Data partitioning method and system for launch vehicle fairing

Abstract

The present invention discloses a data partitioning method and system for a carrier rocket fairing, the method comprising: performing fluid mechanics simulation calculations on the fairing to obtain fairing surface pressure data; converting the fairing surface pressure data from a Cartesian coordinate system into a cylindrical coordinate system; wherein the x-axis in the cylindrical coordinate system is parallel to the fairing axis; performing axial data substation on the fairing surface pressure data along the fairing axis according to the requirements of strength analysis to obtain n axial data sets; performing circumferential data substation within each axial data set to form m circumferential data sets within each axial data set; and calculating the average pressure within each circumferential data set and loading the average pressure into the corresponding area of the fairing.

Description

Technical Field

[0001] The present application relates to the technical field of launch vehicle aerodynamic load analysis, and in particular to a data partitioning method and system for a launch vehicle fairing. Background Art

[0002] The launch vehicle fairing is made of high-strength, lightweight, high-temperature resistant and radio-transparent materials. It is located on the top of the launch vehicle. Its main function is to maintain the aerodynamic shape of the rocket and protect the spacecraft.

[0003] Aerodynamic load is the main load borne by the launch vehicle fairing. When conducting fairing structural strength analysis, finite element software is usually used to calculate the static strength of the fairing. At this time, the aerodynamic load is often directly loaded onto the fairing surface in a cooperative force manner.

[0004] However, since the actual aerodynamic load distribution acts on the outer surface of the fairing, its distribution is closely related to the aerodynamic shape of the fairing. The outer dimensions of the fairing are designed according to the aerodynamic characteristics requirements of the launch vehicle and the space dimensions required to load the spacecraft. Due to the shape limitations of the fairing, the currently loaded aerodynamic load cannot support the refined analysis of the fairing structural strength, resulting in low accuracy of the fairing strength analysis. Summary of the Invention

[0005] In order to achieve refined analysis of structural strength, the present invention provides a data partitioning method and system for a launch vehicle fairing, which improves the accuracy of fairing strength analysis by discretizing the fairing surface pressure data and loading it accordingly onto the outer surface of the fairing.

[0006] To solve the above technical problems, the first aspect of the present invention discloses a data partitioning method for a launch vehicle fairing, the method comprising:

[0007] Performing fluid dynamics simulation calculation on the fairing to obtain fairing surface pressure data;

[0008] Converting the fairing surface pressure data from a Cartesian coordinate system to a cylindrical coordinate system; wherein the z-axis in the cylindrical coordinate system is parallel to the fairing axis;

[0009] According to the requirements of strength analysis, the surface pressure data of the fairing is axially distributed along the axis of the fairing to obtain n axial data sets;

[0010] Perform circumferential data substations within each axial data set, so that m circumferential data sets are formed within each axial data set;

[0011] The average pressure in each circumferential data set is calculated and loaded into the corresponding area of the fairing.

[0012] Optionally, the fairing surface pressure data includes a number of grid pressure data expressed in a Cartesian coordinate system, and each grid pressure data includes: the x, y, and z coordinates of the grid center point, the grid area, the grid average pressure, and the components of the grid pressure in the x, y, and z directions.

[0013] Optionally, converting the fairing surface pressure data from a Cartesian coordinate system to a cylindrical coordinate system specifically includes:

[0014] The x coordinate in the Cartesian coordinate system is consistent with the z coordinate in the cylindrical coordinate system. The pressure components in the y and z directions of the Cartesian coordinate system are transformed into the cylindrical coordinate system. The transformation formula is as follows:

[0015]

[0016]

[0017] Wherein, r, θ, and x represent variables in the cylindrical coordinate system.

[0018] Optionally, after converting the fairing surface pressure data from a Cartesian coordinate system to a cylindrical coordinate system, the method further includes:

[0019] The fairing is divided into n axial substations along the axis of the fairing; wherein, one axial substation corresponds to an x interval in the cylindrical coordinate system, and the range of the x interval is [n xbeg ,n xend ] Among them, n xbeg Indicates the x-coordinate of the front end of the x-interval, n xend Indicates the x-coordinate of the last end of the x-interval;

[0020] In each axial substation, the fairing is circumferentially divided into m circumferential blocks; each circumferential block has its own angular interval.

[0021] Optionally, according to the requirements of the strength analysis, the axial data distribution of the fairing surface pressure data is performed along the fairing axis to obtain n axial data sets, specifically including:

[0022] Sort the fairing surface pressure data in ascending order of x coordinates, and extract the data whose x coordinates are between [n xbeg ,n xend ] to form the n axial data sets.

[0023] Optionally, performing circumferential data substation within each axial data set so as to form m circumferential data sets within each axial data set specifically includes:

[0024] Based on the cylindrical coordinate system, the data in each axial data set are arranged in ascending order according to the central angle;

[0025] The data within each circumferential angle interval is extracted to form a circumferential data set for each of the m circumferential blocks.

[0026] Optionally, calculating the average pressure in each circumferential data set and loading it to the corresponding area of the fairing specifically includes:

[0027] According to the formula Calculate the average pressure in each circumferential data set; where P AVG represents the average pressure in the circumferential data set of the circumferential block, P i Represents the pressure data of each grid in the circumferential block, S i Represents the grid area of each grid in the circumferential block.

[0028] A second aspect of the present invention discloses a data partitioning system for a launch vehicle fairing, the system comprising:

[0029] A simulation calculation module is used to perform fluid dynamics simulation calculation on the fairing to obtain fairing surface pressure data;

[0030] A coordinate conversion module, configured to convert the fairing surface pressure data from a Cartesian coordinate system into a cylindrical coordinate system; wherein the z-axis in the cylindrical coordinate system is parallel to the fairing axis;

[0031] An axial substation module is used to perform axial data substation on the surface pressure data of the fairing along the axis of the fairing according to the requirements of the strength analysis, so as to obtain n axial data sets;

[0032] The circumferential substation module is used to perform circumferential data substation within each axial data set, so that m circumferential data sets are formed within each axial data set;

[0033] The data calculation module is used to calculate the average pressure in each circumferential data set and load it into the corresponding area of the fairing.

[0034] According to a third aspect of the present invention, a computer-readable storage medium is disclosed, on which a computer program is stored. When the program is executed by a processor, the steps of the above method are implemented.

[0035] A fourth aspect of the present invention discloses a computer device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the above method when executing the program.

[0036] Through one or more technical solutions of the present invention, the present invention has the following beneficial effects or advantages:

[0037] The technical solution of the present invention, after obtaining the fairing surface pressure data, converts the fairing surface pressure data into a cylindrical coordinate system representation suitable for the fairing shape, and performs axial and circumferential data distribution on the fairing surface pressure data. After calculating the average pressure within each circumferential data set, it is loaded onto the corresponding area of the fairing. Thus, the present invention can greatly improve the accuracy of the fairing structural strength analysis by subjecting the fairing surface pressure data obtained by aerodynamic calculations to data distribution processing, thereby converting it into discrete distribution data for load calculation, and then loading it onto the fairing outer surface accordingly.

[0038] The above description is only an overview of the technical solution of the present invention. In order to more clearly understand the technical means of the present invention, it can be implemented in accordance with the contents of the specification. In order to make the above and other purposes, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are specifically listed below. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Various other advantages and benefits will become apparent to those skilled in the art upon reading the detailed description of the preferred embodiment below. The accompanying drawings are for illustration purposes only and are not to be construed as limiting the present invention. The same reference numerals are used throughout the accompanying drawings to denote the same components.

[0040] In the attached figure:

[0041] Figure 1 A flow chart of a data partitioning method for a launch vehicle fairing according to an embodiment of the present invention is shown;

[0042] Figure 2 A schematic diagram showing a fairing after axial and circumferential segmentation according to an embodiment of the present invention is shown;

[0043] Figure 3 A schematic diagram of a data partitioning system for a launch vehicle fairing according to an embodiment of the present invention is shown. DETAILED DESCRIPTION

[0044] Exemplary embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the present invention and to fully convey the scope of the present invention to those skilled in the art.

[0045] The embodiment of the present invention discloses a data partitioning method for a launch vehicle fairing. Figure 1 , the method comprises the following steps:

[0046] Step 101: Perform fluid dynamics simulation calculation on the fairing to obtain fairing surface pressure data.

[0047] In this embodiment, calculations can be performed using fluid simulation software. Based on the calculation results, a file storing the fairing surface pressure data can be output. The file name can be in the following format: mcfd.info2.bcsN.DAT, where N represents the boundary number corresponding to the fairing in the fluid dynamics simulation software.

[0048] Furthermore, the fairing surface pressure data includes a number of grid pressure data represented by a Cartesian coordinate system, each grid pressure data includes: the x, y, and z coordinates of the grid center point, the grid area, the grid average pressure, and the components of the grid pressure in the x, y, and z directions.

[0049] Step 102: convert the fairing surface pressure data from a Cartesian coordinate system to a cylindrical coordinate system.

[0050] The origin of the Cartesian coordinate system is at the top of the fairing head, the x-axis is parallel to the fairing axis, the y-axis is located in the longitudinal symmetry plane of the fairing and points upward, and the z-axis is determined according to the right-hand rule.

[0051] Considering the shape restrictions of the fairing, the fairing surface pressure data is converted into a cylindrical coordinate system suitable for the fairing shape. The coordinate origin of the cylindrical coordinate system is at the top of the fairing head, and the z-axis is parallel to the fairing axis.

[0052] During the transformation, the x coordinate in the Cartesian coordinate system is consistent with the z coordinate in the cylindrical coordinate system, and the pressure components in the y and z directions of the Cartesian coordinate system are transformed into the cylindrical coordinate system;

[0053] The conversion formula is as follows:

[0054]

[0055]

[0056] Wherein, r, θ, and z represent variables in the cylindrical coordinate system. Specifically, θ represents the angle value of the grid center point, and r represents the radius of the grid center point.

[0057] Step 103 : Based on the requirements of strength analysis, axial data distribution is performed on the fairing surface pressure data along the fairing axis to obtain n axial data sets.

[0058] Before data substation, the fairing entity can be divided into circumferential parts. Specifically, the fairing is divided into n axial substations along the axis of the fairing. Figure 2 , which is a schematic diagram of the circumferential blocks after the fairing is physically divided axially and circumferentially. Each circumferential block has its own number. Of course, the density of the axial substations can be adjusted adaptively based on actual needs analysis.

[0059] After axial segmentation, one axial substation corresponds to an x interval in the cylindrical coordinate system, and the range of the x interval is [n xbeg ,n xend ] Among them, n xbeg Indicates the x-coordinate of the front end of the x-interval, n xend Indicates the x-coordinate of the last end of the x-interval. Therefore, each axial substation has its own interval range [n xbeg ,n xend ].

[0060] Furthermore, the fairing surface pressure data is divided into substations according to the x-coordinate, and the axial data set of each substation is determined. Specifically, the fairing surface pressure data is sorted in ascending order according to the x-coordinate, and the data of the axial data set of each substation is extracted. xbeg ,n xend ] to form the n axial data sets.

[0061] Step 104 : Perform circumferential data substation within each axial data set, so that m circumferential data sets are formed within each axial data set.

[0062] In this embodiment, in each axial substation, the fairing is circumferentially divided into m circumferential blocks, for example, 360° is equally divided into m circumferential blocks, and each circumferential block has its own angular interval.

[0063] Based on the cylindrical coordinate system, the data in each axial data set are arranged in ascending order according to the central angle; and the data in each circumferential angle interval are extracted to form circumferential data sets for each of the m circumferential blocks.

[0064] Step 105 : Calculate the average pressure in each circumferential data set and load it to the corresponding area of the fairing.

[0065] In this embodiment, the average pressure in each circumferential data set is calculated according to formula (3).

[0066] Formula (3) is expressed as follows:

[0067]

[0068] Among them, P AVGrepresents the average pressure in the circumferential data set of the circumferential block, P i Represents the pressure data of each grid in the circumferential block, S i Represents the grid area of each grid in the circumferential block.

[0069] In this embodiment, the grid pressure and grid area of each circumferential block are multiplied and summed to obtain the total grid pressure of the circumferential block, which is finally divided by the area of the circumferential block to obtain the average pressure in the circumferential data set corresponding to the circumferential block.

[0070] Through the technical solution of the present invention, it is possible to transmit aerodynamic load data to structural strength simulation substantially without error, and the solution can be extended to the processing of aerodynamic load data of other rotating bodies.

[0071] Based on the same inventive concept as in the above embodiment, the embodiment of the present invention also discloses a data partitioning system for a launch vehicle fairing, see Figure 3 , the system comprising:

[0072] A simulation calculation module 301 is used to perform fluid dynamics simulation calculation on the fairing to obtain fairing surface pressure data;

[0073] A coordinate conversion module 302 is used to convert the fairing surface pressure data from a Cartesian coordinate system to a cylindrical coordinate system; wherein the z-axis in the cylindrical coordinate system is parallel to the fairing axis;

[0074] An axial substation module 303 is configured to perform axial data substation on the fairing surface pressure data along the fairing axis according to the requirements of the strength analysis, to obtain n axial data sets;

[0075] The circumferential substation module 304 is used to perform circumferential data substation within each axial data set, so that m circumferential data sets are formed within each axial data set;

[0076] The data calculation module 305 is used to calculate the average pressure in each circumferential data set and load it into the corresponding area of the fairing.

[0077] Based on the same inventive concept as in the aforementioned embodiments, an embodiment of the present invention further discloses a computer-readable storage medium having a computer program stored thereon, which implements the steps of any of the aforementioned methods when executed by a processor.

[0078] Based on the same inventive concept as in the aforementioned embodiments, an embodiment of the present invention further discloses a computer device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the program, the steps of any of the aforementioned methods are implemented.

[0079] Through one or more embodiments of the present invention, the present invention has the following beneficial effects or advantages:

[0080] The technical solution of the present invention, after obtaining the fairing surface pressure data, converts the fairing surface pressure data into a cylindrical coordinate system representation suitable for the fairing shape, and performs axial and circumferential data distribution on the fairing surface pressure data. After calculating the average pressure within each circumferential data set, it is loaded onto the corresponding area of the fairing. Thus, the present invention can greatly improve the accuracy of the fairing structural strength analysis by subjecting the fairing surface pressure data obtained by aerodynamic calculations to data distribution processing, thereby converting it into discrete distribution data for load calculation, and then loading it onto the fairing outer surface accordingly.

[0081] Although the preferred embodiments of the present application have been described, those skilled in the art may make additional changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present application.

[0082] Obviously, those skilled in the art may make various changes and modifications to this application without departing from the spirit and scope of this application. Thus, if these modifications and variations of this application fall within the scope of the claims of this application and their equivalents, this application is intended to include these modifications and variations.

Claims

1. A data partitioning method for a launch vehicle fairing, characterized in that: The method comprises: Performing fluid dynamics simulation calculation on the fairing to obtain fairing surface pressure data; Converting the fairing surface pressure data from a Cartesian coordinate system to a cylindrical coordinate system; wherein the z-axis in the cylindrical coordinate system is parallel to the fairing axis; According to the requirements of strength analysis, the surface pressure data of the fairing is axially distributed along the axis of the fairing to obtain n axial data sets; Perform circumferential data substations within each axial data set, so that m circumferential data sets are formed within each axial data set; The average pressure in each circumferential data set is calculated and loaded into the corresponding area of the fairing.

2. The method according to claim 1, wherein The fairing surface pressure data includes a number of grid pressure data represented by a Cartesian coordinate system, each grid pressure data includes: the x, y, z coordinates of the grid center point, the grid area, the grid average pressure, and the components of the grid pressure in the x, y, and z directions.

3. The method according to claim 2, wherein The converting of the fairing surface pressure data from a Cartesian coordinate system to a cylindrical coordinate system specifically includes: The x coordinate in the Cartesian coordinate system is consistent with the z coordinate in the cylindrical coordinate system. The pressure components in the y and z directions of the Cartesian coordinate system are transformed into the cylindrical coordinate system. The transformation formula is as follows: Wherein, r, θ, and z represent variables in the cylindrical coordinate system.

4. The method according to claim 2, wherein After converting the fairing surface pressure data from a Cartesian coordinate system to a cylindrical coordinate system, the method further includes: The fairing is divided into n axial substations along the axis of the fairing; wherein, one axial substation corresponds to an x interval in the cylindrical coordinate system, and the range of the x interval is [n xbeg ,n xend ] Among them, n xbeg Indicates the x-coordinate of the front end of the x-interval, n xend Indicates the x-coordinate of the last end of the x-interval; In each axial substation, the fairing is circumferentially divided into m circumferential blocks; each circumferential block has its own angular interval.

5. The method according to claim 4, wherein According to the requirements of the strength analysis, the axial data distribution of the fairing surface pressure data is performed along the fairing axis to obtain n axial data sets, specifically including: Sort the fairing surface pressure data in ascending order of x coordinates, and extract the data whose x coordinates are between [n xbeg ,n xend ] to form the n axial data sets.

6. The method according to claim 5, wherein The circumferential data substation is performed within each axial data set, so that m circumferential data sets are formed within each axial data set, specifically including: Based on the cylindrical coordinate system, the data in each axial data set are arranged in ascending order according to the central angle; The data within each circumferential angle interval is extracted to form a circumferential data set for each of the m circumferential blocks.

7. The method according to claim 6, wherein Calculate the average pressure in each circumferential data set and load it to the corresponding area of the fairing, specifically including: According to the formula Calculate the average pressure in each circumferential data set; where P AVG represents the average pressure in the circumferential data set of the circumferential block, P i Represents the pressure data of each grid in the circumferential block, S i Represents the grid area of each grid in the circumferential block.

8. A data partitioning system for a launch vehicle fairing, characterized in that: The system comprises: A simulation calculation module is used to perform fluid dynamics simulation calculation on the fairing to obtain fairing surface pressure data; A coordinate conversion module, configured to convert the fairing surface pressure data from a Cartesian coordinate system into a cylindrical coordinate system; wherein the x-axis in the cylindrical coordinate system is parallel to the fairing axis; An axial substation module is used to perform axial data substation on the surface pressure data of the fairing along the axis of the fairing according to the requirements of the strength analysis, so as to obtain n axial data sets; The circumferential substation module is used to perform circumferential data substation within each axial data set, so that m circumferential data sets are formed within each axial data set; The data calculation module is used to calculate the average pressure in each circumferential data set and load it into the corresponding area of the fairing.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the program is executed by a processor, the steps of the method according to any one of claims 1 to 7 are implemented.

10. A computer device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the program, the steps of the method according to any one of claims 1 to 7 are implemented.

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