CN111458366A - Ablation thermal protection system structure pneumatic heat/heat transfer coupling analysis method - Google Patents
Ablation thermal protection system structure pneumatic heat/heat transfer coupling analysis method Download PDFInfo
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Abstract
The invention relates to a pneumatic heat/heat transfer coupling analysis method for an ablation heat protection system structure, which comprises the following steps: acquiring pneumatic thermal environment data of an ablation thermal protection area; preparing an ablative material layered sensor; carrying out a flat plate thermal examination test with a layered temperature/ablation sensor based on an electric arc wind tunnel to obtain the temperature inside the material and the pyrolysis thickness change rule under the test condition; carrying out identification research on high-temperature thermophysical parameters of the material considering ablation effect to obtain the temperature-dependent change relationship of thermophysical parameters such as thermal conductivity and specific heat capacity of the ablation material under a dynamic pneumatic heating condition; and carrying out the pneumatic heat/heat transfer coupling analysis of the ablation thermal protection system according to the obtained identification data and the obtained pneumatic heat environment data of the ablation thermal protection area. The method can effectively solve the problem of accurate evaluation of the structural thermal response of the ablation thermal protection system.
Description
Technical Field
The invention belongs to the technical field of ablation thermal protection structure thermal response analysis and evaluation, and relates to a pneumatic thermal/heat transfer coupling analysis method of an ablation thermal protection system.
Background
The ablation type composite material can generate pyrolysis and ablation reactions under the action of pneumatic heating, the molecular polymer in the original layer material generates pyrolysis reactions, the pyrolysis reactions generate a large amount of gas mainly comprising H2, CO, H2O, methane and the like, and a porous carbonization layer structure is finally formed; along with the proceeding of the pyrolysis reaction, a large amount of pyrolysis gas is gathered and diffused to be injected into a boundary layer through the porous carbon layer structure, on the other hand, the pyrolysis gas plays a role in cooling the porous carbon layer structure, on the other hand, the thickness of the boundary layer of the material surface is increased, and the pneumatic heat exchange and the shearing force, namely the thermal blocking effect, are reduced; meanwhile, the carbonized layer can react with oxidizing components, and the surface of the material is ablated and retreated while the injection heat flow of the surface is increased. The oxidation ablation phenomenon of the ablation thermal protection system under the action of pneumatic heating is a complex physical and chemical process of multi-field coupling such as flowing, heat transfer, mass transfer, chemical reaction and the like, significant coupling interaction exists between the structural thermal response and the pneumatic heating of the material, the pneumatic heating of the surface of the material can be influenced by pyrolysis gas injection, oxidation ablation of a carbonized layer and the like, the pyrolysis and ablation rate of the material can be influenced by the pneumatic heating, and the structural thermal response analysis difficulty is improved by the coupling effect between the pyrolysis gas injection and the pneumatic heating.
In addition, along with the complex physicochemical processes of material pyrolysis/ablation, the thermophysical parameters of the ablation material, such as thermal conductivity and specific heat capacity, change nonlinearly, and the change rule of the thermophysical parameters is closely related to pneumatic heating conditions, so that the traditional methods widely adopted at present, such as a transient laser pulse method and a thermal probe method, can only be applied to non-ablative materials, cannot reflect the influence of the complex physicochemical process in the dynamic ablation process on high-temperature effective thermophysical parameters, and the obtained thermophysical parameters of the material cannot meet the requirement of the refined design of an ablation-type thermal protection system of a hypersonic aircraft.
The complicated physical and chemical processes of the ablation material under the action of pneumatic heating and the nonlinear change of thermophysical parameters make the precise evaluation of the structural thermal response of the ablation thermal protection system have great technical difficulty, and a corresponding pneumatic thermal/heat transfer coupling analysis method needs to be developed in a targeted manner to support the design of the ablation thermal protection system of a high-speed aircraft.
Disclosure of Invention
The invention aims to overcome the defects of the existing ablation thermal protection system thermal response analysis technology, adopts a means of combining ground test, parameter identification and theoretical analysis to establish a reliable ablation thermal protection system structure thermal response analysis method, and achieves the purpose of improving the ablation thermal protection system structure thermal response prediction precision by developing a flat arc wind tunnel thermal assessment test with a layered temperature/ablation sensor and considering ablation effect material high-temperature thermophysical property parameter identification.
The technical solution of the invention is as follows:
according to one aspect of the invention, a layered temperature and ablation sensor is provided, wherein a sensitive core element of the layered temperature and ablation sensor adopts an ablation material consistent with a thermal protection structure of an elastomer, the sensitive core element of the layered temperature sensor comprises a plurality of temperature measuring points, the sensitive core element of the layered ablation sensor comprises a plurality of voltage measuring points, and the temperature measuring points and the voltage measuring points are located at different depths.
Further, the principle of setting the positions of the temperature measuring points is as follows: determined according to the internal temperature of interest.
Further, the number of the temperature measurement points is selected according to the following principle: in a one-dimensional heat transfer system, the sum of the number of temperature measurement points and the number of known boundary conditions is greater than 3.
Further, the number and the positions of the voltage measuring points are selected according to the ablation positions needing attention.
According to another aspect of the invention, a method for analyzing the aerodynamic heat/heat transfer coupling of an ablation thermal protection system structure is provided, which comprises the following steps:
carrying out aerodynamic thermal analysis of the high-speed aircraft along the trajectory to obtain aerodynamic thermal environment data of an ablation thermal protection area;
preparing an ablative material layered sensor, which comprises a layered temperature sensor and a layered ablation sensor;
placing the prepared layered temperature sensor and the layered ablation sensor in a test model of an ablation material flat arc wind tunnel examination test, developing a flat thermal examination test with the layered temperature/ablation sensor based on the arc wind tunnel, and obtaining the change rule of the temperature and the pyrolysis thickness in the material under the test condition;
according to the obtained change rule of the temperature and the pyrolysis thickness in the material, carrying out identification research on the high-temperature thermophysical parameters of the material considering the ablation effect to obtain the change relation of the thermophysical parameters such as the thermal conductivity, the specific heat capacity and the like of the ablation material along with the temperature under the dynamic pneumatic heating condition;
and carrying out the pneumatic heat/heat transfer coupling analysis of the ablation thermal protection system according to the obtained identification data and the obtained pneumatic heat environment data of the ablation thermal protection area.
Further, the incoming flow state of the flat arc wind tunnel examination test is determined according to the aerodynamic thermal environment data of the high-speed aircraft.
Compared with the prior art, the invention has the beneficial effects that:
according to the invention, the high-temperature thermophysical parameters of the ablation material under the condition close to real dynamic heating are obtained by developing an electric arc wind tunnel thermal examination test with a layered temperature/ablation sensor and material high-temperature thermophysical parameter identification research considering ablation effect, and the pneumatic thermal/heat transfer coupling analysis of the ablation thermal protection system is developed on the basis of the high-temperature thermophysical parameters, so that the problem of accurate evaluation of the structural thermal response of the ablation thermal protection system can be effectively solved.
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The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 illustrates a schematic diagram of a layered temperature/ablation sensor flat panel test piece configuration provided in accordance with an embodiment of the present invention;
FIG. 2 is a schematic diagram illustrating an analysis method for aerodynamic thermal/thermal transfer coupling of an ablation thermal protection system structure according to an embodiment of the invention;
FIG. 3 shows an installation schematic diagram of an electric arc wind tunnel flat plate assessment test piece provided by the embodiment of the invention.
Identification in the drawings:
1. a layered temperature sensor; 2. a layered ablation sensor.
Detailed Description
The present invention will be described in detail with reference to the following examples and accompanying drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
According to one embodiment, as shown in fig. 1, a layered temperature and ablation sensor is provided, in which a sensitive core element of the layered temperature and ablation sensor is made of an ablation material conforming to a thermal protection structure of an elastomer, the sensitive core element of the layered temperature sensor comprises a plurality of temperature measurement points, the sensitive core element of the layered ablation sensor comprises a plurality of voltage measurement points, and the temperature measurement points and the voltage measurement points are located at different depths.
Further in one embodiment, the principle of setting the positions of the temperature measuring points is as follows: determined according to the internal temperature of interest.
Further in one embodiment, the number of temperature measurement points is selected as follows: in a one-dimensional heat transfer system, the sum of the number of temperature measurement points and the number of known boundary conditions is greater than 3.
Further in one embodiment, the number and location of voltage measurement points is selected based on the ablation location that needs to be addressed.
As shown in fig. 2, according to one embodiment, there is provided an ablation thermal protection system structure aerodynamic heat/heat transfer coupling analysis method, comprising the steps of:
the method comprises the steps that firstly, the aerodynamic thermal analysis of a high-speed aircraft along a trajectory is carried out to obtain the aerodynamic thermal environment data of an ablation thermal protection area, in one embodiment, the aerodynamic thermal analysis of the high-speed aircraft along the trajectory is carried out by adopting an aerodynamic thermal engineering calculation method or a CFD numerical simulation method, and the aerodynamic thermal environment data of a projectile ablation thermal protection part, including heat flow, recovery enthalpy, pressure and shearing force, are obtained;
and step two, preparing an ablative material layered sensor, wherein the ablative material layered sensor comprises a layered temperature sensor and a layered ablative sensor, the two layered sensors are prepared by adopting materials consistent with the ablation thermal protection structure of the projectile body, and the size of a sensitive core element of the sensor is consistent with the thickness of the ablative material on the surface of the projectile body.
The method comprises the following steps that a plurality of thermocouples are arranged inside a sensitive core element of a layered temperature sensor to obtain the change rule of the internal temperature of a material, the arrangement positions of the thermocouples are determined according to the concerned internal temperature, the thermocouple range and the type are selected according to the peak temperature of the material of a measured part, in one embodiment, a K-type thermocouple can be selected as a measuring point with the peak temperature below 1300 ℃, and a platinum-rhodium thermocouple can be selected as a measuring point with the peak temperature above 1300 ℃;
the number of the measuring points in the layered temperature sensor is determined according to the known number of the boundary conditions, and in the one-dimensional heat transfer system, the sum of the number of the temperature measuring points and the known number of the boundary conditions is more than 3. In one embodiment, if all heat transfer boundary conditions of the one-dimensional heat transfer system are unknown, the number of temperature measuring points is not less than 3, the temperature history of two measuring points closest to the boundary is used as the boundary condition, and the temperatures of other measuring points are used as identification conditions; if all heat transfer boundary conditions of the one-dimensional heat transfer system are known, the number of temperature measuring points is not less than 1, and the temperature of the measuring points is used as an identification condition; if the one-dimensional heat transfer system can only determine 1 boundary condition, the number of temperature measuring points is not less than 2, the temperature history of the measuring point closest to the unknown boundary is used as the boundary condition, and the temperatures of other measuring points are used as identification conditions; in other embodiments, other temperature measurement point distribution schemes may be used as desired.
A plurality of voltage measuring points are arranged in a sensitive core element of a layered ablation sensor to obtain the pyrolysis thickness of an ablation material, when the positions of the voltage measuring points are pyrolyzed and carbonized, the material is changed from an insulating state to a conducting state, the change rule of the pyrolysis thickness is judged according to the change of voltage, and the number and the positions of the voltage measuring points are determined according to the ablation positions needing attention.
And step three, as shown in fig. 3, placing the prepared ablation material layered sensor in a test model of an ablation material flat arc wind tunnel examination test, wherein the incoming flow state of the flat arc wind tunnel examination test is determined according to the aerodynamic thermal environment data of the high-speed aircraft. A flat plate thermal examination test with a layered temperature/ablation sensor is carried out based on an electric arc wind tunnel to obtain the change rule of the temperature and the pyrolysis thickness in the material under the test condition,
in one embodiment, the layered sensor is placed in the central area of the test model, the end of the layered sensor is flush with the surface of the test model, the incoming flow state of the test is designed according to the thermal environment data obtained in the step one, a plurality of test steps are adopted to simulate the pneumatic heating environment of a full trajectory, and the coverage of parameters such as temperature, pressure, shearing force and the like on the surface of the test piece in the test state on the flight state is ensured through thermal environment calibration, which is a known technology in the field;
and step four, developing material high-temperature thermophysical property parameter identification research considering ablation effect according to the change rule of the temperature and the pyrolysis thickness in the material in the step three, obtaining the change relation of thermophysical property parameters such as thermal conductivity, specific heat capacity and the like of the ablation material along with the temperature under the dynamic pneumatic heating condition, and obtaining the thermophysical property parameters of the composite material for guiding the heat insulation design. The identification of the high-temperature thermophysical parameters considering the ablation effect is a typical variable-geometry domain heat conduction inverse problem, the variable-geometry domain heat conduction inverse problem considering the material pyrolysis reaction, pyrolysis gas injection and ablation regression is generally converted into an optimization problem to solve the problem, the high-temperature thermophysical parameters of the ablation material are inverted through an efficient optimization algorithm, and in one embodiment, the high-temperature thermophysical parameters of the ablation material can be inverted according to the method provided in the inversion of Thermal Properties of ablation anchors [ J ]. Numerical HeatTransfer, Part B,2009,56: 478-.
In one embodiment, a plurality of temperature measuring points are arranged in the material, the identifying measuring points can be flexibly selected according to the temperature process of the actual measuring points, and the high-temperature thermophysical property parameters of the ablation material in the temperature zone range concerned in the dynamic thermal response process can be obtained according to the boundary conditions and the identifying conditions which need to be met by the identification of the high-temperature thermophysical property parameters of the ablation material, so that the accuracy of the high-temperature thermophysical property parameters is improved.
And step five, carrying out pneumatic heat/heat transfer coupling analysis on the ablation thermal protection system according to the identification data obtained in the step four and the pneumatic thermal environment data of the ablation thermal protection area obtained in the step one.
The aerodynamic heat data is loaded on the surface of the material by considering the factors of cold-hot wall heat flow conversion, thermal blocking effect, surface radiation, oxidation heat release of a carbonized layer and the like, and the loading heat flow on the surface of the material is as follows:
wherein: qinLoading the surface of the material with heat flow;
is a hot wall heat flow;
is the thermal blockage coefficient, where qcIs a cold wall heat flow; h iscTo recover enthalpy; h isTwIs the wall enthalpy; h is280kWall enthalpy at a wall temperature of 280 k;
The structure thermal response analysis obtains the dynamic change rule of the temperature distribution, the pyrolysis thickness and the ablation retreat amount of the ablation thermal protection system by considering the influence mechanism of the factors such as material pyrolysis, surface ablation retreat, heat conduction, pyrolysis gas injection and flowing in a carbonization layer on the temperature distribution, and supports the design of heat insulation prevention of the high-speed aircraft.
Through the steps, the problem of accurate evaluation of the structural thermal response of the ablation thermal protection system under the action of pneumatic heating can be solved.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. A layered temperature and ablation sensor is characterized in that a sensitive core element of the layered temperature and ablation sensor is made of an ablation material consistent with a thermal protection structure of a projectile body, the sensitive core element of the layered temperature sensor comprises a plurality of temperature measurement points, the sensitive core element of the layered ablation sensor comprises a plurality of voltage measurement points, and the temperature measurement points and the voltage measurement points are located at positions with different depths.
2. A layered temperature and ablation sensor according to claim 1, wherein: the position setting principle of the temperature measuring points is as follows: determined according to the internal temperature of interest.
3. A layered temperature and ablation sensor according to claim 1, wherein: the number of the temperature measuring points is selected according to the following principle: in a one-dimensional heat transfer system, the sum of the number of temperature measurement points and the number of known boundary conditions is greater than 3.
4. A layered temperature and ablation sensor according to claim 1, wherein: the number and the positions of the voltage measuring points are selected according to the ablation positions needing attention.
5. An analysis method for the aerodynamic thermal/heat transfer coupling of an ablation thermal protection system structure according to claims 1-4, characterized by comprising the following steps:
carrying out aerodynamic thermal analysis of the high-speed aircraft along the trajectory to obtain aerodynamic thermal environment data of an ablation thermal protection area;
preparing an ablative material layered sensor, which comprises a layered temperature sensor and a layered ablation sensor;
placing the prepared layered temperature sensor and the layered ablation sensor in a test model of an ablation material flat arc wind tunnel examination test, developing a flat thermal examination test with the layered temperature/ablation sensor based on the arc wind tunnel, and obtaining the change rule of the temperature and the pyrolysis thickness in the material under the test condition;
according to the obtained change rule of the temperature and the pyrolysis thickness in the material, carrying out identification research on the high-temperature thermophysical parameters of the material considering the ablation effect to obtain the change relation of the thermophysical parameters such as the thermal conductivity, the specific heat capacity and the like of the ablation material along with the temperature under the dynamic pneumatic heating condition;
and carrying out the pneumatic heat/heat transfer coupling analysis of the ablation thermal protection system according to the obtained identification data and the obtained pneumatic heat environment data of the ablation thermal protection area.
6. The method for analyzing the aerodynamic heat/heat transfer coupling of the ablation thermal protection system structure as claimed in claim 5, wherein: the incoming flow state of the flat arc wind tunnel examination test is determined according to the aerodynamic thermal environment data of the high-speed aircraft.
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| CN112083030A (en) * | 2020-08-19 | 2020-12-15 | 北京机电工程研究所 | Heat transfer model correction method for thermal protection material |
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