CN112324592B - Solid rocket engine simulated combustion test equipment shell structure - Google Patents

Abstract

The application discloses a shell structure of a solid rocket engine simulated combustion test device, which relates to the technical field of solid rocket engines and is used for simulating the combustion of a propellant to be tested in the solid rocket engine; the test apparatus comprises: a cylindrical housing having a flange provided on the top peripheral side thereof; a top cover which covers the shell; the clamping mechanism comprises two clamping parts and at least two driving parts; the two clamping parts are oppositely arranged, and a groove is formed in the inner wall of each clamping part; the two driving parts are arranged on two sides of the shell and are respectively connected with one clamping part for driving the corresponding clamping parts to reciprocate linearly along the radial direction of the shell; meanwhile, when the two clamping parts are in butt joint, the two grooves form an annular groove, and the annular groove is clamped outside the edges of the flange and the top cover. The application meets the airtight connection capability of the shell when the propellant burns, ensures the stability of the propellant burning, is easy to open and close the top cover and the shell, and improves the efficiency of the simulated burning test.

Description

Solid rocket engine simulated combustion test equipment shell structure

Technical Field

The application relates to the technical field of solid rocket engines, in particular to a shell structure of a solid rocket engine simulated combustion test device.

Background

The large solid rocket engine is widely applied to a booster for transporting heavy carrier rockets on the aerospace because of the characteristics of large thrust, simple structure and high reliability. In the research and development process of a large solid rocket engine, the combustion performance of the propellant is often required to be measured by combusting the propellant for multiple times in the large solid rocket engine, however, in actual situations, the combustion of the propellant is often performed in a full-size solid rocket engine, the test cost is high, and the whole test period is long, so that the research and development process is slow.

In the combustion process of the propellant, a large amount of high-temperature high-pressure gas is generated by the combustion of the propellant and is sprayed outwards at a high speed, if the connection capability of the shell provided with the propellant is insufficient, the shell is easily damaged and unstable in combustion, and the connection of the shell parts provided with the propellant is required to have a relatively airtight connection capability.

Disclosure of Invention

The embodiment of the application provides a shell structure of a solid rocket engine simulated combustion test device, which aims to solve the problem that in the related art, the shell is unstable in combustion due to the fact that a large amount of high-pressure gas is generated by outward high-speed injection when a propellant is combusted due to insufficient connecting capacity of the shell.

The embodiment of the application provides a shell structure of a solid rocket engine simulated combustion test device, which is used for simulating combustion of a propellant to be tested in the solid rocket engine; the test apparatus comprises:

a cylindrical housing having a flange provided on the top peripheral side thereof;

a top cover which covers the shell;

the clamping mechanism comprises two clamping parts and at least two driving parts; the two clamping parts are oppositely arranged, and a groove is formed in the inner wall of each clamping part; the two driving parts are arranged on two sides of the shell and are respectively connected with one clamping part, and the driving parts are used for driving the corresponding clamping parts to reciprocate linearly along the radial direction of the shell; meanwhile, when the two clamping parts are in butt joint, the two grooves form an annular groove, and the annular groove is clamped outside the edges of the flange and the top cover.

In some embodiments, the end surface of the shell is in sealing connection with the top cover through a first sealing ring;

the top cover extends downwards, a part extending downwards extends into the shell, and the part is in sealing connection with the shell through a second sealing ring.

In some embodiments, the engaging portion has a semicircular structure.

In some embodiments, further comprising:

the operation platform is fixedly arranged on the periphery of the shell, and the driving parts symmetrically distributed relative to the shell are arranged on the operation platform.

In some embodiments, the number of the driving parts is four, and two ends of each clamping part are connected with one driving part.

In some embodiments, the driving part includes a driving oil cylinder, two supports are disposed on the bottom side of each clamping part, and four reaction seats are disposed on the operation platform; the four driving oil cylinders are correspondingly arranged on the counter-force seats and connected with the corresponding supports so as to drive the two clamping parts to be close to or far away from each other along the radial direction of the shell.

In some embodiments, a running wheel is connected to the bottom of the engaging portion, and a track on which the running wheel can run is provided on the operation platform.

In some embodiments, the two engaging portions are connected by a flange.

In some embodiments, the top cover is a flat cover.

In some embodiments, the housing further comprises a bottom cover, the bottom cover being a downwardly convex curved cover.

The technical scheme provided by the application has the beneficial effects that: the airtight connection capability of the shell during propellant combustion is met, the stability of propellant combustion is ensured, the top cover and the shell are easy to open and close, and the efficiency of a simulated combustion test is improved.

The embodiment of the application provides a shell structure of a solid rocket engine simulated combustion test device, which is connected with a top cover through a clamping mechanism, wherein the clamping mechanism comprises clamping parts and driving parts, the driving parts arranged on two sides of the shell respectively drive the corresponding clamping parts to reciprocate linearly along the radial direction of the shell, the two clamping parts are mutually close until being abutted and clamped on the shell and the top cover, the two clamping parts are mutually far away so as to remove the limitation on the shell and the top cover, and the top cover is convenient to detach to replace different propellants to be tested. Meanwhile, in the multiple combustion test, the shell and the top cover are connected by the clamping mechanism, so that the airtight connection capability of the shell in the process of combusting the propellant can be met, the combustion stability of the propellant is ensured, the top cover and the shell are easy to open and close, and the efficiency of the simulated combustion test is improved.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present application, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

Fig. 1 is a perspective view of a shell structure of a solid rocket engine simulated combustion test device according to an embodiment of the present application when two engaging parts are in butt joint;

fig. 2 is a perspective view of a shell structure of a solid rocket engine simulated combustion test device according to an embodiment of the present application when two engaging portions are separated;

FIG. 3 is a full sectional view of a solid rocket engine simulated combustion test device housing structure provided by an embodiment of the present application;

FIG. 4 is a full cross-sectional view of the propellant removed of FIG. 3;

FIG. 5 is a schematic diagram of a pressure relief device in full section;

FIG. 6 is an elevation view of a solid rocket engine simulated combustion test device housing structure according to an embodiment of the present application when two engagement portions are separated;

fig. 7 is a top view of a shell structure of a solid rocket engine simulated combustion test device according to an embodiment of the present application when two engaging parts are in butt joint;

FIG. 8 is a schematic partial cross-sectional view of the junction of the housing, the cover, and the engagement portion according to an embodiment of the present application;

FIG. 9 is a schematic cross-sectional view of a fill structure;

FIG. 10 is a partial perspective view of a propellant and filling structure in a housing according to an embodiment of the present application;

FIG. 11 is a cross-sectional view of a solid rocket engine simulated combustion test device housing structure according to an embodiment of the present application;

FIG. 12 is a perspective view of a solid rocket engine simulated combustion test device shell structure after being cut in half, provided by an embodiment of the application;

FIG. 13 is a schematic view of a first thermal insulation layer;

FIG. 14 is a schematic view of a longitudinal section of a solid rocket engine simulated combustion test device provided by an embodiment of the application, wherein the chord tangent line of the shell structure is perpendicular to the radius of the shell and passes through a pressure relief device and a spray pipe;

FIG. 15 is a schematic view of the distribution of the top cover and the second thermal insulation layer thereon;

FIG. 16 is a schematic illustration of a fourth insulation layer distributed over the propellant;

in the figure: 1. a housing; 10. a combustion chamber; 11. a flange; 12. a first seal ring; 13. a second seal ring; 14. a bottom cover; 2. a top cover; 21. lifting holes; 31. filling the structure; 311. arc sides; 312. a special-shaped side; 32. an ignition device; 33. a propellant; 34. a spray pipe; 41. an engagement portion; 410. a groove; 42. a driving section; 43. a support; 44. a running wheel; 5. an operating platform; 51. a counterforce seat; 52. a track; 6. a pressure relief device; 60. a pressure measuring hole; 61. rupture disk; 62. an adapter; 63. capping; 64. an upper clamping ring; 65. a lower clamp ring; 66. a bolt; 71. a first insulating layer; 710. a heat insulating unit sheet; 711. a fire surface heat insulating layer; 712. adjacent fire surface heat insulation layer; 713. a propellant side insulating layer; 714. a propellant backside insulation layer; 72. a second heat insulating layer; 721. a step heat insulating portion; 722. a filling portion; 73. a third heat insulating layer; 74. a fourth heat insulating layer; 740. a flow-limiting strip; 75. and the pressure relief heat insulation layer.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present application more apparent, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application, and it is apparent that the described embodiments are some embodiments of the present application, but not all embodiments of the present application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.

The embodiment of the application provides a shell structure of a solid rocket engine simulated combustion test device, which is used for simulating combustion of a propellant 33 to be tested in the solid rocket engine; the test equipment comprises a shell 1 and a top cover 2, wherein the top cover 2 is arranged on the shell 1 in a covering mode.

Example 1:

as shown in fig. 1 to 4, the test equipment further comprises a filling structure 31, an ignition device 32, a spray pipe 34, a pressure relief device 6 and a pressure measurement sensor; the filling structure 31 is arranged on the inner wall of the shell 1 in a fitting way, and forms a combustion chamber 10 with the shell 1 for the propellant 33 to burn; the ignition device 32 is arranged on the shell 1 and positioned at the bottom of the combustion chamber 10, and is used for receiving an ignition instruction and igniting a propellant 33 to be tested in the combustion chamber 10; the spray pipe 34 is installed on the top cover 2 and communicated with the combustion chamber 10 so as to spray high-temperature and high-pressure gas generated by the propellant 33 during combustion upwards; the pressure relief device 6 is mounted on the top cover 2 and communicated with the combustion chamber 10, so that when the high-heat high-pressure gas generated by the propellant 33 of the combustion chamber 10 is over-pressurized, the high-heat high-pressure gas is released from the pressure relief device 6, the working pressure in the combustion chamber 10 is reduced, and the combustion stability is ensured;

the pressure measuring sensor is installed on the pressure measuring hole 60 of the pressure relief device 6, and collects working pressure of the combustion chamber 10 when the propellant 33 burns in the combustion chamber 10, and a worker determines the actual combustion performance of the corresponding propellant 33 according to the actual combustion time of the propellant 33 and the collected actual working pressure when burning, so as to provide design reference.

During the combustion process of the propellant 33 in the combustion chamber 10, the shell 1 is vertically arranged, the opening of the spray pipe 34 is vertically upwards, the ignition device 32 receives an ignition command and ignites the propellant 33 in the combustion chamber 10, high-temperature and high-pressure gas is generated and sprayed upwards by the spray pipe 34, the propellant 33 is stably combusted in the combustion chamber 10, the pressure measuring sensor collects the working pressure in the combustion chamber 10, and the combustion time and the average working pressure of the propellant 33 are determined according to the collected working pressure.

Further, the design basis of the throat diameter of the spray pipe 34 is to ensure that the combustion time and the average working pressure of the propellant 33 in the test equipment are equivalent to those of a full-size solid rocket engine to be simulated, namely, the working state of the formal solid rocket engine is simulated.

In the embodiment of the present application, through the calculation of the zero-dimensional inner trajectory, when the throat diameter of the nozzle 34 is 180mm, the calculation results of the combustion time and the average working pressure are shown in table 1.

Table 1 results of calculation of combustion performance of solid rocket engine and test equipment

	Solid rocket engine	Test equipment
			Combustion time s	95.2±2	96
Average working pressure MPa	7.53±0.2	7.6

According to the experimental equipment provided by the embodiment of the application, the charging area of a formal solid rocket engine is simulated in a ratio of 1:1, so that the combustion process of the propellant 33 in the solid rocket engine can be truly simulated, multiple combustion tests are performed, and the test cost is reduced.

As shown in fig. 5, the pressure relief device 6 further includes a rupture disk 61, an adapter 62, and a cap 63; the side wall of the adapter seat 62 is provided with a pressure measuring hole 60 and is arranged on the top cover 2; the cover 63 is detachably arranged above the adapter seat 62; the adapter seat 62 and the cap 63 are annular; the rupture disk 61 is clamped between the adapter seat 62 and the cap 63, and blocks communication between the adapter seat 62 and the cap 63.

In the embodiment of the present application, the cap 63 is detachably connected to the adapter 62, so that the replacement of the rupture disk 61 is facilitated when the rupture disk 61 is exploded. When the operating pressure of the combustion chamber 10 exceeds a preset warning pressure, the rupture disk 61 breaks down to reduce the pressure within the combustion chamber 10.

Further, the rupture disk 61 protrudes outwardly. The protruding direction of the rupture disk 61 is the same as the direction of the high-temperature and high-pressure gas generated.

More specifically, the rupture disk 61 is made of steel, and a cross-shaped weakening groove is concavely formed in the upper surface of the rupture disk 61, and the thickness of the rupture disk 61 and the depth of the weakening groove are determined according to the warning pressure so as to adjust the bursting pressure of the rupture disk 61.

Still further, the pressure relief device 6 further includes:

a clamping mechanism comprising an upper clamping ring 64 and a lower clamping ring 65, the rupture disk 61 being clamped between the upper clamping ring 64 and the lower clamping ring 65; the top of the upper clamping ring 64 is abutted with the cap 63, and the bottom of the lower clamping ring 65 is abutted with the adapter seat 62. In the embodiment of the present application, the rupture disk 61 is clamped by a clamping mechanism, so as to compress the rupture disk 61.

Further, the cap 63 is detachably connected to the adaptor 62 by a plurality of bolts 66, and all the bolts 66 are looped outside the clamping mechanism. The bolts 66 are arranged around the edges of the adapter seat 62 and the cap 63, so that the rupture disk 61 can be more firmly clamped, and the connection capability of the pressure relief device 6 is improved.

Specifically, the connection portion between the upper clamp ring 64 and the lower clamp ring 65 is stepped. I.e., the portion of the lower clamp ring 65 near the outside extends upward and the portion of the upper clamp ring 64 near the inside extends downward. The stepped connection surfaces in the clamping mechanism enable the placement of rupture discs 61 of different thickness and ensure compression of the rupture discs 61.

Example 2:

as shown in fig. 1 to 4 and 6 to 7, the housing 1 has a cylindrical shape, and a flange 11 is provided on the top peripheral side thereof, and the test apparatus further includes:

a holding mechanism including two engaging portions 41 and at least two driving portions 42; the two engaging portions 41 are disposed opposite to each other, and a groove 410 is formed on an inner wall of the engaging portion 41; the two driving parts 42 are arranged at two sides of the shell 1 and are respectively connected with one clamping part 41 for driving the corresponding clamping part 41 to reciprocate linearly along the radial direction of the shell 1; meanwhile, when the two engaging portions 41 are abutted, the two grooves 410 form an annular groove, and the annular groove is caught outside the edges of the flange 11 and the top cover 2.

The embodiment of the application provides a shell structure of solid rocket engine simulated combustion test equipment, which has the working principle that:

after the propellant 33 in the housing 1 is installed, the top cover 2 is placed on the housing 1;

the two driving portions 42 are controlled to respectively drive the corresponding engaging portions 41 to linearly move inwards along the radial direction of the housing 1, the two engaging portions 41 are close to each other until the end portions of the two engaging portions 41 are aligned, at this time, the grooves 410 on the engaging portions 41 together form an annular groove, and the flange 11 on the housing 1 and the edge of the top cover 2 are located in the annular groove and are abutted against the annular groove.

When the next propellant is replaced after the last propellant simulated combustion test is finished, the top cover 2 is required to be opened, the two driving parts 42 are controlled to drive the corresponding clamping parts 41 to move outwards along the radial direction of the shell 1, the two clamping parts 41 are away from each other until the two clamping parts 41 are separated from the shell 1 and the top cover 2, the clamping parts 41 release the limitation on the shell 1 and the top cover 2, and then the top cover 2 is opened.

When the propellant 33 burns in the combustion chamber 10, a large amount of high-heat and high-pressure gas is generated and is ejected upward, the top cover 2 is subjected to a large upward impact force, and when the connection capability between the top cover 2 and the housing 1 is small, the top cover 2 may be separated from the housing 1 by the impact force, which may result in the propellant 33 not being able to burn stably in the combustion chamber 10, therefore, in the embodiment of the present application, a holding mechanism is added, which includes a holding portion 41 and a driving portion 42, the flange 11 of the housing 1, the edge of the top cover 2 are held by grooves on the inner wall of the holding portion 41, and the driving portion 42 is used to open and close the two holding portions 41 as needed.

Further, the engaging portion 41 has a semicircular structure. The engaging portions 41 of the two semicircular ring structures can be held close to each other to clamp the housing 1 and the top cover 2.

Specifically, the two engaging portions 41 are connected by a flange. The connection of the two engaging portions 41 of the flange connection is more reliable and stable.

Further, the test apparatus further comprises:

an operation platform 5 fixedly arranged on the periphery side of the shell 1, wherein the operation platform 5 is provided with driving parts 42 symmetrically distributed with respect to the shell 1.

In the embodiment of the present application, the outer side of the housing 1 is cylindrical, and the driving portion 42 is mounted thereon, which may complicate the composition structure of the driving portion, so that the operating platform is disposed on the outer periphery of the housing 1, and a single driving cylinder can be directly used as the driving portion to control the linear movement of one engagement portion.

Specifically, the number of the driving parts 42 is four, and two ends of each engaging part 41 are connected to one driving part 42. In the embodiment of the present application, since the object to be driven by the driving portion 42 is the engaging portion 41 that matches the case 1 to which the propellant 33 is attached, a large driving force is required. One driving portion 42 is connected to both ends of the engaging portion 41 having a semicircular structure, and both driving portions 42 are synchronously controlled to stably move the engaging portion 41.

Specifically, the driving portion 42 includes a driving cylinder, two supporting seats 43 are disposed on the bottom side of each engaging portion 41, and four reaction seats 51 are disposed on the operation platform 5; the four driving cylinders are correspondingly mounted on the counter-force seats 51 and connected to the corresponding support seats 43, so as to drive the two engaging portions 41 to approach or separate from each other in the radial direction of the housing 1.

Further, a running wheel 44 is connected to the bottom of the engaging portion 41, and a track 52 for the running wheel 44 to run is provided on the operation platform 5.

In the embodiment of the present application, the bottom of the engaging portion 41 is connected with three running wheels 44, one in the middle and one at each of two ends, so as to better support the running of the engaging portion 41 on the operation platform 5, and also ensure that the moving area of the engaging portion is the same after the engaging portion is opened and closed for multiple times.

Preferably, the top cover 2 is a flat cover. In the embodiment of the application, when the top cover 2 is designed as a flat cover, the space between the top cover 2 and the propellant 33 is reduced, so that the erosion and damage of the experimental equipment caused by the flow of high-temperature high-pressure gas in the space are avoided, and the safety and reliability of the experimental equipment are further ensured.

As shown in fig. 8, further, the end face of the housing 1 is in sealing connection with the top cover 2 through a first sealing ring 12; the top cover 2 extends downwards, a part extending downwards extends into the shell 1, and the part and the shell 1 are connected in a sealing way through a second sealing ring 13. In the embodiment of the application, cylindrical surface seals and end surface seals are arranged on the shell 1 and the top cover 2, so that the generated high-heat high-pressure gas is sprayed out of the spray pipe 34, and the ablation and damage of the high-heat high-pressure gas to experimental equipment are reduced.

As shown in fig. 6, preferably, a plurality of lifting holes 21 are provided on the outer side of the top cover 2. In the embodiment of the application, the top cover 2 is used as a part of experimental equipment, and needs to be opened and closed for a plurality of times when performing a plurality of simulated combustion tests, in order to facilitate the opening of the top cover 2, a lifting hole is formed in the top cover 2, and the top cover 2 can be lifted by a crane to separate the top cover 2 from the shell 1.

As shown in fig. 3 to 4, the housing 1 further includes a bottom cover 14, and the bottom cover 14 is a curved cover that is convex downward. In the embodiment of the present application, the bottom cover 14 with a curved surface can avoid stress concentration, reduce the thickness requirement of the bottom cover 14, and save consumables, and in the embodiment of the present application, the thickness of the top cover 2 as a flat cover is greater than that of the bottom cover 14 as a curved surface cover.

Example 3:

as shown in fig. 9 to 13, the filling structure 31 is shaped like a column, the filling structure 31 includes a circular arc side 311 and a shaped side 312, the circular arc side 311 is attached to the inner wall of the housing 1, and the shaped side 312 and the housing 1 enclose to form the combustion chamber 10; the test apparatus further comprises:

a first heat insulating layer 71 attached to the casing 1 and the filling structure 31 by attaching the peripheral outline of the combustion chamber 10, wherein the first heat insulating layer 71 includes one opposite fire side heat insulating layer 711, two adjacent fire side heat insulating layers 712, two propellant side heat insulating layers 713, and one propellant back side heat insulating layer 714, and the thicknesses of the opposite fire side heat insulating layers 711, adjacent fire side heat insulating layers 712, propellant side heat insulating layers 713, and propellant back side heat insulating layers 714 decrease in order;

meanwhile, the fire surface heat insulation layer 711, the adjacent fire surface heat insulation layer 712 and the propellant side heat insulation layer 713 are formed by jointly splicing a plurality of heat insulation unit sheets 710.

In the embodiment of the present application, a plurality of heat insulating unit sheets 710 are manufactured according to the thickness requirements of different areas of the first heat insulating layer 71 in advance, and the thickness of the heat insulating unit sheets 710 is determined according to the position of the heat insulating unit sheets, compared with the conventional first heat insulating layer on the periphery side of the combustion chamber 10, the embodiment of the present application can divide the position of the first heat insulating layer 71 relative to the propellant 33 (or the exposure time of each part of the first heat insulating layer relative to the high-temperature high-pressure gas) into a fire surface heat insulating layer 711, two adjacent fire surface heat insulating layers 712, two propellant side heat insulating layers 713 and a propellant back heat insulating layer 714, so that the heat insulating capability is better, and the excessively thick or thin heat insulating layer is avoided. The first heat insulating layer 71 in the embodiment of the application is formed by encircling a fire opposite heat insulating layer 711, a fire adjacent heat insulating layer 712, a propellant side heat insulating layer 713, a propellant back heat insulating layer 714, a propellant side heat insulating layer 713 and a fire adjacent heat insulating layer 712 which are connected in sequence; the fire surface heat insulating layer 711 is attached to the casing 1 and faces the propellant 33.

In the embodiment of the application, the filling structure 31 is adhered to the inside of the shell 1 and forms a combustion chamber 10 with the inner cavity of the shell 1, a plurality of heat insulation unit sheets 710 with proper thickness are designed in advance according to the specification of the combustion chamber 10 and the position relative to the propellant 33, and then the heat insulation unit sheets are integrally spliced into the first heat insulation layer 71, so that the defect that the first heat insulation layer 71 is difficult to move due to large volume is avoided, and meanwhile, the first heat insulation layer 71 is arranged on the periphery side of the combustion chamber 10, namely, is vertically arranged, so that the propellant 33 is conveniently installed along the vertical direction, and the simulation combustion test of multiple propellants is facilitated.

Meanwhile, the first heat insulation layer 71 is divided into a fire surface heat insulation layer 711, a fire surface heat insulation layer 712, a propellant side heat insulation layer 713 and a propellant back heat insulation layer 714 which are sequentially reduced in thickness relative to the position of the propellant 33, so that the heat insulation material can prevent high-temperature gas generated by simulated combustion of the propellant from ablating the shell 1 when the propellant 33 is combusted, and the safety performance of experimental equipment is improved. The heat insulation layer provided by the embodiment of the application ensures the simulated combustion quality of the propellant, and is convenient for replacing the propellant, so that the simulated combustion can be conveniently tested for multiple times.

As shown in fig. 13, it is preferable that two adjacent heat insulating unit sheets 710 are concavely and convexly adhered. In particular, on the abutting surface of the two heat insulating unit sheets 710, the middle portion of one is protruded outwards, and the middle portion of the other is adapted to be recessed inwards.

As shown in fig. 14, a second heat insulating layer 72 is further attached to the bottom of the top cover 2. The second insulating layer 72 is also flat.

As shown in fig. 15, further, the second heat insulating layer 72 includes a stepped heat insulating step portion 721 and a filling portion 722 filled between the step heat insulating step portion 721 and the top cover 2, the thickness of the step heat insulating step portion 721 being in accordance with the position of the second heat insulating layer 72 at the propellant 33.

As shown in fig. 12, a third heat insulating layer 73 is further attached to the bottom of the combustion chamber 10 on the filling structure 31. The first, second and third heat insulating layers 71, 72 and 73 form heat insulating layers on the upper and lower peripheral sides of the combustion chamber 10 to avoid ablation and destruction of test equipment.

As shown in fig. 14, further, the top cover 2 is provided with a pressure relief device 6, and a pressure relief heat insulation layer 75 is attached to the pressure relief device 6. The pressure relief device 6 is provided with a pressure relief heat insulation layer 75, which forms a fully heat insulation environment for the test equipment and protects the test equipment from being ablated by the generated high-temperature high-pressure gas. The pressure relief device 6 comprises an adapter seat 62 and a rupture disk 61, wherein the pressure relief heat insulation layer 75 is attached to the adapter seat 62, and a layer of soft rubber material, such as silicone rubber, is attached to the inner side of the rupture disk 61 to buffer the impact effect of the initial pressure relief process and avoid the rupture of the rupture disk 61 in advance.

As shown in fig. 16, further, the test apparatus further includes:

the fourth heat insulating layer 74 includes a plurality of flow-limiting strips 740 radially distributed, and all the flow-limiting strips 740 are used to be attached to the top of the propellant 33.

The gap between the fourth heat insulating layer 74 and the second heat insulating layer 72 is 0 to 8mm.

In general, during the installation of the propellant 33, the top cover 2 is carried out after the propellant 33 is placed in the combustion chamber 10, so that it is difficult to control the second heat insulation layer 72 on the top cover 2 to be just contacted with the fourth heat insulation layer 74 on the propellant 33, a certain gap exists between the second heat insulation layer 72 and the fourth heat insulation layer 74, and theoretically, the gap is zero, but in practice, the gap exists, and when the gap is large, the top surface of the propellant 33 is burnt out first, so that the combustion surface is abnormal, the pressure is increased, and the test fails, therefore, the gap between the fourth heat insulation layer 74 and the second heat insulation layer 72 is controlled to be below 8mm, and the generated high-temperature high-pressure gas can be effectively prevented from flowing into the gap to ablate the top surface of the propellant 33.

Preferably, the current-limiting strip 740 is further coated with putty. And (3) pasting putty with the thickness of 2-3 mm on the current-limiting strip, and when the top cover 2 is covered on the shell 1, being capable of accumulating the putty to fill the cavities at two sides, so as to prevent the generated high-heat high-pressure gas from flowing in the gap.

The above embodiments are not limited to the respective embodiments, but may be combined with each other according to actual needs.

In the description of the present application, it should be noted that the azimuth or positional relationship indicated by the terms "upper", "lower", etc. are based on the azimuth or positional relationship shown in the drawings, and are merely for convenience of describing the present application and simplifying the description, and are not indicative or implying that the apparatus or element in question must have a specific azimuth, be constructed and operated in a specific azimuth, and thus should not be construed as limiting the present application. Unless specifically stated or limited otherwise, the terms "mounted," "connected," and "coupled" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to the specific circumstances.

It should be noted that in the present application, relational terms such as "first" and "second" and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.

The foregoing is only a specific embodiment of the application to enable those skilled in the art to understand or practice the application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims (9)

1. A solid rocket engine simulated combustion test device for simulating combustion of a propellant (33) to be tested in a solid rocket engine; the test equipment is characterized by comprising:

a cylindrical shell (1), wherein a flange (11) is arranged on the top circumference side of the cylindrical shell, the shell (1) further comprises a bottom cover (14), and the bottom cover (14) is a downward convex curved surface cover;

a top cover (2) covering the shell (1), wherein a combustion chamber (10) for combusting the propellant (33) is formed in the shell (1);

the spray pipe (34) is arranged on the top cover (2) and communicated with the combustion chamber (10), the shell (1) is vertically arranged, and an opening of the spray pipe (34) is vertically upwards;

-a profiled cylindrical filling structure (31) comprising profiled sides (312), said profiled sides (312) enclosing with said casing (1) forming a combustion chamber (10) for combustion of said propellant (33);

a first heat insulating layer (71) which is attached to the casing (1) and the filling structure (31) so as to be attached to the peripheral outline of the combustion chamber (10);

a second heat insulation layer (72) is adhered to the bottom of the top cover (2), the second heat insulation layer (72) comprises a step-shaped step heat insulation part (721) and a filling part (722) filled between the step heat insulation part (721) and the top cover (2), and the thickness of the step heat insulation part (721) is in the position of the propellant (33) according to the second heat insulation layer (72);

the fourth heat insulation layer (74) comprises a plurality of radial current-limiting strips (740), all the current-limiting strips (740) are used for being attached to the top of the propellant (33), the gap between the fourth heat insulation layer (74) and the second heat insulation layer (72) is 0-8 mm, and putty is further coated on the current-limiting strips (740);

a pressure relief device (6) in communication with the combustion chamber (10); the pressure relief device (6) comprises a rupture disc (61), an adapter seat (62) and a cap (63), and a pressure measuring hole (60) is formed in the side wall of the adapter seat (62); the adapter seat (62) is arranged on the top cover (2); the cover cap (63) is detachably arranged above the adapter seat (62); the adapter seat (62) and the cover cap (63) are annular; the rupture disc (61) is clamped between the adapter seat (62) and the cap (63) and cuts off the communication between the adapter seat (62) and the cap (63);

a clamping mechanism comprising two clamping parts (41) and at least two driving parts (42); the two clamping parts (41) are oppositely arranged, and grooves (410) are formed in the inner walls of the clamping parts (41); the two driving parts (42) are arranged at two sides of the shell (1) and are respectively connected with one clamping part (41) for driving the corresponding clamping part (41) to reciprocate linearly along the radial direction of the shell (1); meanwhile, when the two clamping parts (41) are in butt joint, the two grooves (410) form an annular groove, and the annular groove is clamped outside the edges of the flange (11) and the top cover (2).

2. A solid rocket engine simulated combustion test device as claimed in claim 1, wherein:

the end face of the shell (1) is in sealing connection with the top cover (2) through a first sealing ring (12);

the top cover (2) extends downwards, a part extending downwards extends into the shell (1), and the part is in sealing connection with the shell (1) through a second sealing ring (13).

3. A solid rocket engine simulated combustion test device as claimed in claim 1, wherein:

the engagement portion (41) has a semicircular structure.

4. A solid rocket engine simulated combustion test device as recited in claim 1, further comprising:

the operation platform (5) is fixedly arranged on the periphery of the shell (1), and the driving parts (42) symmetrically distributed relative to the shell (1) are arranged on the operation platform (5).

5. A solid rocket engine simulated combustion test device as claimed in claim 4, wherein the number of said driving portions (42) is four, and each of said engaging portions (41) has two ends connected to one of said driving portions (42).

6. A solid rocket engine simulated combustion test device according to claim 5, wherein said driving portion (42) comprises a driving cylinder, two supports (43) are provided on the bottom side of each engagement portion (41), and four reaction seats (51) are provided on said operating platform (5); the four driving oil cylinders are correspondingly arranged on the counter-force seats (51) and connected with the corresponding support seats (43) so as to drive the two clamping parts (41) to be close to or far from each other along the radial direction of the shell (1).

7. The solid rocket engine simulated combustion test device according to claim 4, wherein a running wheel (44) is connected to the bottom of the clamping part (41), and a track (52) for the running wheel (44) to run is arranged on the operating platform (5).

8. A solid rocket engine simulated combustion test device as claimed in claim 1, wherein:

the two clamping parts (41) are connected through flanges.

9. A solid rocket engine simulated combustion test device as claimed in claim 1, wherein:

the top cover (2) is a flat cover.