A diaphragm structure for a rocket engine combustion chamber and nozzle strong dynamic load test device

Abstract

The present invention discloses a diaphragm structure of a rocket engine combustion chamber and nozzle strong dynamic load test device, including a diaphragm; a steel wire rope, which is cross-distributed at a fixed rotation angle on the negative pressure side of the diaphragm; a shear, which is distributed around the edge of the negative pressure side of the diaphragm; a plurality of shallow grooves are arranged on the negative pressure side of the diaphragm, each shallow groove is cross-distributed at a fixed rotation angle, and the steel wire rope is distributed in the shallow groove. After the high-pressure nozzle reaches the set inflation pressure, the shear cuts the steel wire rope to release the load so that the air pressure breaks the diaphragm along the shallow groove. The present invention adopts a load sharing and load releasing method, by arranging steel wire ropes cross-distributed at a fixed rotation angle on the negative pressure side of the diaphragm, sharing the load on the bearing diaphragm, thereby increasing the bearing pressure limit of the diaphragm to break the membrane after reaching the precise gas state, and cooperating with the cutting of the steel wire rope to release the load to impact the diaphragm to break the membrane, so as to achieve precise control of the timing of membrane breaking and the timing matching of the strong dynamic load test, and improve the accuracy of the test results.

Description

Technical Field

[0001] The invention relates to the technical field of rocket engines, and in particular to a diaphragm structure of a rocket engine combustion chamber and a nozzle strong dynamic load test device. Background Art

[0002] The performance verification of the rocket engine combustion chamber and nozzle is extremely important, and the strong dynamic load test is one of the key links in the technology research and development process. The strong dynamic load test device of the rocket engine combustion chamber and nozzle is driven by high-pressure air and energetic medium. The high-pressure air provides the initial power, and the energy is further released through the combustion or explosion of the energetic medium. The collaborative work accurately simulates the strong dynamic load environment faced by the rocket engine during startup and actual operation, including extremely complex pressure, temperature, speed, etc.

[0003] In the rocket engine combustion chamber and nozzle high dynamic load test device, the instantaneous burst of energy will cause the magnitude and direction of the force to be highly uncertain and complex, and may come from impacts in multiple directions. The high dynamic load environmental test device is a pulse type equipment, which requires the use of a diaphragm to control the flow conditions. At present, the existing diaphragm structure usually adopts a single-layer or multi-layer membrane structure. During the membrane rupture process of this type of diaphragm structure, the membrane rupture pressure limit of the diaphragm will be affected by pressure fluctuations and have a wide range. It is difficult to accurately control the timing of membrane rupture, and thus it is difficult to match the timing of the high dynamic load test, affecting the experimental results.

[0004] Therefore, it is difficult to accurately control the membrane rupture time of the existing diaphragm structure because its ultimate bearing pressure is affected by pressure shock fluctuations, which makes it difficult to match the membrane rupture process with the timing of the strong dynamic load test. Summary of the invention

[0005] The object of the present invention is to provide a diaphragm structure for a rocket engine combustion chamber and nozzle strong dynamic load test device, so as to solve the technical problem in the prior art that the ultimate bearing pressure of the conventional diaphragm is affected by the pressure shock fluctuation and it is difficult to accurately control the membrane rupture time, thereby making it difficult to match the membrane rupture process with the timing of the strong dynamic load test.

[0006] In order to solve the above technical problems, the present invention specifically provides the following technical solutions:

[0007] A diaphragm structure for a rocket engine combustion chamber and nozzle strong dynamic load test device, comprising:

[0008] A diaphragm, arranged between the high-pressure nozzle and the combustion chamber of the test device, for providing pressure bearing;

[0009] Steel wire ropes are cross-distributed on the negative pressure side of the diaphragm at a fixed rotation angle to share the pressure load of the diaphragm;

[0010] A shear, distributed around the negative pressure side edge of the diaphragm, used for cutting the steel wire rope;

[0011] Wherein, a plurality of shallow grooves are arranged on the negative pressure side of the diaphragm, each of the shallow grooves is cross-distributed at a fixed rotation angle, the steel wire rope is distributed in the shallow groove, and after the high-pressure nozzle reaches the set inflation pressure, the shear cuts the steel wire rope to release the load so that the air pressure breaks the diaphragm along the shallow groove.

[0012] As a preferred solution of the present invention, the diaphragm is formed by punching a metal film to form a curved surface structure, the outer curved surface of the diaphragm is located on the negative pressure side, and the inner curved surface is located on the positive pressure side.

[0013] As a preferred solution of the present invention, the diaphragm includes a curved surface diaphragm and an annular diaphragm, and the curved surface diaphragm and the annular diaphragm are formed by punching the diaphragm;

[0014] The annular membrane is fixed between the high-pressure nozzle and the combustion chamber, the inner arc surface of the arc membrane faces the high-pressure nozzle, and the outer arc surface faces the combustion chamber;

[0015] Wherein, the shallow groove is formed on the outer curved surface of the curved surface film.

[0016] As a preferred solution of the present invention, a first flange and a second flange are respectively provided on both sides of the diaphragm, and holes are provided on the diaphragm to match the first flange and the second flange, and the first flange and the second flange are respectively connected to the high-pressure nozzle and the combustion chamber to fix the diaphragm between the high-pressure nozzle and the combustion chamber;

[0017] Wherein, the end of each steel wire rope and each shear are fixed on the inner wall of the second flange, and each steel wire rope passes through the shearing part of the corresponding shear.

[0018] As a preferred solution of the present invention, a slot is provided on the inner wall of the second flange, and a bayonet is provided at the end of the steel wire rope, and the bayonet is inserted into the slot and fixed to tighten the steel wire rope.

[0019] As a preferred solution of the present invention, the slot opening of the card slot faces the first flange, a first strip opening is provided through the inner wall of the card slot, and the first strip opening is connected to the slot opening;

[0020] Wherein, after the bayonet is inserted into the slot, the steel wire rope extends out of the slot through the first strip-shaped opening, and after the first flange and the second flange are connected, the bayonet is tightly fixed in the slot.

[0021] As a preferred solution of the present invention, a partition is provided in the card slot, the card slot is divided by the partition to form an inner chamber and an outer chamber, and the bayonet is installed in the outer chamber;

[0022] The partition plate is provided with a second strip-shaped opening, the second strip-shaped opening is aligned with the first strip-shaped opening, and the steel wire rope extends out of the slot through the first strip-shaped opening and the second strip-shaped opening;

[0023] The shearing part of the shears is located in the inner chamber, and a section of the steel wire rope located in the inner chamber passes through the shearing part of the shears.

[0024] As a preferred solution of the present invention, an annular groove is provided on the outside of the second flange, a plurality of assembly openings are provided on the groove wall of the annular groove, and each of the assembly openings is respectively connected to the inner chamber of each of the slots;

[0025] Each of the shears is circumferentially installed in the annular groove, and the shear is installed at the assembly opening to block the assembly opening and place its shearing portion in the inner chamber.

[0026] As a preferred solution of the present invention, the first flange and the second flange are both provided with pre-installed holes and connection holes, and the diaphragm is formed with holes matching the pre-installed holes;

[0027] The first flange and the second flange are respectively connected to the high-pressure nozzle and the combustion chamber through the connecting hole, and the first flange and the second flange pre-install and fix the diaphragm through the pre-installation hole.

[0028] As a preferred solution of the present invention, sealing gaskets are provided on both sides of the first flange and the second flange, and the sealing gaskets abutting the second flange and the diaphragm form a curved surface, and the curved surface is located at the inner wall edge of the sealing gasket and close to the negative pressure side of the diaphragm.

[0029] Compared with the prior art, the present invention has the following beneficial effects:

[0030] The present invention adopts a method of sharing and releasing loads. By arranging cross-distributed steel wire ropes with a fixed rotation angle on the negative pressure side of the diaphragm, the load on the load-bearing diaphragm is shared, thereby increasing the bearing pressure limit of the diaphragm so as to break the membrane after reaching a precise gas state. The load is released by cutting the steel wire rope to impact the diaphragm to break the membrane, thereby achieving precise control of the timing of membrane rupture and timing matching of the strong dynamic load test, thereby improving the accuracy of the test results. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the implementation methods of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for the implementation methods or the description of the prior art. Obviously, the drawings in the following description are only exemplary, and for ordinary technicians in this field, other implementation drawings can be derived from the provided drawings without creative work.

[0032] Figure 1 A schematic structural diagram of a diaphragm structure of a rocket engine combustion chamber and nozzle strong dynamic load test device provided by an embodiment of the present invention;

[0033] Figure 2 A schematic diagram of the distribution of steel wire ropes of a diaphragm structure of a rocket engine combustion chamber and nozzle strong dynamic load test device provided by an embodiment of the present invention;

[0034] Figure 3 A schematic diagram of the structure of the first flange and the second flange parts of the diaphragm structure of the rocket engine combustion chamber and nozzle strong dynamic load test device provided by an embodiment of the present invention;

[0035] Figure 4 A schematic diagram of the structure of the pre-installed holes and connection holes of the diaphragm structure of the rocket engine combustion chamber and nozzle strong dynamic load test device provided in an embodiment of the present invention.

[0036] The numbers in the figure represent the following:

[0037] 1- diaphragm; 2- steel wire rope; 3- shear; 4- first flange; 5- second flange; 6- pre-installed hole; 7- connection hole; 8- sealing gasket;

[0038] 11-annular membrane; 12-arc membrane; 21-pin; 51-slot; 52-spacer; 53-annular groove; 81-curved surface;

[0039] 121- shallow groove; 511- notch; 512- first strip-shaped opening; 513- inner chamber; 514- outer chamber; 515- second strip-shaped opening; 531- assembly opening. DETAILED DESCRIPTION

[0040] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0041] like Figure 1 , Figure 2As shown, the present invention provides a diaphragm structure of a rocket engine combustion chamber and nozzle strong dynamic load test device, comprising:

[0042] Diaphragm 1, arranged between the high-pressure nozzle and the combustion chamber of the test device, for providing pressure bearing;

[0043] The steel wire rope 2 is cross-distributed on the negative pressure side of the diaphragm 1 at a fixed rotation angle to share the pressure load of the diaphragm 1;

[0044] The shears 3 are distributed around the negative pressure side edge of the diaphragm 1 and are used to cut the steel wire rope 2;

[0045] Among them, a plurality of shallow grooves 121 are arranged on the negative pressure side of the diaphragm 1, and each shallow groove 121 is cross-distributed at a fixed rotation angle. The wire rope 2 is distributed in the shallow groove 121. After the high-pressure nozzle reaches the set inflation pressure, the shearer 3 cuts off the wire rope 2 to release the load so that the air pressure breaks the diaphragm 1 along the shallow groove 121.

[0046] The diaphragm structure of the present invention mainly utilizes the steel wire rope 2 to block the negative pressure side of the diaphragm 1, so that when the positive pressure side of the diaphragm 1 is pressurized, multiple steel wire ropes 2 can share the bearing load on the diaphragm 1, so that the diaphragm 1 can bear a larger pressure to ensure that the diaphragm 1 can be broken after the high-pressure nozzle reaches the set inflation pressure. The diaphragm is broken by cutting off the steel wire rope 2, which can suddenly release a large amount of load to the diaphragm 1, so that the diaphragm 1 is subjected to a pressure far greater than its bearing limit and breaks the membrane, that is, the membrane can be broken instantly after the steel wire rope 2 is cut off, so that the timing of membrane breaking can be accurately controlled. The diaphragm 1 has a shallow groove 121, so when the membrane is broken, the edge of the shallow groove 121 is more easily compressed and broken, thereby improving the membrane breaking speed, and the shallow grooves 121 are cross-distributed at a fixed rotation angle, so that the membrane breaking is more uniform.

[0047] Compared with the existing direct pressure rupture method, the diaphragm structure of the present invention improves the bearing capacity by sharing the load of the diaphragm 1 with the steel wire rope 2, so that after the steel wire rope 2 is cut off, the membrane can be quickly ruptured to achieve the purpose of accurately controlling the timing of rupture and rupture the membrane under precise gas state, and the direction of rupture of the diaphragm 1 is guided by arranging a shallow groove 121 on the diaphragm 1, so as to achieve rapid rupture of the membrane and directional and uniform rupture of the membrane, thereby improving the accuracy of the strong dynamic load test.

[0048] The use of this diaphragm structure achieves precise control, avoids test parameter deviations caused by inaccurate membrane rupture time, and ensures the reliability of test results. Therefore, whether it is a single pulse test or a complex multi-pulse, multi-stage strong dynamic load test, the diaphragm structure of the present invention can meet the strict requirements of the test on the membrane rupture time and membrane rupture process.

[0049] The diaphragm structure of the present invention has significantly improved its bearing capacity. The design of the shallow groove 121 adjusts the stress state of the diaphragm 1 to a certain extent, and the steel wire rope 2 shares the pressure at the critical stage. This enables the diaphragm to withstand higher pressure and meet the requirements under extreme pressure conditions in strong dynamic load environmental tests. Therefore, under the same test conditions, the diaphragm structure of the present invention can withstand greater pressure peaks and longer continuous pressure, effectively reducing the risk of premature rupture of the diaphragm during the test.

[0050] And because the membrane breaking process is associated with the shearing or cutting operation of the steel wire rope 2, and can be precisely controlled in time by the test control system, the membrane structure of the present invention can better match the operating time of the entire strong dynamic load environment test device. During the test, the membrane breaking time can be precisely synchronized with other key test links (such as impact loading time, energy release time, etc.) according to the preset timing parameters. This optimization of timing control is of great significance for realizing complex test designs and improving the accuracy of test results, so that the test can more realistically simulate the actual strong dynamic load scenario.

[0051] Of course, the steel wire ropes 2 can be cut one by one or at the same time. After cutting, the load on the steel wire ropes decreases, the load on the diaphragm increases, and the diaphragm gradually bulges toward the side with low pressure and finally breaks, so that a more complex directional rupture test can be carried out to obtain more comprehensive strong dynamic load test data.

[0052] Based on the above embodiments, in order to optimize the pressure distribution of the diaphragm 1 , the following preferred embodiments are provided.

[0053] like Figure 1 As shown, the diaphragm 1 is formed by punching a metal film to form a curved surface structure, the outer curved surface of the diaphragm 1 is located on the negative pressure side, and the inner curved surface is located on the positive pressure side.

[0054] The diaphragm 1 adopts a curved surface structure, and the pressure will be dispersed along the tangent direction and normal direction of the curved surface, so that the pressure per unit area is relatively reduced, so that the air pressure on the surface of the diaphragm 1 can be more evenly distributed, and when the air pressure increases, the curved surface will produce a slight elastic deformation. This deformation will redistribute the stress inside the structure to adapt to the change in air pressure, and it is not easy to be ruptured prematurely due to pressure fluctuations.

[0055] Specifically, Figure 1 , Figure 2 As shown, the diaphragm 1 includes a curved surface diaphragm 12 and an annular diaphragm 11, and the curved surface diaphragm 12 and the annular diaphragm 11 are formed by stamping the diaphragm 1;

[0056] The annular membrane 11 is fixed between the high-pressure nozzle and the combustion chamber, the inner arc surface of the arc membrane 12 faces the high-pressure nozzle, and the outer arc surface faces the combustion chamber;

[0057] The shallow groove 121 is formed on the outer curved surface of the curved film 12 .

[0058] The diaphragm 1 of this embodiment is composed of a curved membrane 12 and an annular membrane 11. The curved membrane 12 is used to bear pressure, and the annular membrane 11 is convenient for fixing, so that the diaphragm 1 can be stably installed between the high-pressure nozzle and the combustion chamber. In order to make the installation of the diaphragm 1 more convenient, the following preferred embodiments are provided.

[0059] like Figure 1 As shown, a first flange 4 and a second flange 5 are respectively provided on both sides of the diaphragm 1, and holes are provided on the diaphragm 1 to match the first flange 4 and the second flange 5. The first flange 4 and the second flange 5 are respectively connected to the high-pressure nozzle and the combustion chamber to fix the diaphragm 1 between the high-pressure nozzle and the combustion chamber;

[0060] The end of each steel wire rope 2 and each shear 3 are fixed on the inner wall of the second flange 5 , and each steel wire rope 2 passes through the shearing portion of the corresponding shear 3 .

[0061] In this embodiment, the two sides of the diaphragm 1 are clamped and fixed by the first flange 4 and the second flange 5, that is, the first flange 4 and the second flange 5 are clamped and fixed on the annular diaphragm 11, and the end of the wire rope 2 and the shearer 3 are fixed on the inner wall of the second flange 5 (negative pressure side), that is, the second flange 5 and the shearer 3 can be pre-assembled, making installation more convenient.

[0062] Of course, in order to make it more convenient to fix the steel wire rope 2 on the second flange 5, the following preferred embodiments are provided.

[0063] like Figure 1 , Figure 3 As shown, a slot 51 is provided on the inner wall of the second flange 5 , and a pin 21 is provided at the end of the steel wire rope 2 . The pin 21 is inserted into the slot 51 and fixed to tighten the steel wire rope 2 .

[0064] In this embodiment, the connection and fixing method between the steel wire rope 2 and the second flange 5 is to adopt the method of clamping the clamping slot 51 and the clamping pin 21, which is easy to operate and firmly fixed. Of course, in order to make the connection between the clamping slot 51 and the clamping pin 21 more firmly, the following preferred embodiments are provided.

[0065] like Figure 3 As shown, the slot 511 of the slot 51 faces the first flange 4, and a first strip-shaped opening 512 is provided through the inner wall of the slot 51, and the first strip-shaped opening 512 is connected to the slot 511;

[0066] After the bayonet 21 is inserted into the slot 51 , the steel wire rope 2 extends out of the slot 51 through the first strip opening 512 , and after the first flange 4 and the second flange 5 are connected, the bayonet 21 is tightly fixed in the slot 51 .

[0067] In this embodiment, the notch 511 of the slot 51 is set toward the first flange 4. After the first flange 4 and the second flange 5 are abutted, the pin 21 can be fixed in the slot 51. When the wire rope 2 is subjected to force, the slot 51 can withstand a larger radial tension, thereby effectively preventing the pin 21 from detaching during the strong dynamic load test.

[0068] Of course, in order to prevent the shear 3 from affecting the test during the membrane rupture test, the following preferred embodiments are provided.

[0069] like Figure 3 As shown, a partition 52 is provided in the card slot 51, and the card slot 51 is divided by the partition 52 to form an inner chamber 513 and an outer chamber 514, and the card pin 21 is installed in the outer chamber 514;

[0070] A second strip opening 515 is provided on the partition plate 52, the second strip opening 515 is aligned with the first strip opening 512, and the steel wire rope 2 extends out of the slot 51 through the first strip opening 512 and the second strip opening 515;

[0071] The cutting portion of the shears 3 is located in the inner chamber 513 , and a section of the steel wire rope 2 located in the inner chamber 513 passes through the cutting portion of the shears 3 .

[0072] In this embodiment, the partition plate 52 is used to divide the card slot 51 into an inner chamber 513 and an outer chamber 514, so that the card pin 22 is fixed in the outer chamber 514, so that after the wire rope 2 passes through the first strip opening 512 and the second strip opening 515, part of it is placed in the inner chamber 513, and the cutting part of the shearer 3 is located in the inner chamber 513, so that the wire rope 2 can be cut in the inner chamber 513, and the shearer 3 is hidden, so as to prevent the shearer 3 from affecting the airflow on the inner wall of the second flange 5 or being damaged by the impact of the high-pressure airflow.

[0073] The shearer 3 needs to be controlled by the control system of the test, and therefore needs to be electrically connected to the outside. In order to prevent the wiring from being exposed to the high-pressure environment between the high-pressure nozzle and the combustion chamber, the following preferred embodiments are provided.

[0074] like Figure 3 As shown, an annular groove 53 is provided on the outside of the second flange 5, and a plurality of assembly openings 531 are provided on the groove wall of the annular groove 53, and each assembly opening 531 is connected to the inner chamber 513 of each slot 51 respectively;

[0075] Each shear 3 is installed in the annular groove 53 in an circumferential manner, and the shear 3 is installed at the assembly opening 531 to block the assembly opening 531 and place its shearing portion in the inner chamber 513 .

[0076] In this embodiment, an annular groove 53 is provided on the outside of the second flange 5, so that the shear 3 can be installed in the annular groove 53, that is, the control end of the shear 3 is located outside, which is convenient for wiring control;

[0077] The groove wall of the annular groove 53 is provided with a plurality of assembly openings 531, and the shearing portion of the shear 3 can extend into the interior of the inner chamber 513 through the assembly openings 531. Thus, after the shear 3 is installed to seal the assembly openings 531, the shearing portion works in the inner chamber 513, which is convenient for wiring control and does not expose the wires to a high-voltage environment.

[0078] Of course, since the diaphragm 1 is relatively thin, it is necessary to be careful about damage during the installation process. Therefore, in order to facilitate the installation of the diaphragm 1, the following preferred embodiments are provided.

[0079] like Figure 4 As shown, the first flange 4 and the second flange 5 are both provided with pre-installed holes 6 and connecting holes 7, and the diaphragm 1 is formed with holes matching the pre-installed holes 6;

[0080] The first flange 4 and the second flange 5 are respectively connected to the high-pressure nozzle and the combustion chamber through the connecting hole 7 , and the first flange 4 and the second flange 5 pre-install and fix the diaphragm 1 through the pre-installation hole 6 .

[0081] In this embodiment, the first flange 4 and the second flange 5 have two hole positions, namely a pre-installed hole 6 and a connecting hole 7, and the diaphragm 1 can be fixed between the first flange 4 and the second flange 5 through the pre-installed hole 6. Of course, at this time, the bayonet 21 is placed in the slot 51 to fix the wire rope 2 between the first flange 4 and the second flange 5, thereby forming a complete diaphragm structure. This diaphragm structure can be pre-assembled into a whole and then installed between the high-pressure nozzle and the combustion chamber through the connecting hole 7, so that the installation is more convenient and the diaphragm 1 is not easily damaged.

[0082] Of course, in order to prevent leakage after the diaphragm 1 is installed between the first flange 4 and the second flange 5 and affect the gas control accuracy, the following preferred embodiments are provided.

[0083] like Figure 1 As shown, sealing gaskets 8 are provided on both sides of the first flange 4 and the second flange 5 , and the sealing gasket 8 abutting the second flange 5 and the diaphragm 1 forms a curved surface 81 , and the curved surface 81 is located at the inner wall edge of the sealing gasket 8 and close to the negative pressure side of the diaphragm 1 .

[0084] In this embodiment, a sealing gasket 8 is distributed on both sides of the first flange 4 and the second flange 5 to improve the sealing performance of the connection, and the inner ring edge of one side of the sealing gasket 8 abutting the second flange 5 is a curved surface 81, so that the diaphragm 1 with a curved surface structure and the deformed edge of the diaphragm 1 can fit on the curved surface 81, thereby preventing the diaphragm 1 from being squeezed and ruptured prematurely due to the small angle of the inner ring edge of the sealing gasket 8.

[0085] The above embodiments are only exemplary embodiments of the present application and are not intended to limit the present application. The protection scope of the present application is defined by the claims. Those skilled in the art may make various modifications or equivalent substitutions to the present application within the essence and protection scope of the present application, and such modifications or equivalent substitutions shall also be deemed to fall within the protection scope of the present application.

Claims

1. A diaphragm structure for a rocket engine combustion chamber and nozzle strong dynamic load test device, characterized in that: include: A diaphragm (1) is arranged between the high-pressure nozzle and the combustion chamber of the test device and is used to provide pressure bearing; The steel wire ropes (2) are cross-distributed on the negative pressure side of the diaphragm (1) at a fixed rotation angle to share the pressure load of the diaphragm (1); A shear (3) is distributed around the negative pressure side edge of the diaphragm (1) and is used to cut the steel wire rope (2); Wherein, a plurality of shallow grooves (121) are arranged on the negative pressure side of the diaphragm (1), each of the shallow grooves (121) being cross-distributed at a fixed rotation angle, the steel wire rope (2) being distributed in the shallow grooves (121), and after the high-pressure nozzle reaches a set inflation pressure, the shear (3) cuts the steel wire rope (2) to release the load so that the air pressure breaks the diaphragm (1) along the shallow grooves (121); The diaphragm (1) is formed into a curved surface structure by punching a metal film, the outer curved surface of the diaphragm (1) is located on the negative pressure side, and the inner curved surface is located on the positive pressure side; The diaphragm (1) comprises a curved surface diaphragm (12) and an annular diaphragm (11), wherein the curved surface diaphragm (12) and the annular diaphragm (11) are formed by punching the diaphragm (1); The annular membrane (11) is fixed between the high-pressure nozzle and the combustion chamber, the inner arc surface of the arc membrane (12) faces the high-pressure nozzle, and the outer arc surface faces the combustion chamber; Wherein, the shallow groove (121) is formed on the outer curved surface of the curved surface membrane (12).

2. The diaphragm structure of a rocket engine combustion chamber and nozzle strong dynamic load test device according to claim 1, characterized in that: A first flange (4) and a second flange (5) are respectively arranged on both sides of the diaphragm (1); the diaphragm (1) has holes for matching the first flange (4) and the second flange (5); the first flange (4) and the second flange (5) are respectively connected to the high-pressure nozzle and the combustion chamber, so as to fix the diaphragm (1) between the high-pressure nozzle and the combustion chamber; The ends of each steel wire rope (2) and each shear (3) are fixed on the inner wall of the second flange (5), and each steel wire rope (2) passes through the shearing portion of the corresponding shear (3).

3. The diaphragm structure of a rocket engine combustion chamber and nozzle strong dynamic load test device according to claim 2, characterized in that: A clamping groove (51) is provided on the inner wall of the second flange (5), and a clamping pin (21) is provided at the end of the steel wire rope (2); the clamping pin (21) is inserted into the clamping groove (51) and fixed therein, so as to tighten the steel wire rope (2).

4. The diaphragm structure of a rocket engine combustion chamber and nozzle strong dynamic load test device according to claim 3, characterized in that: The slot opening (511) of the clamping slot (51) faces the first flange (4), a first strip opening (512) is provided through the inner wall of the slot (51), and the first strip opening (512) is connected to the slot opening (511); Wherein, after the bayonet (21) is inserted into the slot (51), the steel wire rope (2) extends out of the slot (51) through the first strip-shaped opening (512), and after the first flange (4) and the second flange (5) are connected, the bayonet (21) is tightly fixed in the slot (51).

5. The diaphragm structure of a rocket engine combustion chamber and nozzle strong dynamic load test device according to claim 4, characterized in that: A partition (52) is provided in the card slot (51), the card slot (51) is divided by the partition (52) into an inner chamber (513) and an outer chamber (514), and the card pin (21) is installed in the outer chamber (514); The partition plate (52) is provided with a second strip-shaped opening (515), the second strip-shaped opening (515) is aligned with the first strip-shaped opening (512), and the steel wire rope (2) extends out of the slot (51) through the first strip-shaped opening (512) and the second strip-shaped opening (515); The shearing portion of the shear (3) is located in the inner chamber (513), and a section of the steel wire rope (2) located in the inner chamber (513) passes through the shearing portion of the shear (3).

6. The diaphragm structure of a rocket engine combustion chamber and nozzle strong dynamic load test device according to claim 5, characterized in that: An annular groove (53) is provided on the outside of the second flange (5), a plurality of assembly openings (531) are provided on the groove wall of the annular groove (53), and each of the assembly openings (531) is respectively connected to the inner chamber (513) of each of the clamping grooves (51); Each of the shears (3) is mounted in a circumferential manner in the annular groove (53), and the shears (3) are mounted at the assembly opening (531) to block the assembly opening (531) and place the shearing portion thereof in the inner chamber (513).

7. The diaphragm structure of a rocket engine combustion chamber and nozzle strong dynamic load test device according to claim 2, characterized in that: The first flange (4) and the second flange (5) are both provided with a pre-installed hole (6) and a connection hole (7), and the diaphragm (1) is formed with a hole position matching the pre-installed hole (6); The first flange (4) and the second flange (5) are respectively connected to the high-pressure nozzle and the combustion chamber through the connecting hole (7), and the first flange (4) and the second flange (5) pre-install and fix the diaphragm (1) through the pre-installation hole (6).

8. The diaphragm structure of a rocket engine combustion chamber and nozzle strong dynamic load test device according to claim 7, characterized in that: Sealing gaskets (8) are provided on both sides of the first flange (4) and the second flange (5); the sealing gasket (8) abutting against the second flange (5) and the diaphragm (1) forms a curved surface (81); and the curved surface (81) is located at the inner wall edge of the sealing gasket (8) and close to the negative pressure side of the diaphragm (1).

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