diaphragm assembly 10 and improve the installation efficiency.

[0048] In some possible implementations, a third step surface is further away from the nozzle port 21 than the second step surface in the nozzle 20. The third step surface can abut against the inward side of the first portion 111, further ensuring that the mounting seat 11 is fixed at the nozzle port 21, and preventing the mounting seat 11 from being impacted by the turbo pump and being washed away from the nozzle port 21, thereby causing accidents such as starter failure.

[0049] For some possible embodiments, please refer to Figure 3 , along the radial direction, the outermost hollow 1110, the peripheral wall of the recessed structure 1120 and the outer peripheral wall of the first portion 111 are successively away from the axial direction.

[0050] In this embodiment, the hollow 1110 is only opened in the middle area of ​​the first part 111, ensuring that the peripheral area of ​​the first part 111 has sufficient strength to support the diaphragm 12, and ensuring effective abutment between the first step of the mounting seat 11 and the nozzle mouth 21, thereby preventing the mounting seat 11 from being washed away from the nozzle mouth 21 due to the impact from the turbine pump, thereby causing accidents such as starter failure.

[0051] For some possible embodiments, please refer to Figure 3 and Figure 4 The diaphragm 12 includes a plane portion 121 and an edge portion 122 connected to the outer periphery of the plane portion 121 .

[0052] The edge portion 122 is flush with the side of the planar portion 121 facing the first portion 111 . The edge portion 122 extends in an axial direction away from the first portion 111 and gradually becomes thicker in a radial direction away from the planar portion 121 .

[0053] In this embodiment, the inner side of the diaphragm 12 is flat, and the outer side edge portion 122 protrudes along the axial direction and is concave. Therefore, compared with the plane portion 121, the edge portion 122 is thicker. When the edge portion 122 is connected to the inner peripheral wall of the recessed structure 1120 of the mounting seat 11, the edge portion 122 can better disperse stress and reduce stress concentration, thereby reducing the risk of the diaphragm 12 breaking or separating from the mounting seat 11, thereby ensuring the normal operation of the starter.

[0054] In some embodiments, the connection between the inner side of the edge portion 122 of the diaphragm 12 and the outer peripheral wall is smoothly transitioned, which is equivalent to the equal strength design of the diaphragm 12 itself, thereby improving the connection strength between the inner peripheral wall of the recessed structure 1120 and reducing the possibility of accidents caused by single point failure at the connection.

[0055] In some possible embodiments, Figure 1 and Figure 3 As shown, the first portion 111 is recessed toward one side of the nozzle 20, and the center of the first portion is recessed the deepest.

[0056] In this embodiment, the first portion 111 is recessed on one side facing inward to form a bowl shape. The center position of the first portion corresponds to the center position of the bowl-shaped structure. The recess is the deepest and can serve as an energy concentration area, which facilitates the concentrated conduction of energy from the starting combustion chamber to the center of the diaphragm 12, ensuring that the diaphragm 12 ruptures normally from the center, thereby allowing the energy to be ejected through the nozzle port 21.

[0057] In some possible embodiments, Figure 2 and Figure 3 As shown, the side of the membrane 12 away from the first portion 111 has a plurality of strip-shaped notches 123 .

[0058] The midpoints of the plurality of notches 123 intersect and are located at the center of the diaphragm 12 .

[0059] The center position of the first portion 111 coincides with the midpoint where the plurality of notches 123 intersect along the axial direction.

[0060] In this embodiment, the center of the diaphragm 12 coincides axially with the center of the first part 111, and the center of the notch 123 coincides axially with the center position of the depression of the first part 111. When the first part 111 conducts the energy from the starting combustion chamber to the center of the diaphragm 12, it is beneficial for the energy to act directly on the center where multiple notches 123 intersect, making it easier for the notches 123 of the diaphragm 12 to break from the center to the surrounding area, thereby improving the working reliability of the starter.

[0061] Alternatively, if Figure 2 As shown, the notch 123 is " " is carved on the side of the diaphragm 12 away from the first part 111, and there is no notch on the side of the diaphragm 12 close to the first part 111, so that the side of the diaphragm 12 without notch is directly in close contact with the first part 111 when subjected to high-pressure gas generated in the engine combustion chamber, and is not easily broken under the support of the first part 111.

[0062] In some possible embodiments, Figure 3 and Figure 5 As shown, the recessed structure 1120 includes a first recessed section 1121 and a second recessed section 1122 distributed along an axial direction away from the first portion 111 .

[0063] The radial dimension of the first recessed section 1121 is smaller than the radial dimension of the second recessed section 1122 .

[0064] The outer peripheral wall of the diaphragm 12 is connected to the inner peripheral wall of the first recessed section 1121 .

[0065] In this embodiment, the diaphragm 12 is disposed in the first recessed section 1121 closer to the first portion 111, and the size of the second recessed section 1122 is larger, so that the diaphragm 12 can be welded to the first recessed section 1121 through the second recessed section 1122. Moreover, the second recessed section 1122 can also adapt to the size of the joint connecting the turbo pump and the starter, so that the joint of the turbo pump blocks the second recessed section 1122 and abuts against the second recessed section 1122, and will not be squeezed into the first recessed section 1121, ensuring that the diaphragm 12 located in the first recessed section 1121 is not damaged by the joint, thereby improving the reliability of the diaphragm assembly 10.

[0066] Based on the same inventive concept, an embodiment of the present application also provides a starter for a rocket propulsion system, comprising: a starting combustion chamber, a nozzle 20 and any diaphragm assembly 10 provided in the aforementioned embodiment.

[0067] One end of the nozzle 20 is connected to the starting combustion chamber, and the nozzle opening 21 at the other end faces a direction away from the starting combustion chamber.

[0068] The diaphragm assembly 10 at least partially penetrates into the nozzle opening 21 in the axial direction and is sealingly connected to the nozzle opening 21 .

[0069] In this embodiment, since the starter of the rocket propulsion system adopts any one of the diaphragm assemblies 10 provided in the aforementioned embodiments, its principles and technical effects can be referred to in the aforementioned embodiments and will not be described in detail here.

[0070] In this embodiment, the mounting seat 11 is arranged at the nozzle mouth 21, and the diaphragm 12 is arranged in the recessed structure 1120 on one side of the mounting seat 11. The side of the mounting seat 11 facing the nozzle 20 has a hollow 1110, so that the high-pressure gas ejected from the nozzle 20 can break through the diaphragm 12 through the hollow 1110, and then be conducted into the turbo pump, thereby starting the turbo pump. The diaphragm assembly 10 provided in the present application at least partially penetrates into the nozzle mouth 21, and can be installed from the outside of the nozzle mouth 21 to the inside. Compared with the technical solution in the related art that the diaphragm 12 needs to be installed in the nozzle mouth 21 first, and then the nozzle 20 is installed at one end of the starter combustion chamber, the embodiment of the present application has no restriction on the installation order of the starter and the nozzle 20. After the starter is ignited, the mounting seat 11 can be removed from the nozzle 20 of the starter, so that the starter combustion chamber and the nozzle 20 of the starter can be reused.

[0071] In addition, unlike the technical solution in the related art that is limited by the small installation space in the nozzle 20 and can only use brazing to weld the diaphragm 12 to the nozzle 20, the diaphragm 12 and the mounting seat 11 can be assembled and welded before being installed in the nozzle mouth 21. The welding is less affected by the environment, and a welding method with higher reliability than brazing can be used before being installed in the nozzle 20. This can improve the connection reliability between the diaphragm 12 and the mounting seat 11, improve the working reliability of the starter, and facilitate the normal launch of the carrier rocket.

[0072] In some possible embodiments, the starter further includes a sealing ring 30 .

[0073] The sealing ring 30 is disposed around the first portion 111 of the partial diaphragm assembly 10 and is sealed to the nozzle opening 21 .

[0074] In this embodiment, the sealing ring 30 is disposed outside the first portion 111 of the partial diaphragm assembly 10 and is axially extruded between the second portion 112 and the nozzle 20, so that the space inside and outside the nozzle 20 is effectively isolated by the diaphragm assembly 10, thereby ensuring the normal operation of the starter.

[0075] Based on the same inventive concept, an embodiment of the present application also provides a rocket propulsion system, including: a turbopump and any starter provided in the aforementioned embodiments.

[0076] The turbo pump is connected to the other end of the nozzle 20 of the starter.

[0077] In this embodiment, since the rocket propulsion system adopts any one of the starters provided in the aforementioned embodiments, its principles and technical effects can be referred to in the aforementioned embodiments and will not be described in detail here.

[0078] In this embodiment, the mounting seat 11 is arranged at the nozzle mouth 21, and the diaphragm 12 is arranged in a recessed structure 1120 on one side of the mounting seat 11. The side of the mounting seat 11 facing the nozzle 20 has a hollow 1110, so that the high-pressure gas ejected from the nozzle 20 can break through the diaphragm 12 through the hollow 1110, and then be transmitted to the turbine pump, thereby starting the turbine pump.

[0079] The diaphragm assembly 10 can effectively isolate the turbo pump from the starting combustion chamber, which is equivalent to effectively isolating the starting combustion chamber from the engine combustion chamber, thereby ensuring that the diaphragm assembly 10 always remains in a normal state after the previous start and before this start, avoiding the starter from being ruptured by the impact of the high-temperature and high-pressure combustion gas generated by the previous start, thereby improving the working reliability of the starter.

[0080] Optionally, the rocket propulsion system includes a rocket engine.

[0081] By applying the embodiments of the present application, at least the following beneficial effects can be achieved: 1. In the embodiment of the present application, the mounting seat 11 is arranged at the nozzle mouth 21, and the diaphragm 12 is arranged in the recessed structure 1120 on one side of the mounting seat 11. The side of the mounting seat 11 facing the nozzle 20 has a hollow 1110, so that the high-pressure gas ejected from the nozzle 20 can break through the diaphragm 12 through the hollow 1110, and then be conducted into the turbo pump, thereby starting the turbo pump. The embodiment of the present application uses the mounting seat 11 to indirectly mount the diaphragm 12 on the nozzle mouth 21. Compared with the diaphragm 12, the mounting seat 11 has a higher thickness and strength, a higher connection reliability with the nozzle mouth 21, good sealing, and is easy to replace, which can improve the reusability and economy of the starter of the rocket power system.

[0082] 2. The diaphragm assembly 10 provided in the present application at least partially penetrates into the nozzle mouth 21 and can be installed from the outside of the nozzle mouth 21 to the inside. Compared with the technical solution in the related art that the diaphragm 12 needs to be installed in the nozzle mouth 21 first, and then the nozzle 20 is installed at one end of the starter combustion chamber, the embodiment of the present application has no restrictions on the installation sequence of the starter and the nozzle 20. After the starter is ignited, the mounting seat 11 can be removed from the nozzle 20 of the starter, so that the starter combustion chamber and the nozzle 20 of the starter can be reused.

[0083] 3. Different from the technical solution in the related art that the diaphragm 12 and the nozzle 20 can only be welded by brazing in the nozzle 20 due to the small installation space in the nozzle 20, the diaphragm 12 and the mounting seat 11 can be assembled and welded before being installed in the nozzle mouth 21. The welding is less affected by the environment. Before being installed in the nozzle 20, a welding method with higher reliability than brazing can be used, thereby improving the connection reliability between the diaphragm 12 and the mounting seat 11, improving the working reliability of the starter, and facilitating the normal launch of the carrier rocket.

[0084] 4. In the embodiment of the present application, the diaphragm 12 contacts or abuts against the first part 111, thereby minimizing the possibility of a gap between the diaphragm 12 and the first part 111. When subjected to the impact from the turbo pump (i.e., subjected to the impact force from outside the nozzle 20), the side of the diaphragm 12 facing the inside of the nozzle 20 can be supported by the first part 111, thereby minimizing the deformation of the diaphragm 12, thereby reducing the possibility of the diaphragm 12 being broken by the impact from the turbo pump.

[0085] 5. In the embodiment of the present application, the outer diameter of at least part of the second portion 112 is greater than the outer diameter of the first portion 111, so that a first step surface is formed between the outer peripheries of the first portion 111 and the second portion 112 of the mounting seat 11, and the inner wall at the nozzle mouth 21 also has a second step surface. When the mounting seat 11 is inserted into the nozzle mouth 21, the first step surface on the outer periphery of the mounting seat 11 abuts against the second step surface in the nozzle mouth 21, which can effectively prevent the mounting seat 11 from sliding into the nozzle 20.

[0086] In the description of the present application, the directions or positional relationships indicated by words such as "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the exemplary directions or positional relationships shown in the accompanying drawings. They are for the convenience of describing or simplifying the description of the embodiments of the present application, and do not indicate or imply that the referred device or component must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be understood as limitations on the present application.

[0087] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, unless otherwise specified, "plurality" means two or more.

[0088] In the description of this specification, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0089] The above is only a partial implementation method of the present application. It should be pointed out that for ordinary technicians in this technical field, without departing from the technical concept of the scheme of the present application, other similar implementation methods based on the technical ideas of the present application are also within the protection scope of the embodiments of the present application.

Claims

1. A diaphragm assembly, characterized in that: Starters for rocket propulsion systems, including: The mounting seat at least partially penetrates into the nozzle of the starter in the axial direction and is sealed and connected to the nozzle of the starter; the mounting seat comprises a first part and a second part distributed in the axial direction; the first part has a plurality of hollows in the axial direction; the second part has a concave structure with an opening facing away from the first part; A diaphragm, an outer peripheral wall of which is connected to an inner peripheral wall of the recessed structure; The hollow is connected between the space in the nozzle and the diaphragm.

2. The diaphragm assembly according to claim 1, characterized in that: One side of the diaphragm contacts or abuts against the first portion to seal the hollow.

3. The diaphragm assembly according to claim 1, characterized in that: An outer diameter of at least a portion of the second portion is larger than an outer diameter of the first portion.

4. The diaphragm assembly according to claim 1, characterized in that: Along the radial direction, the outermost hollow part, the peripheral wall of the recessed structure and the outer peripheral wall of the first part are successively away from the axial direction.

5. The diaphragm assembly according to claim 1, characterized in that: The diaphragm includes a plane portion and an edge portion connected to the periphery of the plane portion; The edge portion is flush with the plane portion facing the first portion. The edge portion extends in an axial direction away from the first portion and gradually becomes thicker in a radial direction away from the plane portion.

6. The diaphragm assembly according to claim 1, characterized in that: The first portion is recessed toward one side in the nozzle, and a center position of the first portion is recessed the deepest.

7. The diaphragm assembly according to claim 6, characterized in that: The membrane has a plurality of strip-shaped notches on one side away from the first portion; The midpoints of the plurality of notches intersect and are located at the center of the diaphragm; The center position of the first portion coincides with the midpoint where the plurality of notches intersect along the axial direction.

8. The diaphragm assembly according to claim 1, characterized in that: The recessed structure comprises a first recessed section and a second recessed section distributed along an axial direction away from the first portion; The radial dimension of the first recessed section is smaller than the radial dimension of the second recessed section; The outer peripheral wall of the diaphragm is connected to the inner peripheral wall of the first recessed section.

9. A starter for a rocket power system, characterized in that: include: A starting combustion chamber, a nozzle and a diaphragm assembly as claimed in any one of claims 1 to 8; One end of the nozzle is connected to the starting combustion chamber, and the nozzle opening at the other end faces away from the starting combustion chamber; The diaphragm assembly at least partially penetrates into the nozzle opening in the axial direction and is sealedly connected to the nozzle opening.

10. The starter according to claim 9, characterized in that Also includes: Sealing ring; The sealing ring is arranged outside a portion of the first portion of the diaphragm assembly and is sealed and connected to the nozzle opening.

11. A rocket propulsion system, characterized in that: include: A turbo pump and a starter as claimed in any one of claims 9 to 10; The turbo pump is connected to the other end of the nozzle of the starter.

Images