A multidisciplinary coupling analysis framework and method for hose-drogue aerial refueling

Abstract

The application relates to the technical field of aerial refueling, and discloses a hose-drogue aerial refueling multi-disciplinary coupling analysis framework and method, which comprises the following steps: a data layer is used to provide required file information for fluid mechanics analysis and multi-body dynamics calculation; a grid layer is used to generate a discrete grid file according to the file information provided by the data layer; a calculation preparation layer is used to provide required unsteady aerodynamic effect parameters, an aerodynamic database and a three-dimensional tanker wake flow field file for hose-drogue coupling calculation; a calculation layer is used to perform fluid-solid coupling dynamics response simulation on the release and stabilization process of the hose-drogue in the tanker wake flow field; and a post-processing layer is used to post-process and display the aerial refueling hose-drogue calculation data obtained through the coupling simulation calculation. In this way, quick and high-precision simulation of the release and stabilization process of the hose-drogue in the tanker wake flow can be performed, and key technical support can be provided for the design and safety evaluation of a domestic soft aerial refueling system.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aerial refueling, in particular to a hose-drogue aerial refueling multidisciplinary coupling analysis framework and method. BACKGROUND

[0002] Aerial refueling technology plays an extremely important role in improving the sustained flight efficiency of an aircraft. A receiver aircraft can obtain longer loiter time and greater mission activity radius by aerial refueling; multiple aerial refueling can greatly extend the loiter time of the receiver aircraft; the receiver aircraft can reduce the take-off fuel carrying capacity to exchange for heavier mission load or shorter take-off distance. Since the process of landing to replenish fuel and taking off again is omitted, aerial refueling technology reduces the total fuel consumption of the aircraft per unit time and improves the mission economy.

[0003] The aerial refueling mode in which a tanker aircraft transmits fuel to a receiver aircraft through a hose-drogue device is called hose-drogue aerial refueling, also known as soft aerial refueling. Compared with the hard pipe refueling mode, the hose-drogue aerial refueling has the advantages of small equipment volume, flexible installation, and support for multiple receiver aircrafts to be refueled at the same time.

[0004] In recent years, in the design evaluation of aerial refueling systems and the research and development of autonomous refueling docking technology, it is urgently needed to predict and analyze the dynamic response of the hose-drogue, a rigid-flexible coupling structure, in the atmospheric environment. Compared with flight tests and wind tunnel scale tests, establishing a numerical simulation method for aerial refueling dynamics is a cost-effective research approach with fast response and avoidance of scale errors.

[0005] In previous domestic and foreign numerical simulation researches on aerial refueling, there have been long-term defects such as insufficient accuracy of dynamic modeling of the hose-drogue, excessive simplification of the aerodynamic characteristics of the refueling drogue, and lack of evaluation of dynamic aerodynamic effects during the release and stabilization process of the hose-drogue. In addition, the fluid-structure coupling simulation method based on unsteady computational fluid dynamics requires a large amount of calculation and is only suitable for simulating a few typical states, making it difficult to quickly respond to batch simulations of multiple parameters of aerial refueling. At present, there is no aerial refueling simulation research method that takes into account accurate simulation of the hose-drogue structure, evaluation of unsteady aerodynamic effects, aerodynamic characteristics based on the real drogue shape, and rapid analysis capability. SUMMARY

[0006] Therefore, the purpose of the present application is to provide a hose-drogue aerial refueling multidisciplinary coupling analysis framework and method, which can perform rapid and high-precision simulation of the release and stabilization process of the hose-drogue in the tanker aircraft wake. The specific scheme is as follows:

[0007] A hose-drogue aerial refueling multidisciplinary coupling analysis framework comprises:

[0008] a data layer, configured to provide a CAD model file of an external shape of a refueling machine and a refueling drogue, a flow field calculation parameter input file, and a multi-body dynamics calculation parameter input file required for fluid mechanics analysis and multi-body dynamics calculation;

[0009] a grid layer, configured to generate discrete grid files according to file information provided by the data layer; the discrete grid files include a flow field grid file, a surface grid file, and a hose finite element discrete file;

[0010] a calculation preparation layer, configured to provide unsteady aerodynamic effect parameters, an aerodynamic database, and a three-dimensional refueling machine wake flow field file required for drogue coupling calculation;

[0011] a calculation layer, configured to perform fluid-structure coupling dynamics response simulation on a release and stabilization process of the drogue in the refueling machine wake flow field according to the discrete grid files generated by the grid layer and information provided by the calculation preparation layer;

[0012] a post-processing layer, configured to post-process and display calculation data of the aerial refueling drogue obtained by the coupling simulation calculation.

[0013] Preferably, in the above-mentioned multi-disciplinary coupling analysis framework for aerial refueling drogue provided by the embodiment of the present application, the grid layer is specifically configured to generate the flow field grid file and the surface grid file of the refueling machine and the refueling drogue according to the CAD model file of the external shape of the refueling machine and the refueling drogue and the flow field calculation parameter input file; and generate the hose finite element discrete file according to the multi-body dynamics calculation parameter input file.

[0014] Preferably, in the above-mentioned multi-disciplinary coupling analysis framework for aerial refueling drogue provided by the embodiment of the present application, the calculation preparation layer includes:

[0015] a parameter calculation module, configured to perform trial calculation on the release and stabilization process of the drogue by using a URANS flow field solver and a multi-body dynamics solver to determine unsteady aerodynamic effect parameters as a benchmark;

[0016] a database generation module, configured to obtain six-component aerodynamic force coefficients of the drogue under different attack angles, sideslip angles, and different incoming flow velocities by using a RANS flow field solver to generate an aerodynamic database;

[0017] a flow field file calculation module, configured to calculate a three-dimensional refueling machine wake flow field file based on a structure interfacing grid by using the RANS flow field solver.

[0018] Preferably, in the above-mentioned multi-disciplinary coupling analysis framework for aerial refueling drogue provided by the embodiment of the present application, the calculation layer includes:

[0019] a modeling module configured to perform dynamic modeling on the hose drogue using a multibody dynamics solver;

[0020] a flow velocity acquisition module configured to obtain the flow velocity of the drogue in the wake flow field of the tanker by spatial interpolation on the drogue position in the wake flow field of the tanker;

[0021] a pneumatic load acquisition module configured to obtain the pneumatic load of the drogue by interpolation on the pneumatic database;

[0022] a coupling simulation calculation module configured to perform batch simulation calculation on the fluid-structure coupling dynamic response of the release and stabilization process of the hose drogue in the wake flow field of the tanker according to the flow velocity of the drogue, the pneumatic load of the drogue and the unsteady pneumatic effect parameter.

[0023] Preferably, in the above-mentioned multi-disciplinary coupling analysis framework for the hose drogue aerial refueling provided by the embodiments of the present application, the post-processing layer comprises:

[0024] a first processing module configured to perform post-processing on the tanker wake flow field file using a wake flow field post-processing program to generate a readable file of the tanker wake flow field;

[0025] a second processing module configured to draw an animation file of the dynamic response of the hose drogue using a multibody dynamics post-processing program and display a corresponding animation video;

[0026] a third processing module configured to output the motion law, the pneumatic load law and the stress-strain law data file in the dynamic response of the drogue by the multibody dynamics solver.

[0027] The embodiments of the present application also provide a coupling analysis method of the above-mentioned multi-disciplinary coupling analysis framework for the hose drogue aerial refueling provided by the embodiments of the present application, comprising:

[0028] generating a discrete grid file according to the CAD model file of the tanker and the refueling drogue, the flow field calculation parameter input file and the multibody dynamics calculation parameter input file; the discrete grid file comprises a flow field grid file, a surface grid file and a hose finite element discrete file;

[0029] obtaining a three-dimensional tanker wake flow field file, a pneumatic database and an unsteady pneumatic effect parameter;

[0030] performing fluid-structure coupling dynamic response simulation on the release and stabilization process of the hose drogue in the wake flow field of the tanker according to the discrete grid file, the unsteady pneumatic effect parameter, the pneumatic database and the three-dimensional tanker wake flow field file;

[0031] performing post-processing and display on the calculation data of the aerial refueling hose drogue obtained by the coupling simulation calculation.

[0032] Preferably, in the coupling analysis method provided by the embodiment of the present application, the obtaining of the three-dimensional tanker wake flow field file, the aerodynamic database and the unsteady aerodynamic effect parameter comprises:

[0033] Based on the structural docking grid, a RANS flow field solver is used to perform parallel CFD calculation on the tanker and its wake flow field, and a three-dimensional tanker wake flow field file is calculated.

[0034] The RANS flow field solver is used to obtain six-component aerodynamic force coefficients of the cone sleeve under different attack angles, sideslip angles and different incoming flow velocities, and an aerodynamic database is generated.

[0035] A URANS flow field solver and a multi-body dynamics solver are used to perform trial calculation on the release and stabilization process of the hose cone sleeve, serving as a benchmark for determining the unsteady aerodynamic effect parameter.

[0036] Preferably, in the coupling analysis method provided by the embodiment of the present application, the fluid-structure coupling dynamic response simulation of the release and stabilization process of the hose cone sleeve in the tanker wake flow field comprises:

[0037] A multi-body dynamics solver is used to perform dynamic modeling on the hose cone sleeve.

[0038] The position of the cone sleeve in the tanker wake flow field is spatially interpolated to obtain the incoming flow velocity of the cone sleeve.

[0039] The aerodynamic load of the cone sleeve is obtained by interpolation of the aerodynamic database.

[0040] According to the incoming flow velocity of the cone sleeve, the aerodynamic load of the cone sleeve and the unsteady aerodynamic effect parameter, batch simulation calculation is performed on the fluid-structure coupling dynamic response of the release and stabilization process of the hose cone sleeve in the tanker wake flow field.

[0041] Preferably, in the coupling analysis method provided by the embodiment of the present application, in the process of performing dynamic modeling on the hose cone sleeve, the hose is discretized by using a cable-beam element based on absolute node coordinates, the cone sleeve is a six-degree-of-freedom rigid body, and the constraint relationship between the hose and the cone sleeve is a fixed constraint between the cable-beam and the rigid body.

[0042] Preferably, in the coupling analysis method provided by the embodiment of the present application, the post-processing and display of the air refueling hose cone sleeve calculation data obtained by the coupling simulation calculation comprises:

[0043] A wake flow field post-processing program is used to post-process the tanker wake flow field file to generate a readable file of the tanker wake flow field.

[0044] The animation file of the dynamic response of the hose drogue is drawn using a multi-body dynamics post-processing program, and a corresponding animation video is displayed.

[0045] The motion law, aerodynamic load law and stress-strain law data files in the dynamic response of the drogue are output by the multi-body dynamics solver.

[0046] As can be seen from the above technical solution, the multi-disciplinary coupling analysis framework for hose drogue aerial refueling provided by the application comprises: a data layer, which is used to provide the required CAD model files of the shape of the tanker and the drogue, the flow field calculation parameter input files and the multi-body dynamics calculation parameter input files for fluid mechanics analysis and multi-body dynamics calculation; a mesh layer, which is used to generate discrete mesh files according to the file information provided by the data layer; the discrete mesh files comprise flow field mesh files, surface mesh files and hose finite element discrete files; a calculation preparation layer, which is used to provide the required unsteady aerodynamic effect parameters, aerodynamic databases and three-dimensional tanker wake flow field files for hose drogue coupling calculation; a calculation layer, which is used to perform fluid-structure coupling dynamics response simulation on the release and stabilization process of the hose drogue in the tanker wake flow field according to the discrete mesh files generated by the mesh layer and the information provided by the calculation preparation layer; and a post-processing layer, which is used to post-process and display the aerial refueling hose drogue calculation data obtained by the coupling simulation calculation.

[0047] According to the above multi-disciplinary coupling analysis framework for hose drogue aerial refueling provided by the application, through the interaction of the data layer, the mesh layer, the calculation preparation layer, the calculation layer and the post-processing layer, the required input information can be provided for fluid mechanics analysis and multi-body dynamics calculation, the discrete mesh files required for calculation and post-processing display can be generated according to the information, and the required test parameters, flow fields and aerodynamic databases can be provided for hose drogue coupling calculation, so that the fluid-structure coupling dynamics response simulation on the release and stabilization process of the hose drogue device in the tanker wake flow field is completed, and finally the aerial refueling hose drogue calculation data obtained by the coupling calculation is post-processed and displayed, thereby the rapid and high-precision simulation of the release and stabilization process of the hose-drogue in the tanker wake flow can be performed, and key technical support for the design and safety evaluation of the soft aerial refueling system of China is provided.

[0048] In addition, the application also provides a corresponding coupling analysis method for the multi-disciplinary coupling analysis framework for hose drogue aerial refueling, which further makes the above multi-disciplinary coupling analysis framework for hose drogue aerial refueling more practical, and the coupling analysis method has corresponding advantages. BRIEF DESCRIPTION OF DRAWINGS

[0049] In order to make the technical scheme of the embodiments of the present application or the related art clearer, the accompanying drawings needed in the embodiments or the related art description will be briefly introduced. Obviously, the accompanying drawings in the following description only aim at the embodiments of the present application, and other drawings can be obtained by those skilled in the art without any creative effort on the basis of the provided drawings.

[0050] Figure 1 A structure schematic diagram of a hose-drogue aerial refueling multidisciplinary coupling analysis framework provided for the embodiments of the present application is shown in the figure.

[0051] Figure 2 A specific structure schematic diagram of a hose-drogue aerial refueling multidisciplinary coupling analysis framework provided for the embodiments of the present application is shown in the figure.

[0052] Figure 3 A coupling analysis method flowchart of a hose-drogue aerial refueling multidisciplinary coupling analysis framework provided for the embodiments of the present application is shown in the figure.

[0053] Figure 4 A coupling analysis method specific flowchart of a hose-drogue aerial refueling multidisciplinary coupling analysis framework provided for the embodiments of the present application is shown in the figure.

[0054] Figure 5 A calculation coordinate system schematic diagram of a refueling drogue provided for the embodiments of the present application is shown in the figure.

[0055] Figure 6 A dynamics model schematic diagram of a hose-drogue provided for the embodiments of the present application is shown in the figure.

[0056] Figure 7 A flowchart of a query and interpolation algorithm in a flow field space grid provided for the embodiments of the present application is shown in the figure.

[0057] Figure 8 A tanker wake flow field density nephogram provided for the embodiments of the present application is shown in the figure.

[0058] Figure 9 A tanker wake flow field downwash attack angle nephogram provided for the embodiments of the present application is shown in the figure.

[0059] Figure 10 A calculation grid schematic diagram of a refueling drogue provided for the embodiments of the present application is shown in the figure.

[0060] Figure 11 A local overlapping grid topology diagram between a tanker and a refueling drogue provided for the embodiments of the present application is shown in the figure.

[0061] Figure 12 A drogue x-direction velocity U variation with time t law diagram provided for the embodiments of the present application is shown in the figure.

[0062] Figure 13A z-direction velocity W of the cone sleeve provided by the embodiment of the present application varies with time t;

[0063] Figure 14 A x-direction displacement of the cone sleeve provided by the embodiment of the present application varies with time t;

[0064] Figure 15 A z-direction displacement of the cone sleeve provided by the embodiment of the present application varies with time t;

[0065] Figure 16 A pitch angle STA of the cone sleeve provided by the embodiment of the present application varies with time t;

[0066] Figures 17a to 17h The release speed of each of the embodiments of the present application is 0.3 m / s, and the dynamic display figure of the hose-cone sleeve post-processing corresponding to each 1 s is shown. DETAILED DESCRIPTION

[0067] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the present application.

[0068] The present application provides a hose-cone aerial refueling multi-disciplinary coupling analysis framework, as shown in Figure 1 , which comprises:

[0069] A data layer 11 is configured to provide a CAD model file of an external shape of a tanker and a refueling cone, a flow field calculation parameter input file and a multi-body dynamics calculation parameter input file required for fluid mechanics analysis and multi-body dynamics calculation;

[0070] A grid layer 12 is configured to generate discrete grid files, including a flow field grid file, a surface grid file and a hose finite element discrete file, according to the file information provided by the data layer 11;

[0071] A calculation preparation layer 13 is configured to provide unsteady aerodynamic effect parameters, an aerodynamic database and a three-dimensional tanker wake flow field file required for hose-cone coupling calculation;

[0072] A calculation layer 14 is configured to perform fluid-solid coupling dynamics response simulation on a release and stabilization process of the hose-cone in the tanker wake flow field, according to the discrete grid files generated by the grid layer 12 and the information provided by the calculation preparation layer 13;

[0073] A post-processing layer 15 is configured to post-process and display the data of the hose-drogue air refueling calculated by the coupling simulation.

[0074] In the above-mentioned multi-disciplinary coupling analysis framework of the hose-drogue air refueling provided by the embodiment of the present application, the required input information for fluid mechanics analysis and multi-body dynamics calculation can be provided through the interaction of the data layer 11, the grid layer 12, the calculation preparation layer 13, the calculation layer 14 and the post-processing layer 15, the discrete grid files required for calculation and post-processing display can be generated according to the information, the required test parameters, flow field and aerodynamic database for the coupling calculation of the hose-drogue can be provided, the fluid-structure coupling dynamics response simulation of the release and stabilization process of the hose-drogue device in the wake flow field of the tanker can be completed, and finally the data of the hose-drogue air refueling calculated by the coupling calculation can be displayed, analyzed and post-processed, so that the rapid and high-precision simulation of the release and stabilization process of the hose-drogue in the wake flow of the tanker can be performed, and key technical support for the design and safety evaluation of the soft air refueling system of China can be provided.

[0075] Figure 1 and Figure 2 The multi-disciplinary coupling analysis framework of the hose-drogue air refueling device is shown, and the calculation framework can be divided into five levels according to the analysis process, and the specific structure is shown in Figure 2 .

[0076] In the specific implementation, in the above-mentioned multi-disciplinary coupling analysis framework of the hose-drogue air refueling provided by the embodiment of the present application, as shown in Figure 2 , the information provided by the data layer 11 can be divided into two categories of geometric information and calculation parameter information according to the data types. The geometric information includes the CAD model file of the tanker shape and the CAD model file of the refueling drogue shape; the calculation parameter information is divided into flow field calculation parameter input file and multi-body dynamics calculation parameter input file. The data layer 11 classifies and manages the input data through separate modular input data packets.

[0077] In the specific implementation, in the above-mentioned multi-disciplinary coupling analysis framework of the hose-drogue air refueling provided by the embodiment of the present application, the grid layer 12 can be specifically used to generate the flow field grid file and the surface grid file of the tanker and the refueling drogue according to the CAD model file of the tanker and the refueling drogue shape and the flow field calculation parameter input file; and generate the finite element discrete file of the hose according to the multi-body dynamics calculation parameter input file.

[0078] Specifically, in the grid layer 12, the discrete grid files are divided into flow field grid files, surface grid files and hose finite element discrete files according to the use; wherein the flow field grid files are generated for the fueling machine and the fueling cone sleeve numerical model shape, the structured / unstructured grid is generated and parallel preprocessed; the surface grid files are the surface grid of the fueling machine and the fueling cone sleeve for post-processing display; the hose finite element discrete files are generated according to the dynamic input parameters. The grid layer 12 is an intermediate link between the data layer 11 and the coupled calculation, and is the need of the discretization of the coupled numerical calculation.

[0079] In the specific implementation, in the above-mentioned multi-disciplinary coupling analysis framework of the hose cone sleeve in-flight refueling provided by the embodiment of the application, the calculation preparation layer 13 can specifically include:

[0080] A parameter calculation module, configured to perform experimental calculation on the release and stabilization process of the hose cone sleeve by using a URANS (unsteady Reynolds-Averaged Navier-Stokes) flow field solver containing moving dynamic overlapping grids and a multi-body dynamics solver, as a benchmark for determining the unsteady aerodynamic effect parameters;

[0081] A database generation module, configured to obtain six-component aerodynamic force coefficients of the cone sleeve under different attack angles, sideslip angles and different incoming flow velocities by using a RANS (Reynolds-Averaged Navier-Stokes) method flow field solver, and generate an aerodynamic database;

[0082] A flow field file calculation module, configured to calculate a three-dimensional fueling machine wake flow field file based on a structure docking grid using a RANS flow field solver.

[0083] Specifically, in the calculation preparation layer 13, the release and stabilization process of the hose-cone sleeve is calculated experimentally by using a URANS flow field solver containing moving dynamic overlapping grids and a multi-body dynamics solver, as a benchmark for determining the unsteady aerodynamic effect parameters, and the unsteady aerodynamic effect parameters of the cone sleeve can be obtained by full coupling calculation of unsteady CFD-multi-body dynamics, which can be applied to the subsequent multi-disciplinary analysis framework calculation method composed of the fueling machine wake field post-processing, the cone sleeve aerodynamic database and the multi-body dynamics solver. Based on the real shape of the fueling cone sleeve, six-component aerodynamic force coefficients of the cone sleeve under different attack angles, sideslip angles and different incoming flow velocities are obtained by using a RANS flow field solver, and a CFD aerodynamic database is generated. A three-dimensional fueling machine wake flow field file is calculated based on a structure docking grid using a RANS flow field solver, which contains flow information such as flow velocity, density and vorticity. The calculation preparation layer 13 extracts and converts the common information in the batch hose cone sleeve dynamic process calculation of different incoming flows and dynamic parameters into different types of preparation data, and obtains them by using various calculation means.

[0084] In a specific implementation, in the above-mentioned multi-disciplinary coupling analysis framework for the hose-drogue aerial refueling provided by the embodiment of the present application, the calculation layer 14 can specifically include:

[0085] a modeling module configured to perform dynamic modeling of the hose-drogue using a multi-body dynamics solver;

[0086] an incoming flow velocity acquisition module configured to obtain the incoming flow velocity of the drogue at the drogue position in the tanker wake flow field through spatial interpolation;

[0087] an aerodynamic load acquisition module configured to obtain the aerodynamic load of the drogue through aerodynamic database interpolation;

[0088] a coupling simulation calculation module configured to perform batch simulation calculation of the fluid-structure coupling dynamic response of the hose-drogue in the release and stabilization process in the tanker wake flow field according to the incoming flow velocity of the drogue, the aerodynamic load of the drogue, and the unsteady aerodynamic effect parameters.

[0089] Specifically, the calculation layer 14 is the core calculation step in the coupling calculation framework, and its function is to complete the fluid-structure coupling dynamic response simulation of the hose-drogue device in the release, oscillation, and stabilization process in the tanker wake flow field. In the calculation layer 14, the multi-body dynamics solver is used to perform dynamic modeling of the hose-drogue, the spatial interpolation is performed on the drogue position in the wake flow field to obtain the incoming flow velocity of the drogue, the aerodynamic database interpolation is used to obtain the aerodynamic load of the drogue, and finally the coupling simulation calculation of the hose-drogue is completed in combination with the unsteady aerodynamic effect parameters. In this way, the accurate acquisition of the aerodynamic characteristics of the drogue in the tanker wake flow field is realized through spatial-velocity interpolation; wherein the tanker wake flow field can be obtained through steady CFD calculation, or the velocity field can be obtained through a theoretical model or test data.

[0090] In a specific implementation, in the above-mentioned multi-disciplinary coupling analysis framework for the hose-drogue aerial refueling provided by the embodiment of the present application, the post-processing layer 15 can specifically include:

[0091] a first processing module configured to perform post-processing on the tanker wake flow field file using a wake flow field post-processing program to generate a readable file of the tanker wake flow field;

[0092] a second processing module configured to draw an animation file of the dynamic response of the hose-drogue using a multi-body dynamics post-processing program, and display the corresponding animation video;

[0093] a third processing module configured to output the motion law, aerodynamic load law, and stress-strain law data files in the dynamic response of the drogue through the multi-body dynamics solver.

[0094] Specifically, in the post-processing layer 15, a tecplot readable file in a plt format of an output refueling machine wake flow field is output, and the file contains spatial flow field information; an animation file of a dynamic response of the hose cone is drawn by using a special multi-body dynamics post-processing program, and the file can generate a video by using tecplot; and a multi-body dynamics solver outputs a data file of a motion law, an aerodynamic load law and a stress-strain law in the dynamic response of the cone.

[0095] Based on the same inventive concept, the embodiment of the present application also provides a coupling analysis method of the hose cone aerial refueling multi-disciplinary coupling analysis framework. Since the principle of the method for solving problems is similar to the aforementioned hose cone aerial refueling multi-disciplinary coupling analysis framework, the implementation of the method can be referred to the implementation of the hose cone aerial refueling multi-disciplinary coupling analysis framework, and the implementation of the hose cone aerial refueling multi-disciplinary coupling analysis framework can also be referred to the implementation of the method, and the repeated parts will not be described herein.

[0096] In the implementation, the coupling analysis method of the hose cone aerial refueling multi-disciplinary coupling analysis framework provided by the embodiment of the present application specifically includes the following steps: Figure 3 as shown in the figure, specifically comprising:

[0097] S301, generating a discrete grid file according to a CAD model file of an external shape of a refueling machine and a refueling cone, a flow field calculation parameter input file and a multi-body dynamics calculation parameter input file; the discrete grid file includes a flow field grid file, a surface grid file and a hose finite element discrete file;

[0098] S302, obtaining a three-dimensional refueling machine wake flow field file, an aerodynamic database and unsteady aerodynamic effect parameters;

[0099] S303, performing fluid-structure coupling dynamics response simulation on a release and stabilization process of the hose cone in the refueling machine wake flow field according to the discrete grid file, the unsteady aerodynamic effect parameters, the aerodynamic database and the three-dimensional refueling machine wake flow field file;

[0100] S304, post-processing and displaying the aerial refueling hose cone calculation data obtained by the coupling simulation calculation.

[0101] In the coupling analysis method provided by the embodiment of the present application, by executing the steps S301 to S304, the release and stabilization process of the hose-cone in the refueling machine wake flow can be simulated quickly and accurately, and key technical support is provided for the design and safety evaluation of the soft aerial refueling system of China.

[0102] Further, in the implementation, in the coupling analysis method provided by the embodiment of the present application, the step S302 obtains the three-dimensional refueling machine wake flow field file, the aerodynamic database and the unsteady aerodynamic effect parameters, as shown in the figure, Figure 4As shown, can specifically include the following steps:

[0103] First, based on the structure of the docking grid using RANS flow field solver, the refueling machine and its wake flow field to carry out parallel CFD calculation, calculation of three-dimensional refueling machine wake flow field file; Specifically, using a structure grid and RANS model based on computational fluid dynamics solver, the refueling machine and its wake flow field to carry out parallel CFD calculation, the flow field generated as Para.dat file and so on.

[0104] Then, using RANS flow field solver to obtain the six-component aerodynamic force coefficients of the cone sleeve under different attack angles, sideslip angles and different incoming flow velocities, and generate an aerodynamic database; Specifically, using conventional fluid mechanics calculation software including commercial software to calculate the aerodynamic force / moment coefficient database of the refueling cone sleeve under different incoming flow attack angles α, sideslip angles β. The conversion formula of the aerodynamic force / moment coefficient is:

[0105]

[0106]

[0107] Where i can be x, y, z, corresponding to the three calculation coordinate system directions. i F is the aerodynamic force in the i direction, which has a dimensionless quantity. i M is the aerodynamic moment in the i direction, which has a dimensionless quantity (the moment reference point is the centroid of the cone sleeve) ; ρ is the atmospheric density, V ∞ is the far-field incoming flow velocity, S ref is the reference area of the cone sleeve, L ref is the reference length of the cone sleeve, C f,i is the dimensionless aerodynamic force coefficient in the i direction, C m,i is the dimensionless aerodynamic moment coefficient in the i direction. The calculation coordinate system of the refueling cone sleeve is defined as Figure 5 shown.

[0108] The file format of the aerodynamic database of the refueling cone sleeve is shown in Table 1.

[0109] Table 1 Aerodynamic database file format of refueling cone sleeve

[0110]

[0111] Finally, the release and stabilization process of the hose drogue is calculated by the URANS flow field solver and the multi-body dynamics solver, which is used as a reference for determining the parameters of the unsteady aerodynamic effect. Specifically, the unsteady URANS computational fluid dynamics parallel program based on the dynamic overlapping grid is combined with the multi-body dynamics solver to perform a reference state coupling simulation of the fluid-structure coupling dynamic response of the given hose drogue structure during the release and stabilization process. The unsteady URANS fluid mechanics calculation can realize real-time accurate generation of the aerodynamic load of the drogue in the unsteady flow field, and the simulation result truly reflects the influence of the fluid-structure coupling unsteady aerodynamic effect caused by the drogue movement. The purpose of the reference calculation is to determine the aerodynamic damping coefficient (c x ,c y ,c z ) of the drogue, which is one of the input parameters in the next flow field interpolation coupling simulation.

[0112] Further, in the coupling analysis method provided by the embodiment of the present application, the step S303 of simulating the release and stabilization process of the hose drogue in the flow field of the tanker wake can specifically include: using a multi-body dynamics solver to model the dynamics of the hose drogue; interpolating the position of the drogue in the flow field of the tanker wake to obtain the drogue incoming flow velocity; interpolating the aerodynamic database to obtain the aerodynamic load of the drogue; and performing batch simulation of the fluid-structure coupling dynamic response of the hose drogue in the flow field of the tanker wake during the release and stabilization process according to the drogue incoming flow velocity, the drogue aerodynamic load and the unsteady aerodynamic effect parameters.

[0113] In the above step, the multi-body dynamics solver is combined with the sampling interpolation program of the wake flow field information to perform batch simulation of the fluid-structure coupling dynamic response of the given hose drogue structure during the release and stabilization process. In each time step of the coupling calculation, the multi-body dynamics solver transmits the drogue mass center position vector at the current time to the sampling interpolation program, which obtains the incoming flow velocity vector at the spatial position through spatial sampling interpolation and returns it to the multi-body dynamics solver. The multi-body dynamics solver converts the incoming flow condition into real-time aerodynamic load of the drogue through the drogue aerodynamic database. Data transmission is realized through dynamic files.

[0114] In the coupling analysis method provided by the embodiment of the present application, in the process of modeling the dynamics of the hose drogue, the refueling hose is discretized by a cable-beam element based on absolute node coordinates, the refueling drogue is a six-degree-of-freedom rigid body, and the constraint relationship between the hose and the drogue is a fixed constraint between the cable-beam and the rigid body. The dynamic modeling diagram of a typical refueling hose drogue is shown in Figure 6 .

[0115] In a specific implementation, in the coupling analysis method provided by the embodiment of the application, the step S304 of post-processing and displaying the aerial refueling hose-drogue coupling calculation data obtained by the coupling simulation calculation can specifically include: using a wake flow field post-processing program to post-process the tanker wake flow field file to generate a readable file of the tanker wake flow field; using a multi-body dynamics post-processing program to draw an animation file of the dynamic response of the hose-drogue and display the corresponding animation video; and outputting, by a multi-body dynamics solver, the motion law, aerodynamic load law and stress-strain law data files in the dynamic response of the drogue.

[0116] Specifically, the wake flow field file of the tanker is post-processed by using the wake flow field post-processing program to generate a plt format space flow field file that can be opened by using the tecplot software. The multi-body dynamics post-processing program is used to read in the multi-body dynamics kinematics output file and the tanker drogue surface grid file, generate an animation file that can be opened by using the tecplot software, and then generate a video avi format file by using the tecplot software.

[0117] It should be noted that the numerical solution of the tanker wake flow field is expressed as flow field information in discrete grid elements, including flow field density, velocity vector, internal energy and turbulence information. In the coupling simulation of the hose-drogue dynamics and flow field interpolation, after the spatial position of the drogue is given, the inflow velocity vector at the position needs to be obtained by querying and interpolating in the space flow field. Figure 7 A flowchart of the used querying and interpolation algorithm is shown. The flow steps include: first, input the position information to be queried; then, establish a grid binary tree; wherein the root node contains the region as the basic space, and all the elements in the flow field are loaded in the planned space; thereafter, search for the grid element corresponding to the target point; wherein the possible intersection points can be first judged by recursion, and then the unique element corresponding to the target point is further judged by quasi-Newton iteration; if the search fails, the corresponding element is determined by using the nearest distance method to search; finally, the weighted coefficients are determined according to the distances from the target point to the corner points of the element; and the target point is assigned a value by weighted average.

[0118] Next, taking the release of the hose-drogue of a certain tanker scale model under a given inflow condition as an example, the coupling analysis method of the hose-drogue aerial refueling multi-disciplinary coupling analysis framework provided by the embodiment of the application is described in detail, and the specific steps are as follows:

[0119] Step one, calculate the tanker wake flow field;

[0120] The inflow condition is that the flight height h = 500 m, V ∞= 46 m / s, angle of attack a = 2°, sideslip angle b = 0°. The grid is structured grid, with a total number of 88 million, which is generated by NNW-Gridstar. The parallel CFD program Pmb3d is used, with a parallel scale of 1024 cores, and the total calculation time is about 24 hours. Figure 8 Density contours of the tanker wake field in different vertical sections are given, Figure 9 The downwash angle a of the tanker wake field in different vertical sections is given.

[0121] Step two, generate the aerodynamic database of the refueling cone sleeve;

[0122] For the refueling cone sleeve shape, the corresponding structured docking calculation grid is generated by NNW-Gridstar grid software. Figure 10 The calculation grid of the refueling cone sleeve is shown. The incoming flow velocity and height parameters of the refueling cone sleeve database calculation are consistent with the tanker, the calculation interval of the angle of attack a is-50°-50°, every 5° takes one point, the value range of the sideslip angle b is-4°, 0°, 4°; The reference area of the cone sleeve is 8.2645*10 -3 m 2 , the reference length is 0.0909m.

[0123] Step three, fluid-structure coupling simulation of the hose cone sleeve in unsteady flow field;

[0124] The mass characteristics and structural parameters of the hose-cone sleeve are shown in Table 2, the hose release speed is a = 0.3 m / s, and the incoming flow conditions are the same as in the tanker wake calculation. A dynamic overlapping grid-based unsteady URANS flow field solver and multi-body dynamics solver coupling simulation calculation is carried out, which is used as a benchmark reference for calibrating the unsteady effect parameter of the aerodynamic damping coefficient of the cone sleeve. Figure 11 The local overlapping grid topology between the tanker and the refueling cone sleeve is shown. The physical time of the simulation is 8.8s, the unsteady time step of the flow field calculation a = 0.02s, which includes the process of the hose-cone sleeve release to the full length and further stable convergence to the equilibrium position. The initial release length of the hose is 0.0909m, which is inclined at an angle of 30° to the x-axis of the calculation coordinate system, and the full length of the hose is 2.2m. In the pilot's view of the tanker, the positive direction of the x-axis is backward, the y-axis is right, and the z-axis is upward.

[0125] Table 2 Mass characteristics and structural parameters of the hose-cone sleeve

[0126] Thimble mass (kg) 0.043 cone main moment of inertia (kg·m 2 ) Jx 2.222e -5 ]]> cone main moment of inertia (kg·m 2 )Jy]]> 5.33e -5 ]]> cone main moment of inertia (kg·m 2 ) Jz 5.33e -5 ]]> Density of hose material (kg / m 3 )]]> 702.271 Hose tensile modulus E (Pa) 2.0e 10 ]]> Hose cross-sectional area A (m 2 )]]> 5.0265482e -5 ]]> Hose cross-sectional moment of inertia I (kg-m 4 )]]> 2.01062e -10 ]]>

[0127] Step four, dynamic and flow field interpolation coupling simulation of the hose cone sleeve;

[0128] The fueling machine wake flow field obtained in step one is taken as the input of the wake flow field information sampling interpolation program, the fueling cone sleeve aerodynamic database obtained in step two and the multi-body dynamics modeling parameters in step three are taken as the input of the multi-body dynamics solver; the two programs are coupled to simulate the hose-cone sleeve release and stabilization process, through several trials, the aerodynamic damping coefficient of the cone sleeve is calibrated to c x = 0.0, c y = 1.0, c z = 0.1. The hose-cone sleeve dynamics simulation results based on flow field interpolation and the calculation results based on the unsteady CFD method and their comparison are shown in Figures 12 to 16 , the results show that the fluid-structure coupling dynamics response of the hose-cone sleeve based on the wake flow field interpolation is consistent with the calculation results based on the unsteady CFD method.

[0129] The calculation accuracy of the hose-cone sleeve dynamic simulation calculation method based on the wake flow field interpolation is equivalent to the calculation results based on the unsteady CFD method based on a higher precision physical model, the advantage of the former is that it greatly reduces the calculation resources required by the flow field parallel calculation of the latter. In this example, when completing the same example with the same physical simulation time in the same computing cluster, the coupling method based on the unsteady CFD method consumes 32000 cores, and the computing resources need to use 192 core parallelism; while the hose-cone sleeve dynamic simulation method based on the wake flow field interpolation only needs 2 computing cores, and the computing core time is about 80, which reduces the calculation resource consumption of a single calculation to 1 / 400 of the unsteady CFD method under the premise of basically maintaining the calculation accuracy. In multiple batches of calculations and design optimization simulations of different inflow conditions, different dynamics parameters, etc. of the in-flight refueling device, the multi-disciplinary coupling method of the hose-cone sleeve in this calculation framework has the dual advantages of calculation accuracy and calculation efficiency based on the unsteady CFD calculation as a benchmark and the wake flow field interpolation method as the core.

[0130] Step five, post-processing and display;

[0131] Figures 17a to 17h The hose-cone sleeve release process dynamic response animation file generated by the multi-body dynamics post-processing program is shown. The calculation time t = 0s ~ 7s, the release speed Δv = 0.3m / s. The stress and strain of the refueling hose, the cone sleeve load curve and other information are output in text form. The fueling machine wake flow field uses the flow field post-processing program to generate a tecplot readable file in plt format as a visual output.

[0132] The various embodiments described in the specification are progressive in nature, and each embodiment highlights the differences from other embodiments. The same or similar parts among the various embodiments can be mutually referred to. For the coupling analysis method disclosed in the embodiments, since it corresponds to the multi-disciplinary coupling analysis framework for the hose-drogue aerial refueling disclosed in the embodiments, the description is relatively simple, and the relevant parts can be referred to the description of the multi-disciplinary coupling analysis framework for the hose-drogue aerial refueling.

[0133] Those skilled in the art will further appreciate that the units and algorithm steps of the examples described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, computer software, or a combination of both. To clearly illustrate the interchangeability of hardware and software, the components and steps of the examples have been described in general terms in the above description. Whether the functions are performed in hardware or software depends on the particular application and design constraints. Those skilled in the art can implement the described functions in different ways for each particular application, but such implementation should not be considered to be beyond the scope of the present application.

[0134] The steps of the methods or algorithms described in conjunction with the embodiments disclosed herein can be implemented directly in hardware, by a software module executed by a processor, or a combination of both. The software module can be stored in a random access memory (RAM), a memory, a read-only memory (ROM), an electrically programmable ROM, an electrically erasable programmable ROM, a register, a hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art.

[0135] In summary, the embodiment of the application provides a kind of hose cone midair refueling multidisciplinary coupling analysis framework, comprising: data layer 11, for fluid mechanics analysis and multidisciplinary dynamics calculation required refueling machine and refueling cone appearance CAD model file, flow field calculation parameter input file and multidisciplinary dynamics calculation parameter input file are provided;Mesh layer 12, for generating discrete grid file according to the file information provided by data layer 11;Discrete grid file includes flow field grid file, surface grid file and hose finite element discrete file;Preparation layer 13 for calculation, for the required non-steady aerodynamic effect parameter, aerodynamic database and three-dimensional refueling machine wake flow field file are provided for hose cone coupling calculation;Calculation layer 14, for the release and stabilization process of hose cone in the wake flow field of refueling machine is carried out fluid-solid coupling dynamics response simulation according to the discrete grid file generated by mesh layer 12 and the information provided by preparation layer 13 for calculation;Post-processing layer 15, for the midair refueling hose cone calculation data obtained by coupling simulation calculation is post-processed and displayed.The above-mentioned hose cone midair refueling multidisciplinary coupling analysis framework provided by the application can carry out the quick high-precision simulation of the release and stabilization process of hose-cone in the wake flow of refueling machine through the interaction of data layer 11, mesh layer 12, preparation layer 13 for calculation, calculation layer 14 and post-processing layer 15, to provide key technical support for the design and safety evaluation of Chinese soft midair refueling system.In addition, the application also provides a corresponding coupling analysis method for the hose cone midair refueling multidisciplinary coupling analysis framework, to further make the above-mentioned hose cone midair refueling multidisciplinary coupling analysis framework more practical, and the coupling analysis method has corresponding advantages.

[0136] Finally, it should also be noted that, in this paper, such as first and second relationship terms are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between the entities or operations.And, the term "include", "contain" or any other variant thereof is intended to cover non-exclusive inclusion, so that the process, method, article or equipment including a series of elements not only includes those elements, but also includes other elements not explicitly listed, or includes elements inherent in such process, method, article or equipment.In the absence of more limitations, the element defined by the statement "including a …" does not exclude the presence of other identical elements in the process, method, article or equipment including the element.

[0137] The above describes the multi-disciplinary coupling analysis framework and method for the hose-drogue aerial refueling in detail, the principle and implementation manner of the present application are described by using specific examples, the above description of the examples is only used for helping to understand the method of the present application and the core idea; meanwhile, for the general technical personnel in the field, according to the idea of the present application, the specific implementation manner and application range will be changed, and the above description should not be understood as the limitation of the present application.

Claims

1. A multidisciplinary coupled analysis system for in-flight refueling with a hose-and-cone sleeve, characterized in that, include: The data layer provides the necessary CAD model files of the fuel tanker and fuel cone, flow field calculation parameter input files, and multibody dynamics calculation parameter input files for fluid dynamics analysis and multibody dynamics calculations. The mesh layer is used to generate discrete mesh files based on the file information provided by the data layer; the discrete mesh files include flow field mesh files, surface mesh files, and hose finite element discrete files. The computational preparation layer provides the necessary unsteady aerodynamic effect parameters, aerodynamic database, and three-dimensional fuel tanker wake flow field file for hose-cone coupling calculations. The computational layer is used to perform fluid-structure interaction dynamic response simulation of the release and stabilization process of the hose cone sleeve in the wake flow field of the refueling machine, based on the discrete mesh file generated by the mesh layer and the information provided by the computational preparation layer. The post-processing layer is used to post-process and display the calculation data of the aerial refueling hose cone obtained from the coupled simulation calculation; The computing layer includes: The modeling module is used to perform dynamic modeling of the hose cone sleeve using a multibody dynamics solver; The incoming flow velocity acquisition module is used to obtain the incoming flow velocity of the cone sleeve by spatial interpolation of the cone sleeve position in the wake flow field of the fuel dispenser; A pneumatic load acquisition module is used to obtain the tapered sleeve pneumatic load through interpolation from the pneumatic database. The coupled simulation calculation module is used to perform batch simulation calculations of the fluid-structure interaction dynamic response of the hose cone sleeve during the release and stabilization process in the wake flow field of the refueling machine, based on the incoming flow velocity of the cone sleeve, the aerodynamic load of the cone sleeve, and the unsteady aerodynamic effect parameters.

2. The hose-and-cone aerial refueling multidisciplinary coupled analysis system according to claim 1, characterized in that, The mesh layer is specifically used to generate the flow field mesh file and the surface mesh file of the fuel dispenser and the fuel dispenser cone based on the CAD model file of the fuel dispenser and the fuel dispenser cone and the flow field calculation parameter input file; The finite element discrete file of the hose is generated based on the input file of the multibody dynamics calculation parameters.

3. The hose-and-cone aerial refueling multidisciplinary coupled analysis system according to claim 1, characterized in that, The computation preparation layer includes: The parameter calculation module is used to perform experimental calculations on the release and stabilization process of the hose cone sleeve using the URANS flow field solver and multibody dynamics solver, which contain parallel dynamic overlapping meshes, as a benchmark for determining unsteady aerodynamic effect parameters. The database generation module is used to obtain the six-component aerodynamic coefficients of the cone sleeve under different angles of attack, sideslip angles and different incoming flow velocities using the RANS flow field solver, and generate an aerodynamic database. The flow field file calculation module is used to calculate the three-dimensional fuel tanker wake flow field file based on the structural docking mesh using the RANS flow field solver.

4. The multidisciplinary coupled analysis system for in-flight refueling with a hose and cone sleeve according to claim 1, characterized in that, The post-processing layer includes: The first processing module is used to post-process the fuel dispenser wake flow field file using the wake flow field post-processing program to generate a readable file of the fuel dispenser wake flow field. The second processing module is used to draw animation files of the dynamic response of the hose cone sleeve using a multibody dynamics post-processor and display the corresponding animation video. The third processing module is used to output data files of motion laws, aerodynamic load laws, and stress-strain laws in the dynamic response of the cone sleeve through the multibody dynamics solver.

5. A coupling analysis method for a multidisciplinary coupled analysis system for in-flight refueling with a hose and cone as described in any one of claims 1 to 4, characterized in that, include: Based on the CAD model file of the fuel dispenser and fuel cone, the flow field calculation parameter input file, and the multibody dynamics calculation parameter input file, a discrete mesh file is generated; the discrete mesh file includes the flow field mesh file, the surface mesh file, and the hose finite element discrete file. Obtain the 3D fuel tanker wake field file, aerodynamic database, and unsteady aerodynamic effect parameters; Based on the discrete mesh file, the unsteady aerodynamic effect parameters, the aerodynamic database, and the three-dimensional fuel tanker wake field file, the fluid-structure interaction dynamic response simulation of the release and stabilization process of the hose cone sleeve in the fuel tanker wake field is performed. Post-processing and display of the aerial refueling hose cone calculation data obtained from coupled simulation calculations; The fluid-structure interaction dynamic response simulation of the release and stabilization process of the hose cone sleeve in the wake flow field of the refueling machine includes: Dynamic modeling of the hose tapered sleeve was performed using a multibody dynamics solver. Spatial interpolation of the cone sleeve position is performed in the flow field of the fuel dispenser wake to obtain the inflow velocity of the cone sleeve; The aerodynamic load of the cone sleeve is obtained by interpolation using the aerodynamic database. Based on the incoming flow velocity of the cone sleeve, the aerodynamic load of the cone sleeve, and the unsteady aerodynamic effect parameters, batch simulation calculations are performed on the fluid-structure interaction dynamic response of the hose cone sleeve during the release and stabilization process in the wake flow field of the refueling machine.

6. The coupling analysis method according to claim 5, characterized in that, The acquisition of the three-dimensional fuel tanker wake field file, aerodynamic database, and unsteady aerodynamic effect parameters includes: Using the RANS flow field solver based on the structural mesh, parallel CFD calculations were performed on the flow field of the refueling aircraft and its wake, resulting in a three-dimensional flow field file of the refueling aircraft wake. The RANS flow field solver was used to obtain the six-component aerodynamic coefficients of the cone sleeve under different angles of attack, sideslip angles and different incoming flow velocities, and an aerodynamic database was generated. Experimental calculations were performed on the release and stabilization process of the hose cone using the URANS flow field solver and multibody dynamics solver, which included parallel dynamic overlapping meshes, as a benchmark for determining unsteady aerodynamic effect parameters.

7. The coupling analysis method according to claim 5, characterized in that, In the process of dynamic modeling of the hose tapered sleeve, the hose is discretized using cable-beam elements based on absolute node coordinates, the tapered sleeve is a six-degree-of-freedom rigid body, and the constraint relationship between the hose and the tapered sleeve is the fixed support constraint between the cable beam and the rigid body.

8. The coupling analysis method according to claim 5, characterized in that, The post-processing and display of the aerial refueling hose cone calculation data obtained from the coupled simulation calculation includes: The wake flow field file of the fuel dispenser is post-processed using a wake flow field post-processing program to generate a readable file of the fuel dispenser wake flow field. An animation file of the dynamic response of the hose cone sleeve is generated using a multibody dynamics post-processor, and the corresponding animation video is displayed. The multibody dynamics solver outputs data files of the motion laws, aerodynamic load laws, and stress-strain laws in the dynamic response of the cone sleeve.

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