Total temperature and total pressure stagnation cavity design method under ultra-high temperature condition and total temperature and total pressure stagnation cavity

Abstract

The invention provides a total temperature and total pressure stagnation cavity design method under an ultra-high temperature condition and a total temperature and total pressure stagnation cavity, and the method comprises the steps: firstly, combining design constraints and performance index requirements, and preliminarily determining the layout of an air inlet and exhaust flow channel of a sensor and the self assembly relation of the sensor; determining a structural material of the stagnation cavity according to performance index requirements and the preliminarily determined self-assembly relation of the sensor, acquiring physical parameters of the stagnation cavity, preliminarily determining the structure of the stagnation cavity based on the preliminarily determined air inlet and outlet runner layout of the sensor and the self-assembly relation of the sensor, and determining the structure of the stagnation cavity based on the three-dimensional model of the stagnation cavity and the physical parameters. Obtaining a sensor performance analysis result through CFD and theoretical calculation, comparing the sensor performance analysis result with a corresponding performance index, and carrying out the repeated iteration adjustment of the stagnation cavity structure according to the difference until each performance of the stagnation cavity meets the index requirements. According to the technical scheme, the technical problem that in the prior art, a high-recovery-rate stagnation cavity cannot be designed and obtained under the ultra-high-temperature condition is solved.

Description

Technical Field

[0001] The present invention relates to the field of total temperature sensing technology, and in particular to a total temperature and total pressure stagnation cavity design method and a total temperature and total pressure stagnation cavity under ultra-high temperature conditions. Background Art

[0002] As a flow field stagnation parameter, total temperature is a key parameter supporting the research and development of supersonic vehicle engine control, flight control, structural thermal protection, etc., especially in the control of air-breathing ramjet engines. High-precision real-time measurement of total temperature parameters is a prerequisite for ensuring safe, stable and efficient flight of the aircraft. The sensor stagnation cavity is the core structure to ensure sufficient stagnation of airflow and reduce velocity error and radiation error. At present, most total temperature sensors at home and abroad are mainly used in subsonic aircraft and ground wind tunnel test scenarios. The external dimensions are less constrained, and conventional intake and exhaust structures can meet the design requirements of the stagnation cavity. However, for total temperature sensors under hypersonic conditions, it is necessary to consider stealth, wave transmission, total temperature and total pressure integration, etc., and the installation and use of the sensor does not affect the aerodynamic shape. Therefore, compared with subsonic aircraft and ground test platforms, the stagnation cavity structure design of ultra-high temperature total temperature sensors is more complicated.

[0003] As mentioned above, for hypersonic vehicles, it is necessary to combine the interface requirements and size constraints on the aircraft, rationally design the sensor stop structure, carry out design work such as total temperature and total pressure integrated design, flow path design, intake and exhaust design, and installation combination design, and finally realize a total temperature and total pressure integrated stop structure with a high recovery rate. However, there is currently no design method for a high recovery rate stop cavity under ultra-high temperature conditions. Summary of the invention

[0004] The present invention provides a total temperature and total pressure stagnation cavity design method under ultra-high temperature conditions and a total temperature and total pressure stagnation cavity, which can solve the technical problem in the prior art that a high recovery rate stagnation cavity cannot be designed under ultra-high temperature conditions.

[0005] According to one aspect of the present invention, a method for designing a total temperature and total pressure stagnation cavity under ultra-high temperature conditions is provided, the method comprising:

[0006] S1, determine the design constraints and performance index requirements of the sensor, and preliminarily determine the layout of the sensor's inlet and exhaust flow channels and the sensor's own assembly relationship based on the design constraints;

[0007] S2, determining the structural material of the stagnation cavity according to the performance index requirements and the preliminarily determined assembly relationship of the sensor itself, and obtaining the physical property parameters of the structural material;

[0008] S3, preliminarily determining the stagnation cavity structure based on the preliminarily determined sensor intake and exhaust flow path layout and the sensor's own assembly relationship;

[0009] S4, establishing a three-dimensional model of the stagnation cavity according to the stagnation cavity structure;

[0010] S5, based on the stagnation cavity three-dimensional model and physical property parameters, the performance result of the current stagnation cavity three-dimensional model is obtained through CFD simulation analysis, and compared with the performance index requirements. If the performance index requirements are not met, go to S6; if the performance index requirements are met, go to S7;

[0011] S6, adjusting the current stagnation cavity three-dimensional model and returning to S5;

[0012] S7, taking the current stagnation cavity three-dimensional model as the final model, and determining the stagnation cavity manufacturing process according to the final model.

[0013] Furthermore, when the layout of the inlet and exhaust flow passages of the sensor is preliminarily determined according to the design constraints, the inlet pressure is higher than the exhaust pressure.

[0014] Furthermore, the design constraints include: size constraints, installation requirements and integration requirements, and the performance index requirements include temperature measurement range requirements, temperature measurement deviation requirements, dynamic response time constant requirements, recovery rate requirements and maximum stress requirements.

[0015] Furthermore, the size constraint is that the maximum outer diameter of the sensor projected along the axis of the missile is no more than 20 mm, the installation requirement is that the size of the sensor installation hole reserved on the antenna cover is 12 mm, and the integration requirement is the integrated collection of total temperature and total pressure in the sensor.

[0016] Furthermore, the temperature measurement range is required to be -50°C to 1000°C, the temperature measurement deviation is required to be no more than 4% of the measured value, and the dynamic response time constant is required to be no higher than 1s.

[0017] Furthermore, the layout of the sensor inlet and exhaust flow channels is preliminarily determined as follows: the total pressure air intake hole is arranged at the center of the front end ball head, the total temperature air intake hole is arranged on the side of the total pressure hole, the center line connecting the total pressure air intake hole and the total temperature air intake hole is in a horizontal state, the total temperature exhaust hole is arranged 4mm away from the center of the front end ball head, the diameter of the total pressure air intake hole is not less than 1mm, the diameter of the total temperature air intake hole is 2mm~3mm, and the diameter of the total temperature exhaust hole is 1.5mm~2mm.

[0018] According to another aspect of the present invention, a total temperature and total pressure stagnation cavity is provided. The total temperature and total pressure stagnation cavity is a total temperature and total pressure stagnation cavity designed by the total temperature and total pressure stagnation cavity design method under ultra-high temperature conditions proposed in the present invention.

[0019] By applying the technical solution of the present invention, a design method for a total temperature and total pressure stagnation cavity under ultra-high temperature conditions and a total temperature and total pressure stagnation cavity are provided. The method first combines the design constraints and performance index requirements to preliminarily determine the sensor intake and exhaust flow path layout and the sensor's own assembly relationship, and then determines the structural material of the stagnation cavity according to the performance index requirements and the preliminarily determined sensor's own assembly relationship, and obtains its physical property parameters. Then, based on the preliminarily determined sensor intake and exhaust flow path layout and the sensor's own assembly relationship, the stagnation cavity structure is preliminarily determined. Then, based on the three-dimensional model of the stagnation cavity structure and the physical property parameters, the sensor performance analysis results are obtained through CFD and theoretical calculations, which are compared with the corresponding performance indicators. According to the differences, the stagnation cavity structure is repeatedly adjusted iteratively until all performances of the stagnation cavity meet the index requirements. This method can guide the design of the total temperature and total pressure sensor stagnation cavity under ultra-high temperature and strong volume constraint conditions, and finally obtain a stagnation cavity structure with a high recovery rate. It is simple and practical, easy to implement and effective, and has strong feasibility. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The included drawings are used to provide a further understanding of the embodiments of the present invention, which constitute a part of the specification, are used to illustrate the embodiments of the present invention, and together with the text description, explain the principles of the present invention. Obviously, the drawings in the following description are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0021] Figure 1 A schematic flow chart of a total temperature and total pressure stagnation cavity design method under ultra-high temperature conditions provided in accordance with a specific embodiment of the present invention is shown;

[0022] Figure 2 A schematic diagram showing size constraints and installation requirements provided according to a specific embodiment of the present invention is shown;

[0023] Figure 3 A schematic diagram of the layout of the inlet and exhaust flow passages of a sensor provided according to a specific embodiment of the present invention is shown. DETAILED DESCRIPTION

[0024] It should be noted that, in the absence of conflict, the embodiments in this application and the features in the embodiments can be combined with each other. The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present invention and its application or use. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0025] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0026] Unless otherwise specifically stated, the relative arrangement of the parts and steps described in these embodiments, numerical expressions and numerical values ​​do not limit the scope of the present invention. At the same time, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to the actual proportional relationship. The technology, method and equipment known to ordinary technicians in the relevant field may not be discussed in detail, but in appropriate cases, the technology, method and equipment should be regarded as a part of the authorization specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0027] According to a specific embodiment of the present invention, a method for designing a total temperature and total pressure stagnation cavity under ultra-high temperature conditions is provided, the method comprising:

[0028] S1, determine the design constraints and performance index requirements of the sensor, and preliminarily determine the layout of the sensor's inlet and exhaust flow channels and the sensor's own assembly relationship based on the design constraints;

[0029] S2, determining the structural material of the stagnation cavity according to the performance index requirements and the preliminarily determined assembly relationship of the sensor itself, and obtaining the physical property parameters of the structural material;

[0030] S3, preliminarily determining the stagnation cavity structure based on the preliminarily determined sensor intake and exhaust flow path layout and the sensor's own assembly relationship;

[0031] S4, establishing a three-dimensional model of the stagnation cavity according to the stagnation cavity structure;

[0032] S5, based on the stagnation cavity three-dimensional model and physical property parameters, the performance result of the current stagnation cavity three-dimensional model is obtained through CFD simulation analysis, and compared with the performance index requirements. If the performance index requirements are not met, go to S6; if the performance index requirements are met, go to S7;

[0033] S6, adjusting the current stagnation cavity three-dimensional model and returning to S5;

[0034] S7, taking the current stagnation cavity three-dimensional model as the final model, and determining the stagnation cavity manufacturing process according to the final model.

[0035] By applying this configuration, a design method for a total temperature and total pressure stagnation cavity under ultra-high temperature conditions is provided. The method first combines the design constraints and performance index requirements to preliminarily determine the sensor intake and exhaust flow path layout and the sensor's own assembly relationship, and then determines the structural material of the stagnation cavity according to the performance index requirements and the preliminarily determined sensor's own assembly relationship, and obtains its physical property parameters. Then, based on the preliminarily determined sensor intake and exhaust flow path layout and the sensor's own assembly relationship, the stagnation cavity structure is preliminarily determined. Then, based on the 3D model and physical property parameters of the stagnation cavity structure, the sensor performance analysis results are obtained through CFD and theoretical calculations, which are compared with the corresponding performance indicators. According to the differences, the stagnation cavity structure is repeatedly adjusted iteratively until all performances of the stagnation cavity meet the index requirements. This method can guide the design of the total temperature and total pressure sensor stagnation cavity under ultra-high temperature and strong volume constraint conditions, and finally obtain a stagnation cavity structure with a high recovery rate. It is simple and practical, easy to implement and effective, and has strong feasibility. Compared with the prior art, the technical solution of the present invention can solve the technical problem that a high recovery rate stagnation cavity cannot be designed under ultra-high temperature conditions in the prior art.

[0036] Furthermore, in the embodiment of the present invention, the design constraints include: size constraints, installation requirements and integration requirements, and the performance index requirements include temperature measurement range requirements, temperature measurement deviation requirements, dynamic response time constant requirements, recovery rate requirements and maximum stress requirements. As a specific embodiment of the present invention, the size constraint is that the maximum outer diameter of the sensor projected along the axis of the missile is not greater than 20mm, the installation requirement is that the size of the sensor installation hole reserved on the antenna cover is 12mm, and the integration requirement is the integrated collection of total temperature and total pressure in the sensor. The temperature measurement range is required to be -50℃~1000℃, the temperature measurement deviation is required to be no more than 4% of the measured value, and the dynamic response time constant is required to be no higher than 1s.

[0037] In addition, in the embodiment of the present invention, when the layout of the inlet and exhaust flow passages of the sensor is preliminarily determined according to the design constraints, the inlet pressure is higher than the exhaust pressure.

[0038] Based on the above embodiments, in the embodiments of the present invention, the layout of the inlet and exhaust flow channels of the sensor is preliminarily determined as follows: the total pressure air intake hole is arranged at the center of the front end ball head, the total temperature air intake hole is arranged on the side of the total pressure hole, the center line connecting the total pressure air intake hole and the total temperature air intake hole is in a horizontal state, the total temperature exhaust hole is arranged 4mm away from the center of the front end ball head, the diameter of the total pressure air intake hole is not less than 1mm, the diameter of the total temperature air intake hole is 2mm~3mm, and the diameter of the total temperature exhaust hole is 1.5mm~2mm.

[0039] In summary, the main steps of the total temperature and total pressure stagnation cavity design method under ultra-high temperature conditions provided by the present invention can be referred to Figure 1 The specific implementation of each step has been described in detail in the above embodiments, and will not be described in detail here. It should be known to those skilled in the art that this example is only an application mode to help understand the total temperature and total pressure stagnation cavity design method under ultra-high temperature conditions provided by the present invention, and does not limit it in any way.

[0040] In order to facilitate a clearer understanding of the total temperature and total pressure stagnation cavity design method under ultra-high temperature conditions provided by the present invention, the above-mentioned processes will be described in detail below using practical application examples. Relevant technical personnel in the field should know that this example is only for the purpose of facilitating a clearer understanding of the total temperature and total pressure stagnation cavity design method under ultra-high temperature conditions provided by the present invention, and does not impose any technical limitation on it.

[0041] like Figure 1 As shown, the overall idea of ​​the present invention is: first, combining the design constraints (mainly including size constraints, installation requirements, integration requirements, etc.) and performance index requirements, a preliminary stagnation cavity structure design scheme is proposed, and the sensor recovery rate, time constant and maximum stress are obtained through CFD and theoretical calculations, and then compared with the corresponding performance indicators to check the indicator closure. For unclosed items, the sensor structure is changed according to the difference between the calculation results and the indicator requirements, and it is iterated repeatedly until the stagnation cavity recovery rate, time constant and maximum stress meet the indicator requirements. Specifically, the following steps are included:

[0042] The first step is to collect and organize the design constraints and performance index requirements of the sensor. The design constraints mainly include size constraints, installation requirements, integration requirements, etc. Observe the characteristics of size constraints and installation requirements, and preliminarily conceive the layout of the sensor's inlet and exhaust flow channels and the sensor's own assembly relationship. The flow channel layout needs to ensure that the inlet pressure is higher than the exhaust pressure during the product's operation; the sensor's own assembly relationship needs to consider factors such as process feasibility, insulation requirements, and structural strength requirements.

[0043] In practical applications, such as Figure 2 As shown in the figure, the design constraints are as follows: based on the wave transmission requirement, the maximum outer diameter of the sensor projected along the axis of the missile is not greater than 20mm; the reserved mounting hole size of the antenna cover is 12mm; the sensor needs to realize the integrated collection of total temperature and total pressure; the performance index requirements are as follows: according to the user input requirements, the temperature measurement range of the sensor needs to cover -50℃~1000℃; the overall temperature measurement deviation cannot exceed 4% of the measured value; the dynamic response characteristics require that the time constant is not higher than 1s.

[0044] The second step is to select structural materials that meet both the temperature resistance requirements and the structural realization requirements in the first step, based on the upper temperature limit requirements in the performance index requirements. After the material selection is initially determined, the physical properties of the structural materials are sorted out to provide support for subsequent performance analysis.

[0045] Based on the above-mentioned embodiment, the upper limit of the temperature measurement range of the sensor is 1000°C, and the high-temperature alloy material can meet the application requirements, so the high-temperature alloy is used as the structural material in this embodiment, and the high-temperature alloy can achieve precision processing; because the temperature measurement deviation does not exceed 4% and the time constant is not greater than 1s, the exposed thermocouple (or other temperature sensitive devices) cannot directly meet the measurement requirements, so it is necessary to specially design a stagnation cavity to suppress radiation error and velocity error to ensure the high-precision and high-dynamic index requirements of the sensor.

[0046] The third step is to give a preliminary stagnation cavity structure plan, such as Figure 3 As shown in the figure, since the deviation of the total pressure measurement value is more sensitive to position than the deviation of the total temperature measurement value, the total pressure air intake hole is set at the center of the front ball head (the intersection of the center axis of the projectile and the front arc) in the preliminary stagnation chamber structure plan; the total temperature air inlet hole is set on the side of the total pressure hole, and the center line of the two is in a horizontal state; the total temperature exhaust hole is set 4mm away from the front end; the diameter of the total pressure air intake hole is not less than 1mm; the diameter of the total temperature air inlet hole is 2mm~3mm; the diameter of the total temperature exhaust hole is 1.5mm~2mm.

[0047] The fourth step is to process and simplify the preliminary three-dimensional model of the stagnation cavity structure, carry out CFD simulation analysis, and combine heat transfer theory to evaluate the performance of the sensor, compare it with the input technical index requirements, analyze the closure situation, find out the reasons for performance deviation, further optimize the local design parameters of the stagnation cavity, and iterate repeatedly until the sensor performance meets the index requirements.

[0048] For example, if the calculated velocity error accounts for a high proportion, reaching more than 10°C, then if the structural strength permits, the total temperature air inlet hole length should be appropriately increased from 4.5mm to 6mm; if the radiation error accounts for a high proportion, the position relationship between the hot node and the front end should be adjusted (keeping the overhang length unchanged), and the hot node should be moved back 1mm; if the velocity error accounts for a high proportion, it means that the air flow velocity in the stagnation cavity is high and is not fully stagnant, then the exhaust hole diameter needs to be reduced from 2mm to 1.5mm; among them, the radiation error and thermal conductivity error are related to the convective heat transfer coefficient between the airflow and the wire, and appropriately increasing the air flow velocity in the stagnation cavity can increase the convective heat transfer efficiency.

[0049] When the final performance of the sensor meets the index requirements, the design of the stagnation cavity is completed, and subsequent manufacturing process plan formulation, prototype development and verification work can be carried out.

[0050] In summary, the present invention provides a design method for a total temperature and total pressure stagnation cavity under ultra-high temperature conditions and a total temperature and total pressure stagnation cavity. The method first combines the design constraints and performance index requirements to preliminarily determine the sensor intake and exhaust flow path layout and the sensor's own assembly relationship, and then determines the structural material of the stagnation cavity based on the performance index requirements and the preliminarily determined sensor's own assembly relationship, and obtains its physical property parameters. Then, based on the preliminarily determined sensor intake and exhaust flow path layout and the sensor's own assembly relationship, the stagnation cavity structure is preliminarily determined. Then, based on the 3D model and physical property parameters of the stagnation cavity structure, the sensor performance analysis results are obtained through CFD and theoretical calculations, which are compared with the corresponding performance indicators. According to the differences, the stagnation cavity structure is repeatedly adjusted iteratively until all performances of the stagnation cavity meet the index requirements. This method can guide the design of the total temperature and total pressure sensor stagnation cavity under ultra-high temperature and strong volume constraint conditions, and finally obtain a stagnation cavity structure with a high recovery rate. It is simple and practical, easy to implement and effective, and has strong feasibility. Compared with the prior art, the technical solution of the present invention can solve the technical problem in the prior art that a high recovery rate stagnation cavity cannot be designed under ultra-high temperature conditions.

[0051] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0052] In addition, it should be noted that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0053] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for designing a total temperature and total pressure stagnation cavity under ultra-high temperature conditions, characterized in that: The method comprises: S1, determining the design constraints and performance index requirements of the sensor, and preliminarily determining the layout of the sensor's inlet and exhaust flow channels and the sensor's own assembly relationship based on the design constraints; S2, determining the structural material of the stagnation cavity according to the performance index requirements and the preliminarily determined assembly relationship of the sensor itself, and obtaining the physical property parameters of the structural material; S3, preliminarily determining the stagnation cavity structure based on the preliminarily determined sensor intake and exhaust flow path layout and the sensor's own assembly relationship; S4, establishing a three-dimensional model of the stagnation cavity according to the stagnation cavity structure; S5, obtaining a performance result of the current stagnation cavity three-dimensional model through CFD simulation analysis based on the stagnation cavity three-dimensional model and the physical property parameters, and comparing the performance result with the performance index requirement. If the performance index requirement is not met, go to S6; if the performance index requirement is met, go to S7; S6, adjusting the current stagnation cavity three-dimensional model and returning to S5; S7, taking the current stagnation cavity three-dimensional model as the final model, and determining the stagnation cavity manufacturing process according to the final model.

2. The method according to claim 1, characterized in that When the layout of the inlet and exhaust flow passages of the sensor is preliminarily determined according to the design constraints, the inlet pressure is higher than the exhaust pressure.

3. The method according to claim 1, characterized in that The design constraints include: size constraints, installation requirements and integration requirements, and the performance index requirements include temperature measurement range requirements, temperature measurement deviation requirements, dynamic response time constant requirements, recovery rate requirements and maximum stress requirements.

4. The method according to claim 3, characterized in that The size constraint is that the maximum outer diameter of the sensor projected along the axis of the missile is not greater than 20 mm, the installation requirement is that the size of the sensor installation hole reserved on the antenna cover is 12 mm, and the integration requirement is the integrated collection of total temperature and total pressure in the sensor.

5. The method according to claim 4, characterized in that The temperature measurement range is required to be -50°C to 1000°C, the temperature measurement deviation is required to be no more than 4% of the measured value, and the dynamic response time constant is required to be no higher than 1s.

6. The method according to claim 5, characterized in that The preliminary determined layout of the sensor inlet and exhaust flow channels is as follows: the total pressure air intake hole is set at the center of the front end ball head, the total temperature air intake hole is set at the side of the total pressure hole, the center line connecting the total pressure air intake hole and the total temperature air intake hole is in a horizontal state, the total temperature exhaust hole is set 4mm away from the center of the front end ball head, the diameter of the total pressure air intake hole is not less than 1mm, the diameter of the total temperature air intake hole is 2mm~3mm, and the diameter of the total temperature exhaust hole is 1.5mm~2mm.

7. A total temperature and total pressure stagnation chamber, characterized in that: The total temperature and total pressure stagnation cavity is a total temperature and total pressure stagnation cavity designed according to the total temperature and total pressure stagnation cavity design method under ultra-high temperature conditions according to any one of claims 1 to 6.

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