CN114166991A - Single-side multi-outlet testing device for heat insulation layer of rocket engine - Google Patents
Single-side multi-outlet testing device for heat insulation layer of rocket engine Download PDFInfo
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- 238000009413 insulation Methods 0.000 title claims abstract description 113
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- 238000007789 sealing Methods 0.000 claims description 6
- 238000012544 monitoring process Methods 0.000 claims description 3
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- 238000002679 ablation Methods 0.000 description 57
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- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
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- G01N31/00—Investigating or analysing non-biological materials by the use of the chemical methods specified in the subgroup; Apparatus specially adapted for such methods
- G01N31/12—Investigating or analysing non-biological materials by the use of the chemical methods specified in the subgroup; Apparatus specially adapted for such methods using combustion
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The embodiment of the application provides a single-side multi-outlet testing device for a heat insulating layer of a rocket engine. This unilateral many play testing arrangement includes: a test engine unit having a combustion chamber and an output; the output end is provided with at least two gas channels; the combustion chamber is used for generating a real gas environment simulating a rocket engine; one end of each tail pipe unit is detachably connected with the test engine unit and is communicated with the corresponding gas channel, and the tail pipe units are used for correspondingly bearing different types of heat insulation layer test pieces and forming the same test environment; and each spray pipe unit is detachably connected to one end, far away from the test engine unit, of the corresponding tail pipe unit. The embodiment of the application can realize that different types of heat insulation layer test pieces are in the same test environment in the channel on the premise of a plurality of channels, improves the assessment precision and reduces the test cost.
Description
Technical Field
The application relates to the technical field of solid rocket engine testing, in particular to a single-side multi-outlet testing device for a heat insulating layer of a rocket engine.
Background
The heat insulation layer is a key part of the solid rocket engine, plays a role in heat protection on the shell, ensures that the shell is not burnt through or heated to lose strength, protects the shell from being corroded by the explosive columns and buffering the bonding stress between the explosive columns and the shell, and can also ensure the airtightness of the fiber winding shell for the fiber winding shell. Therefore, it is necessary to conduct the ablation test of the heat insulating layer to examine the ablation resistance.
However, the existing insulation layer ablation test mode generally has the following defects:
1. the difference between the test environment and the real working environment is large, and the accuracy of ablation performance parameters obtained by the test is low;
2. the single test is limited to ablation of a single heat insulation layer test piece, and a fractional test is adopted for heat insulation layer test pieces of different types (such as different types or different batches) so that the same test environment with high precision is difficult to reproduce, namely the ablation performance parameter precision of each heat insulation layer test piece obtained by the fractional test under the same test environment is lower;
3. a single test is limited to ablation of a single heat insulation layer test piece, only ablation performance parameters of one heat insulation layer test piece can be obtained by fuel and time consumed by each test, and the test cost is high.
Disclosure of Invention
The application provides a single-side multi-outlet testing device for a heat insulating layer of a rocket engine aiming at the defects of the prior art, and is used for solving at least one technical problem in the prior art.
In a first aspect, the present application provides a single-side multi-outlet testing apparatus for a thermal insulation layer of a rocket motor, including:
a test engine unit having a combustion chamber and an output; the output end is provided with at least two gas channels, and two ends of each gas channel are respectively communicated with the combustion chamber and the external environment of the test engine unit; the combustion chamber is used for generating a real gas environment simulating a rocket engine;
one end of each tail pipe unit is detachably connected with the test engine unit, is communicated with the corresponding gas channel and is used for correspondingly bearing different types of heat insulation layer test pieces and forming the same test environment;
and each nozzle unit is detachably connected to one end, far away from the test engine unit, of the corresponding tail pipe unit.
The beneficial technical effects brought by the technical scheme provided by the embodiment of the application comprise: the single-side multi-outlet test device for the heat insulation layer of the rocket engine adopts a test engine unit with a combustion chamber, and a tail pipe unit and a spray pipe unit structure which are connected to the output end of the test engine unit, is closer to the structure of a real solid rocket engine, can simulate the working environment of the real solid rocket engine, and is beneficial to obtaining the ablation performance parameters of a heat insulation layer test piece with higher precision.
The two or more than two gas channels at the output end of the test engine unit and the two or more than two tail pipe units not only provide two or more than two test stations for the heat insulation layer test piece, namely, each tail pipe unit correspondingly bears different types of heat insulation layer test pieces, provides the same test conditions (comprising the same airflow environment such as temperature, pressure, gas velocity, particle concentration in airflow and the like) in the tail pipe for each heat insulation layer test piece, so that the single-side multiple-outlet test device for the heat insulation layer of the rocket engine can simultaneously ablate different types of heat insulation layer test pieces in the same ablation test, and all the heat insulation layer test pieces are positioned in the same test environment in the channel under the premise of a plurality of channels, the ablation performance comparison and examination precision of different types of heat-insulating layer test pieces in the same real gas environment can be greatly improved.
In addition, the single-side multiple-outlet test device for the heat insulation layer of the rocket engine can simultaneously ablate different types of heat insulation layer test pieces in the same ablation test, so that the fuel consumption can be effectively reduced, the test time can be shortened, and the test cost can be reduced.
Additional aspects and advantages of the present application will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the present application.
Drawings
The foregoing and/or additional aspects and advantages of the present application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1 is a schematic cross-sectional view of a single-side multi-outlet testing device for a thermal insulation layer of a rocket motor according to an embodiment of the present disclosure;
FIG. 2 is a right side view of a single-side multiple-out test apparatus for a rocket motor insulation layer according to an embodiment of the present disclosure;
FIG. 3 is a schematic cross-sectional view of a test engine unit in a single-side multi-outlet test device for a thermal insulation layer of a rocket engine provided in an embodiment of the present application;
fig. 4 is a schematic cross-sectional structure diagram of a nozzle unit in a single-side multiple-outlet testing device for a thermal insulation layer of a rocket engine provided by an embodiment of the application.
In the figure:
100-testing the engine unit; 101-a combustion chamber; 102-a gas channel;
110-a combustion chamber housing; 120-sealing cover plate;
130-a flow directing structure; 131-a flow guide plate; 132-a backplane; 133-a measurement adapter;
140-a thermally insulating structure;
200-a tailpipe unit; 210-tailpipe cylinder; 220-a first connecting flange; 230-a second connecting flange;
300-a nozzle unit; 310-a nozzle barrel; 320-a nozzle diffuser section; 330-throat liner;
400-thermal insulation layer test piece; 500-grain; 600-ignition charge.
Detailed Description
Reference will now be made in detail to the present application, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar parts or parts having the same or similar functions throughout. In addition, if a detailed description of the known art is not necessary for illustrating the features of the present application, it is omitted. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present application and are not to be construed as limiting the present application.
It will be understood by those within the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. It will be understood that when an element is referred to as being "connected" or "coupled" to another element, it can be directly connected or coupled to the other element or intervening elements may also be present. Further, "connected" or "coupled" as used herein may include wirelessly connected or wirelessly coupled. As used herein, the term "and/or" includes all or any element and all combinations of one or more of the associated listed items.
The terms referred to in this application will first be introduced and explained:
average mass ablation rate: after the heat insulation layer test piece is scoured and ablated by high-temperature and high-pressure gas, the quality of the test piece is t in the working timeaAverage loss rate within.
Average wire ablation rate: after the heat insulation layer test piece is scoured and ablated by high-temperature and high-pressure gas, the inner diameter of the test piece is within the working time taThe average rate of increase in.
The inventor of the application researches and discovers that when designing and selecting the heat insulating layer of the solid rocket motor, the ablation performance of different heat insulating materials in the same working environment is required to be referred to. The method for evaluating the ablation performance of the heat-insulating layer material mainly comprises the following steps: oxyacetylene ablation, plasma heating, arc heating, ablation test engine or scaled engine ablation, and the like.
Both the oxyacetylene ablation method and the plasma heating method have no condensed phase particles, and have larger difference with the components and the content of fuel gas in a real engine, larger difference between the test environment and the real working environment, and lower accuracy of the test result.
The arc heater is used for forming an arc between electrodes by utilizing large current to heat gas for carrying out an ablation test of a heat insulating layer, and simulating condensed-phase alumina particles in gas of a solid rocket engine by manually adding particles. It can be seen that the arc heating test implemented by the arc heater is characterized in that: ablation state parameters are easy to adjust, but the differences of components and content of fuel gas, condensed phase particle characteristics and the like from a real engine are large, the differences of a test environment and a real working environment are also large, and the accuracy of a test result is low.
The ablation test engine (or scaling engine) is closer to the real working mode of the solid rocket engine, and can simulate the real working environment of the solid rocket engine to obtain the ablation performance parameters of the heat insulation layer material.
Just because the working modes of the ablation test engine and a real solid rocket engine are closer, an engineer in the industry only designs a long tail jet pipe like the real solid rocket engine when designing the ablation test engine, namely only an installation position of a heat insulation layer test piece. And is widely recognized by engineers in the industry: the same test environment refers to a test environment provided by the same test equipment operating under the same set parameter state.
Therefore, for the heat insulation layer test pieces of different types (for example, different types, different batches and the like), an engineer in the industry only obtains corresponding ablation performance parameters in a fractional test mode, namely, an ablation test engine is started and operated successively, and each heat insulation layer test piece is tested one by one.
However, even with the same test apparatus, it is not guaranteed that the parameters are the same for each test. Errors (such as errors of starting of an engine each time, errors of various parameters of pressure, temperature and the like in a testing device) between tests cannot be avoided, so that the heat-insulating layer test pieces are difficult to be ensured to be in the real same test environment in the tests in multiple times, and the ablation performance comparison and assessment accuracy of different types of heat-insulating layer test pieces in the same real gas environment is difficult to improve. In addition, the fuel and time consumed by each test can only obtain the ablation performance parameters of one heat insulation layer test piece, and the test cost is higher.
The application provides a unilateral many play testing arrangement of rocket engine heat insulation layer, aims at solving prior art as above technical problem.
The following describes the technical solutions of the present application and how to solve the above technical problems with specific embodiments.
The embodiment of the application provides a single-side multi-outlet testing device for a thermal insulation layer of a rocket engine, and the structural schematic diagram of the single-side multi-outlet testing device for the thermal insulation layer of the rocket engine is shown in fig. 1 and comprises the following components: a test engine unit 100, at least two tailpipe units 200 and at least two nozzle units 300.
The test engine unit 100 has a combustion chamber 101 and an output. The output end has at least two gas passages 102, and both ends of the gas passages 102 are respectively communicated with the combustion chamber 101 and the external environment of the test engine unit 100. The combustion chamber 101 is used to create a real gas environment simulating a rocket engine.
One end of each tail pipe unit 200 is detachably connected to the test engine unit 100 and is communicated with the corresponding gas channel 102 for correspondingly carrying the different kinds of the heat insulating layer test pieces 400 and forming the same test environment.
Each nozzle unit 300 is detachably attached to the end of the corresponding tailpipe unit 200 remote from the test engine unit 100.
In this embodiment, the single-side multiple-outlet test device for the thermal insulation layer of the rocket engine adopts the test engine unit 100 with the combustion chamber 101, and the tail pipe unit 200 and the nozzle unit 300 connected to the output end of the test engine unit 100, which are closer to the structure of a real solid rocket engine, so that a more real working environment of the solid rocket engine can be simulated, and the obtaining of the ablation performance parameters of the thermal insulation layer test piece 400 with higher precision is facilitated.
Two or more gas passages 102 at the output of the test engine unit 100, with two or more pluralities of tailpipe units 200, not only are two or more pluralities of test stations provided for the insulation barrier test piece 400, namely, each tail pipe unit 200 correspondingly bears different types of heat insulating layer test pieces 400, and provides the same test conditions (comprising the same air flow environment such as temperature, pressure, gas velocity, particle concentration in air flow and the like) in the tail pipe for each heat insulating layer test piece 400, so that the single-side multiple-test device for the heat insulation layer of the rocket engine can simultaneously ablate different types of heat insulation layer test pieces 400 in the same ablation test, and each heat insulation layer test piece 400 is in the same test environment in the channel under the premise of a plurality of channels, the ablation performance comparison and examination precision of different types of heat-insulating layer test pieces 400 in the same real gas environment can be greatly improved.
In addition, the single-side multiple-out test device for the heat insulation layer of the rocket engine can simultaneously ablate different types of heat insulation layer test pieces 400 in the same ablation test, so that the fuel consumption can be effectively reduced, the test time can be shortened, and the test cost can be reduced.
The inventor of the present application considers that the tailpipe unit 200 needs to support different kinds of the thermal insulation layer test pieces 400 correspondingly, and both ends of the tailpipe unit 200 need to be detachably connected to the test engine unit 100 and the nozzle unit 300, respectively, so as to improve the convenience of mounting and dismounting the thermal insulation layer test pieces 400. To this end, embodiments of the present application provide the tailpipe unit 200 with the following possible implementations:
as shown in fig. 1, a tailpipe unit 200 of the embodiment of the present application includes: a tail pipe cylinder 210, and a first connecting flange 220 and a second connecting flange 230 respectively located at both ends of the tail pipe cylinder 210.
The inner wall of the tailpipe cylinder 210 is used for detachable connection with the thermal insulation layer test piece 400.
The first connecting flange 220 is detachably connected to the test engine unit 100.
The second connection flange 230 is detachably connected to the spout unit 300.
In this embodiment, the tailpipe cylinder 210 is a hollow cylindrical structure, which can provide a real testing environment in the tailpipe for the thermal insulation layer test piece 400, and the inner wall of the tailpipe cylinder 210 can correspondingly bear different types of thermal insulation layer test pieces 400.
The first and second connection flanges 220 and 230 may facilitate detachable connection of both ends of the tailpipe cylinder 210 to the test engine unit 100 and the nozzle unit 300, respectively, facilitate attachment and detachment of the thermal insulation layer test piece 400, and facilitate maintenance of the tailpipe unit 200.
For example, in the preparation process of the ablation test, the thermal insulation layer test piece 400 may be first mounted on the inner wall of the tail pipe cylinder 210 of the tail pipe unit 200, then the nozzle unit 300 may be mounted on the second connection flange 230, then the tail pipe cylinder 210 with the thermal insulation layer test piece 400 mounted thereon may be communicated with the corresponding gas passage 102 of the test engine unit 100, and the first connection flange 220 may be connected to the test engine unit 100.
After the ablation test is finished, the connection between the first connecting flange 220 and the test engine unit 100 can be firstly released, so that the heat insulation layer test piece 400 can be more easily detached from the inner wall of the nozzle diffusion section 320 in the nozzle unit 300; of course, it is also possible to first disconnect the second connecting flange 230 from the nozzle unit 300 and then disconnect the first connecting flange 220 from the test engine unit 100.
Alternatively, the first connecting flange 220 and the tailpipe cylinder 210 may be integrally connected by welding or riveting, and the second connecting flange 230 and the tailpipe cylinder 210 may also be integrally connected by welding or riveting.
Alternatively, the first connecting flange 220 may be connected to the test engine unit 100 by bolts and nuts, and the second connecting flange 230 may be connected to the nozzle unit 300 by bolts and nuts.
Optionally, an O-ring may be further installed between the first connecting flange 220 and the test engine unit 100 to improve the sealing performance between the gas channel 102 of the test engine unit 100 and the tailpipe cylinder 210; an O-ring seal may be added between the second coupling flange 230 and the nozzle unit 300 to improve the sealing performance between the tailpipe cylinder 210 and the nozzle unit 300.
The inventors of the present application considered that, in the ablation test, depending on the position of each thermal insulation layer test piece 400 (i.e., the position of each tailpipe unit 200), which is determined by the layout of the gas passages 102, there may be some environmental differences among the thermal insulation layer test pieces 400. To this end, the embodiments of the present application provide the following possible implementations for the layout of the gas channel 102:
in some possible embodiments, as shown in fig. 2, at least two gas passages 102 surround the center point of the output end.
In this embodiment, the gas channel 102 is disposed around the center point of the output end of the test engine unit 100, which is beneficial for forming a uniform layout, thereby reducing the possible environmental differences of the heat insulation layer test pieces 400, and improving the ablation performance comparison and evaluation accuracy of the heat insulation layer test pieces 400 of different types in the same real gas environment. Meanwhile, the area utilization rate of the output end of the test engine unit 100 is improved, that is, more gas channels 102 can be arranged under the condition that the area of the output end of the test engine unit 100 is fixed.
In some possible embodiments, the at least two gas passages 102 are equidistant from a center point of the output end.
In this embodiment, the gas channels 102 are arranged in a manner that the distance between the gas channels 102 and the central point of the output end of the test engine unit 100 is equal, so that the gas channels 102 are located on the circumference around the central point of the output end, which is beneficial to reducing the possible environmental difference of the heat insulation layer test pieces 400, and improving the ablation performance comparison and evaluation accuracy of the heat insulation layer test pieces 400 of different types in the same real gas environment.
In some possible embodiments, the distance between every two adjacent gas channels 102 is equal.
In this embodiment, the gas passages 102 are arranged in a manner that the distances between every two adjacent gas passages 102 are equal, which is beneficial to uniformly distributing the gas passages 102 at the output end of the test engine unit 100, and is further beneficial to reducing the possible environmental differences of the heat insulation layer test pieces 400, and improving the precision of the ablation performance comparison and examination of the heat insulation layer test pieces 400 of different types in the same real gas environment. For example, the gas passages 102 are distributed in a matrix, or in a honeycomb, etc.
In some possible embodiments, the distance between at least two gas passages 102 and the center point of the output end is equal, and the distance between every two adjacent gas passages 102 is equal.
In this embodiment, each gas channel 102 may be located on a circumference with the center point of the output end as the center of a circle, and the gas channels are uniformly distributed on the circumference, which may be beneficial to reduce the possible environmental difference of each heat insulation layer test piece 400, and improve the accuracy of the ablation performance comparison and evaluation of different types of heat insulation layer test pieces 400 in the same real gas environment.
In some possible embodiments, one gas channel 102 of the at least two gas channels 102 is located at a center point of the output end.
In this embodiment, one gas channel 102 of the gas channels 102 is disposed at a central point of the output end of the test engine unit 100, which may be beneficial to the layout and positioning of all the gas channels 102, for example: the gas channels 102 are distributed in a matrix or honeycomb manner; on the other hand, it is also beneficial to improve the area utilization rate of the output end of the test engine unit 100, for example: at least part of the gas channels 102 in each gas channel 102 are arranged around the center point of the output end, and one gas channel 102 in each gas channel 102 is arranged at the center point of the output end of the test engine unit 100, so that the area in the middle of each gas channel 102 which is arranged around the circle can be fully utilized by the gas channel 102.
The inventors of the present application considered that, in addition to testing the engine unit 100, the nozzle unit 300 is also an important component for helping the tailpipe unit 200 to be able to form a more realistic working environment of the thermal insulation layer test piece 400, i.e., the structure of the nozzle unit 300 itself may have an influence on the test environment of the thermal insulation layer test piece 400. To this end, embodiments of the present application provide the following possible implementations for the structure of the spout unit 300:
as shown in fig. 4, in the single-side multi-outlet testing apparatus for thermal insulation layer of rocket motor provided in the embodiment of the present application, the nozzle unit 300 includes: nozzle barrel 310, nozzle diffuser 320, and throat insert 330.
The outer wall of the nozzle barrel 310 is detachably connected with the inner wall of the gas channel 102.
The inner wall of the nozzle barrel 310 is detachably connected to the outer wall of the nozzle diffuser 320.
The inner wall of nozzle diffuser 320 is removably attached to throat insert 330.
In this embodiment, the nozzle barrel 310 may serve as a supporting structure of the entire nozzle unit 300 for mating connection with the inner wall of the gas channel 102.
The nozzle diffusion section 320 can simulate a turbulent flow structure in a nozzle of a real solid rocket engine, help the tail pipe unit 200 provide a test environment which is closer to the working environment of the real solid rocket engine for the heat insulation layer test piece 400, and is beneficial to obtaining ablation performance parameters of the heat insulation layer test piece 400 with higher precision.
The outer wall of the nozzle barrel 310 is detachably connected with the inner wall of the gas channel 102. Thus, the installation convenience between the throat insert 330 and the nozzle unit 300 can be improved, the throat insert 330 of the corresponding type can be replaced according to the test requirement, and the compatibility of the nozzle unit 300 can be improved.
The inner wall of the nozzle barrel 310 is detachably connected to the outer wall of the nozzle diffuser 320. Therefore, the installation convenience between the nozzle diffusion section 320 and the nozzle cylinder body 310 can be improved, and further the size requirement of the throat insert 330 of the type required by the test can be met by replacing the nozzle diffusion sections 320 with different sizes, or the requirement of the test airflow parameters can be met by replacing the nozzle diffusion sections 320 with different turbulent flow types, or the replacement and maintenance of the nozzle diffusion sections 320 are facilitated.
The inventors of the present application considered that the combustion chamber 101 of the test engine unit 100 was used to create the same real gas environment simulating a rocket motor, and different types of the heat insulating layer test pieces 400 were tested. To this end, the embodiments of the present application provide the following possible implementations for testing the structure of the engine unit 100:
as shown in fig. 3, in the single-side multi-outlet test apparatus for thermal insulation layer of rocket motor provided in the embodiment of the present application, the test motor unit 100 includes: a combustor casing 110, a cap plate 120, and a flow directing structure 130.
The capping plate 120 is coupled to one end of the combustor casing 110.
The flow guide structure 130 includes: a baffle 131 and a bottom plate 132. The guide plate 131 is an annular structure with unequal calibers at two ends, the first end of the guide plate 131 is connected with the other end of the combustion chamber shell 110, the second end of the guide plate 131 is connected with the bottom plate 132, and the caliber of the first end is larger than that of the second end.
The capping plate 120, the combustor casing 110, the baffle 131 and the bottom plate 132 enclose a combustion chamber 101. The gas channel 102 opens onto the base plate 132.
In the present embodiment, the test engine unit 100 includes a combustion chamber housing 110, a cover plate 120, and a flow guide structure 130 enclosing a combustion chamber 101, which is relatively simple in structure and easy to manufacture and assemble. A portion of the combustion chamber 101 may be used to contain fuel that, when ignited, may create a real gas environment that simulates a rocket engine.
The bottom plate 132 in the flow guide structure 130 provides a layout site for each gas channel 102, i.e., provides an installation station for each tailpipe unit 200, and provides a test station for the thermal insulation layer test piece 400. The guide plate 131 in the guide structure 130 serves as a connecting structure between the combustion chamber shell 110 and the bottom plate 132, so that the real fuel gas generated by the combustion chamber 101 and used for simulating the rocket engine can be guided to each tail pipe unit 200 in a manner of simulating the real air flow of the rocket engine, and a more real working environment of the solid rocket engine can be simulated for the heat insulation layer test piece 400, thereby facilitating the acquisition of ablation performance parameters of the heat insulation layer test piece 400 with higher precision.
Alternatively, the combustor casing 110 may take a cylindrical structure with both ends open.
Alternatively, the fuel may be in the form of a charge 500 of a real solid rocket engine.
In some possible embodiments, in order to make the test engine unit 100 easier to manufacture, assemble or maintain, the present embodiment provides a test engine unit 100 comprising at least one of the following features:
optionally, the capping plate 120 is removably attached to one end of the combustor casing 110.
Alternatively, the first end of the baffle 131 is detachably connected to the other end of the combustion chamber housing 110.
Optionally, the second end of the baffle 131 is removably attached to the base plate 132.
The inventors of the present application have considered that in the ablation test, environmental parameters within the combustion chamber 101 of the test engine unit 100 need to be monitored. To this end, the flow guiding structure 130 provided in the embodiment of the present application further includes: the adapter 133 is measured.
As shown in fig. 2 and 3, a measurement adapter 133 is disposed on an outer wall of the baffle 131 for mounting a pressure sensor.
The pressure sensor is used to monitor the operating pressure of the combustion chamber 101.
In this embodiment, the measurement adapter 133 provides an installation station for the pressure sensor, and the measurement adapter 133 is disposed on the outer wall of the diversion plate 131, so that the pressure sensor can be closer to the tailpipe unit 200, which is beneficial to monitoring the pressure parameter of the combustion chamber 101, which is closer to the environment of the thermal insulation layer test piece 400, and improving the monitoring accuracy.
Optionally, the pressure sensor may be in communication connection with an upper computer, and may send the monitored working pressure of the combustion chamber 101 to the upper computer, where the working pressure is stored or subjected to operational analysis and the like. Other parameters of at least part of the combustion gas in the combustion chamber 101 can be calculated thermodynamically, depending on the type of fuel (propellant) selected.
Alternatively, the measurement adapter 133 may also be used to mount other sensors instead, such as: a temperature sensor for measuring the temperature in the combustion chamber 101, or a flow rate sensor for measuring the flow rate of the gas in the combustion chamber 101, or the like. These sensors may be used alternatively or in any combination.
The inventors of the present application considered that a large amount of heat was generated in the test engine unit 100 in the ablation test. To this end, the test engine unit 100 provided by the embodiment of the present application further includes: an insulating structure 140.
As shown in fig. 3, the insulation structure 140 includes at least one of the following features:
optionally, the insulation structure 140 is disposed on a side of the cover plate 120 adjacent to the bottom plate 132. The thermal isolation structure 140 thus reduces the escape or dissipation of heat generated within the test engine unit 100 from the cover plate 120, and also reduces the occurrence of structural damage, such as deformation, due to overheating of the cover plate 120.
Optionally, a heat insulation structure 140 is provided to the inner wall of the combustor casing 110. This may reduce the escape or dissipation of heat generated within the test engine unit 100 from the combustion chamber housing 110, and may also reduce the occurrence of structural damage, such as deformation, due to overheating of the combustion chamber housing 110.
Optionally, insulation 140 is provided to the inner wall of the baffle 131. Thus, the thermal insulation structure 140 can reduce the heat generated in the test engine unit 100 from escaping or dissipating from the baffle 131, and can also reduce the structural damage such as deformation caused by overheating of the baffle 131.
Optionally, the thermal insulation structure 140 is disposed on a side of the bottom plate 132 adjacent to the cover plate 120. The thermal insulation structure 140 thus reduces the escape or dissipation of heat generated within the test engine unit 100 from the base plate 132, and also reduces the occurrence of structural damage, such as deformation, due to overheating of the base plate 132.
It is understood that the various arrangements provided by the embodiments of the present application for the insulation structure 140 may be implemented individually or in any combination as desired.
The following is a further example of the various implementable single-side multiple-outlet testing devices for the insulation layer of the rocket motor described above.
The general assembly method of the single-side multi-outlet testing device for the heat insulating layer of the rocket engine comprises the following steps:
the inner wall of the combustion chamber case 110, one side of the capping plate 120, the inner wall of the guide plate 131, and one side of the bottom plate 132 are respectively bonded to the corresponding heat insulation structures 140.
The ignition charge 600 is adhered to one end of the charge 500, and then the other end surface of the charge 500 is coated with an adhesive and then placed inside the combustion chamber case 110, and the ignition lead of the ignition charge 600 is led out from the combustion chamber case 110.
After the adhesive is applied to the surface of the heat insulation structure 140 on the capping plate 120, the cap plate 120 and the heat insulation structure 140 on the capping plate 120 are mounted on one end of the combustion chamber housing 110 by bolts, and the charge 500 is bonded to the heat insulation structure 140.
The guide plate 131 and the bottom plate 132 are installed by screws or bolts to form the flow guide structure 130, and then the flow guide structure 130 is installed at the other end of the combustion chamber shell 110 by screws or bolts, and the ignition lead is led out from any gas channel 102 on the bottom plate 132.
The weight m of each heat insulating layer test piece 400 was measured and recordedjAnd an inner diameter djAfter the thermal insulation layer test piece 400 to be examined is installed in the tail pipe cylinder 210 of the tail pipe unit 200, the nozzle unit 300 is connected with the second connecting flange 230 of the tail pipe unit 200 in an installing mode, then the first connecting flange 220 of the tail pipe unit 200 is connected with the middle bottom plate 132 of the flow guide structure 130 in an installing mode, the tail pipe cylinder 210 is communicated with the corresponding gas channel 102, the ignition lead is led out from any nozzle unit 300, and the assembly of the rocket engine thermal insulation layer single-side multi-outlet testing device is completed.
A performance test method for a heat insulation layer test piece 400 of a single-side multi-outlet test device based on a rocket engine heat insulation layer comprises the following steps:
the single-side multi-outlet testing device of the heat insulating layer of the rocket engine which is assembled totally is fixed on a test bed, and a pressure sensor is arranged on the measuring adapter 133.
And connecting the ignition lead with the ignition system of the test bed, and entering a formal ignition program.
After the ablation experiment is started by ignition, whether the experiment process is normal or not is observed, and pressure intensity-time data are obtained by testing.
After the completion of the ablation test, the heat insulating layer test piece 400 in each tail pipe unit 200 was taken out, the ablation condition of each heat insulating layer test piece 400 was observed, and the weight m 'of the heat insulating layer test piece 400 was measured and recorded'jAnd inner diameter d'j(ii) a Processing the pressure intensity-time data to obtain: operating time ta(starting point: initial rising section 0.3MPa time, end point: falling section 0.3MPa time), average pressure
(average pressure over working time); obtaining pressure intensity
Under the condition of adopting the same propellant formula as the explosive column 500, the average ablation rate of the thermal insulation layer test piece 400 in each tail pipe unit 200 is as follows: (m)j-m′j)/(mj·ta) The average line ablation rate was: (d'j-dj)/(2·ta)。
By applying the embodiment of the application, at least the following beneficial effects can be realized:
1. the single-side multiple-outlet test device for the heat insulation layer of the rocket engine adopts a test engine unit 100 with a combustion chamber 101, and a tail pipe unit 200 and a spray pipe unit 300 which are connected with the output end of the test engine unit 100, is closer to the structure of a real solid rocket engine, can simulate the working environment of the real solid rocket engine, and is beneficial to obtaining the ablation performance parameters of the heat insulation layer test piece 400 with higher precision.
2. Two or more gas passages 102 at the output of the test engine unit 100, with two or more pluralities of tailpipe units 200, not only are two or more pluralities of test stations provided for the insulation barrier test piece 400, namely, each tail pipe unit 200 correspondingly bears different types of heat insulating layer test pieces 400, and provides the same test conditions (comprising the same air flow environment such as temperature, pressure, gas velocity, particle concentration in air flow and the like) in the tail pipe for each heat insulating layer test piece 400, so that the single-side multiple-test device for the heat insulation layer of the rocket engine can simultaneously ablate different types of heat insulation layer test pieces 400 in the same ablation test, and each heat insulation layer test piece 400 is in the same test environment in the channel under the premise of a plurality of channels, the ablation performance comparison and examination precision of different types of heat-insulating layer test pieces 400 in the same real gas environment can be greatly improved.
3. The single-side multiple-outlet test device for the heat insulation layer of the rocket engine can simultaneously ablate different types of heat insulation layer test pieces 400 in the same ablation test, can effectively reduce fuel consumption, shorten test time and reduce test cost.
4. The tail pipe cylinder 210 is a hollow cylindrical structure, and can provide a real tail pipe internal test environment for the heat insulation layer test piece 400, and the inner wall of the tail pipe cylinder 210 can correspondingly bear different types of heat insulation layer test pieces 400. The first and second connection flanges 220 and 230 may facilitate detachable connection of both ends of the tailpipe cylinder 210 to the test engine unit 100 and the nozzle unit 300, respectively, facilitate attachment and detachment of the thermal insulation layer test piece 400, and facilitate maintenance of the tailpipe unit 200.
5. The gas channel 102 is arranged around the central point of the output end of the test engine unit 100, so that uniform arrangement is facilitated, the possible environmental difference of the heat-insulating layer test pieces 400 is reduced, and the ablation performance comparison and assessment accuracy of the heat-insulating layer test pieces 400 of different types in the same real gas environment is improved. Meanwhile, the area utilization rate of the output end of the test engine unit 100 is improved, that is, more gas channels 102 can be arranged under the condition that the area of the output end of the test engine unit 100 is fixed.
6. The gas channels 102 are arranged in a manner that the distances between the gas channels 102 and the central point of the output end of the test engine unit 100 are equal, so that the gas channels 102 are located on the circumference with the central point of the output end as the center of a circle, the environment difference possibly existing in the heat insulation layer test pieces 400 is reduced, and the ablation performance comparison and examination precision of the heat insulation layer test pieces 400 in different types under the same real gas environment is improved.
7. The gas channels 102 adopt a layout mode that the distances between every two adjacent gas channels 102 are equal, so that the gas channels 102 are uniformly distributed at the output end of the test engine unit 100, the possible environmental differences of the heat-insulating layer test pieces 400 are reduced, and the ablation performance comparison and assessment accuracy of the heat-insulating layer test pieces 400 of different types in the same real gas environment is improved. For example, the gas passages 102 are distributed in a matrix, or in a honeycomb, etc.
8. One gas channel 102 of the gas channels 102 is arranged at the center point of the output end of the test engine unit 100, which is beneficial to the layout and positioning of all the gas channels 102, for example: the gas channels 102 are distributed in a matrix or honeycomb manner; on the other hand, it is also advantageous to improve the area utilization of the output end of the test engine unit 100.
Those skilled in the art will understand that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. in this application indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the application and simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the application.
The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless otherwise specified.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
In the description herein, particular features, structures, materials, or characteristics may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing is only a partial embodiment of the present application, and it should be noted that, for those skilled in the art, several modifications and decorations can be made without departing from the principle of the present application, and these modifications and decorations should also be regarded as the protection scope of the present application.
Claims (10)
1. A single-side multi-outlet testing device for a heat insulating layer of a rocket engine is characterized by comprising:
a test engine unit having a combustion chamber and an output; the output end is provided with at least two gas channels, and two ends of each gas channel are respectively communicated with the combustion chamber and the external environment of the test engine unit; the combustion chamber is used for generating a real gas environment simulating a rocket engine;
one end of each tail pipe unit is detachably connected with the test engine unit and is communicated with the corresponding gas channel, and the tail pipe units are used for correspondingly bearing different types of heat insulation layer test pieces and forming the same test environment;
and each spray pipe unit is detachably connected to one end, far away from the test engine unit, of the corresponding tail pipe unit.
2. The single-sided multi-tap testing apparatus of claim 1, wherein the tailpipe unit comprises: the tail pipe comprises a tail pipe cylinder, a first connecting flange and a second connecting flange, wherein the first connecting flange and the second connecting flange are respectively positioned at two ends of the tail pipe cylinder;
the inner wall of the tail pipe cylinder is detachably connected with the heat insulation layer test piece;
the first connecting flange is detachably connected with the test engine unit;
the second connecting flange is detachably connected with the spray pipe unit.
3. The single-side multi-outlet testing device according to claim 1 or 2, wherein at least two gas passages surround a center point of the output end.
4. The single-side multi-outlet testing device as claimed in claim 3, wherein the distances between the at least two gas passages and the center point of the output end are equal;
and/or the distance between every two adjacent gas channels is equal.
5. The single-side multi-outlet testing device as claimed in claim 1 or 2, wherein one of the at least two gas passages is located at a central point of the output end.
6. The single-side multi-outlet testing device according to claim 1 or 2, wherein the nozzle unit comprises: the nozzle comprises a nozzle barrel, a nozzle diffusion section and a throat liner;
the outer wall of the spray pipe cylinder body is detachably connected with the inner wall of the gas channel;
the inner wall of the spray pipe barrel is detachably connected with the outer wall of the spray pipe diffusion section;
the inner wall of the nozzle diffusion section is detachably connected with the throat insert.
7. The single-sided multi-output testing device according to claim 1 or 2, wherein the test engine unit comprises: the combustor comprises a combustor shell, a sealing cover plate and a flow guide structure;
the sealing cover plate is connected with one end of the combustion chamber shell;
the flow guide structure comprises: a baffle and a bottom plate; the guide plate is of an annular structure with unequal calibers at two ends, the first end of the guide plate is connected with the other end of the combustion chamber shell, the second end of the guide plate is connected with the bottom plate, and the caliber of the first end is larger than that of the second end;
the cover plate, the combustion chamber shell, the flow guide plate and the bottom plate enclose to form the combustion chamber; the gas channel is arranged on the bottom plate.
8. The single-sided multi-output testing device according to claim 7, wherein the flow guide structure further comprises: measuring the adapter;
the measuring adapter is arranged on the outer wall of the guide plate and used for mounting a pressure sensor;
the pressure sensor is used for monitoring the working pressure of the combustion chamber.
9. The single-sided multi-outlet test device of claim 7, wherein the test engine unit comprises at least one of the following features:
the sealing cover plate is detachably connected with one end of the combustion chamber shell;
the first end of the guide plate is detachably connected with the other end of the combustion chamber shell;
the second end of the guide plate is detachably connected with the bottom plate.
10. The single-sided multi-outlet test device of claim 7, wherein the test engine unit further comprises: a thermally insulating structure; the insulation structure includes at least one of the following features:
the heat insulation structure is arranged on one side of the cover plate close to the bottom plate;
the heat insulation structure is arranged on the inner wall of the combustion chamber shell;
the heat insulation structure is arranged on the inner wall of the guide plate;
the heat insulation structure is arranged on one side of the bottom plate close to the cover plate.
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6711901B1 (en) * | 2000-01-21 | 2004-03-30 | Alliant Techsystems Inc. | Rocket motor nozzle assemblies having vacuum plasma-sprayed refractory metal shell throat inserts, methods of making, and rocket motors including same |
| CN103967653A (en) * | 2014-04-28 | 2014-08-06 | 北京航空航天大学 | Axial injection end combustion solid-liquid rocket engine structure |
| CN105527370A (en) * | 2015-11-03 | 2016-04-27 | 西北工业大学 | Apparatus for simulating insulation ablation under condition of particle deposition in cavity in back wall of submerged nozzle |
| CN109630321A (en) * | 2019-01-08 | 2019-04-16 | 北京理工大学 | Condensed-phase product collection device in solid propellant rocket plume based on long tail pipe |
| CN111122767A (en) * | 2019-11-29 | 2020-05-08 | 南京理工大学 | Detachable solid rocket engine jet pipe throat lining ablation test device |
| CN112098100A (en) * | 2020-08-28 | 2020-12-18 | 西北工业大学 | Solid engine heat insulation layer ablation performance parallel examination test device |
| CN112555058A (en) * | 2021-02-19 | 2021-03-26 | 星河动力(北京)空间科技有限公司 | Test device for nozzle throat lining of rocket engine |
-
2021
- 2021-11-02 CN CN202111290071.6A patent/CN114166991A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6711901B1 (en) * | 2000-01-21 | 2004-03-30 | Alliant Techsystems Inc. | Rocket motor nozzle assemblies having vacuum plasma-sprayed refractory metal shell throat inserts, methods of making, and rocket motors including same |
| CN103967653A (en) * | 2014-04-28 | 2014-08-06 | 北京航空航天大学 | Axial injection end combustion solid-liquid rocket engine structure |
| CN105527370A (en) * | 2015-11-03 | 2016-04-27 | 西北工业大学 | Apparatus for simulating insulation ablation under condition of particle deposition in cavity in back wall of submerged nozzle |
| CN109630321A (en) * | 2019-01-08 | 2019-04-16 | 北京理工大学 | Condensed-phase product collection device in solid propellant rocket plume based on long tail pipe |
| CN111122767A (en) * | 2019-11-29 | 2020-05-08 | 南京理工大学 | Detachable solid rocket engine jet pipe throat lining ablation test device |
| CN112098100A (en) * | 2020-08-28 | 2020-12-18 | 西北工业大学 | Solid engine heat insulation layer ablation performance parallel examination test device |
| CN112555058A (en) * | 2021-02-19 | 2021-03-26 | 星河动力(北京)空间科技有限公司 | Test device for nozzle throat lining of rocket engine |
Non-Patent Citations (1)
| Title |
|---|
| 李江, 何国强, 陈剑, 刘洋, 娄永春: "高过载条件下绝热层烧蚀实验方法研究 (Ⅱ)收缩管聚集法", 推进技术, no. 03, pages 196 - 198 * |
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