A simulation method, device and equipment for a hose-driven control cone sleeve and a medium

Abstract

The application discloses a hose-active control cone sleeve simulation method and device, equipment and medium, relates to the technical field of simulation, and includes: calculating the wake flow field of a refueling machine, obtaining the aerodynamic database of the active control cone sleeve under different incoming flow conditions; coupling simulation is performed on the unsteady URANS flow field solver and the multi-body dynamics solver to determine the aerodynamic damping coefficient; based on the multi-body dynamics solver, the preset wake flow field sampling interpolation program, the preset control instruction and the preset control algorithm, simulation calculation is performed on the active control cone sleeve to obtain the control coupling dynamics response of the active control cone sleeve; the wake flow field post-processing program is used to post-process the refueling machine wake flow field file to generate a flow field display file, and the multi-body dynamics post-processing program is used to post-process the output motion parameter file of the cone sleeve rigid body and the hose and the surface grid file of the active control cone sleeve to generate an animation display file. The above scheme has high-precision physical modeling and high calculation efficiency.

Description

Technical Field

[0001] This invention relates to the field of simulation technology, and in particular to a simulation method, apparatus, equipment and medium for a flexible hose-active control cone sleeve. Background Technology

[0002] Due to the limitations of its flexible structure, the hose-and-drogue refueling system is prone to displacement and oscillation under the aerodynamic interference forces of the tanker's wake, gusts, crosswinds, and the approach headwave of the receiver aircraft. This irregular movement of the drogue requires the receiver aircraft to perform complex control maneuvers during refueling, making it difficult to complete the refueling operation accurately in one go. This characteristic not only reduces the fuel replenishment efficiency of flexible refueling, but the oscillating drogue may also collide with the receiver aircraft, leading to safety accidents. Improving the flexible refueling drogue using active / passive control methods to achieve motion stability and attitude control of the drogue connected to the hose is an advanced flexible refueling concept proposed by the engineering community in recent years. By adjusting and stabilizing the drogue's balance position through aerodynamic control, and suppressing the drogue's oscillation during the receiver aircraft's approach, the receiver aircraft does not need to perform complex tracking maneuvers during the approach and docking process. This reduces the workload of the receiver aircraft pilot, thereby improving the success rate, refueling efficiency, and safety of in-flight refueling. Such systems are generally referred to as "active control drogue systems." Among the existing active control cone sleeve systems, the active control cone sleeve system based on aerodynamic control surfaces has advantages such as high control sensitivity, clear control law, and direct modification based on existing soft aerial refueling cone sleeves, and has been widely studied by the domestic and foreign aerospace engineering community.

[0003] Existing research methods for active control cone sleeves mainly fall into two categories: wind tunnel testing and numerical simulation. However, due to the limitations of wind tunnel test sections, it is difficult to simultaneously place a refueling cone sleeve with multiple control surfaces and a correspondingly sized hose into the wind tunnel for scaled-down and full-scale tests. Therefore, numerical simulation methods for active control cone sleeves can simulate the actual shape and parameters of a soft-type active control cone sleeve refueling device, but the simulation process still suffers from low accuracy and computational efficiency.

[0004] In summary, how to achieve high-precision and high-efficiency simulation calculations for the hose-active control cone sleeve to meet engineering design requirements is a problem that needs to be solved. Summary of the Invention

[0005] In view of this, the purpose of this invention is to provide a simulation method, apparatus, equipment, and medium for a hose-active control cone sleeve, capable of achieving high-precision and high-computational-efficiency simulation calculations for the hose-active control cone sleeve to meet engineering design requirements. The specific solution is as follows:

[0006] In a first aspect, this application discloses a simulation method for a hose-active control cone sleeve, comprising:

[0007] Calculate the wake flow field of the refueling aircraft to generate a refueling aircraft wake flow field file, and obtain the aerodynamic database of the reference configuration and rudder configuration of the active control cone under different incoming flow conditions;

[0008] Coupled simulations were performed on the unsteady URANS flow field solver and the multibody dynamics solver, and the aerodynamic damping coefficient of the active control cone was determined by combining the aerodynamic database.

[0009] The aerodynamic damping coefficient is used as an input parameter, and the active control cone sleeve is simulated and calculated based on the multibody dynamics solver, the preset wake flow field sampling interpolation program, the preset control command and the preset control algorithm to obtain the control coupling dynamic response of the active control cone sleeve.

[0010] The wake flow field file of the refueling machine is post-processed using a wake flow field post-processing program to obtain a flow field display file that meets the preset readability conditions. Based on the motion parameter files of the cone sleeve rigid body and hose output by the multibody dynamics solver, as well as the pre-determined surface mesh file of the active control cone sleeve, an animation display file of hose-active control cone sleeve is generated using the multibody dynamics post-processing program.

[0011] Optionally, the calculation of the fuel dispenser wake flow field to generate a fuel dispenser wake flow field file includes:

[0012] We used a computational fluid dynamics solver based on structured meshes and RANS models to perform parallel CFD calculations on the flow field of the refueling aircraft wake, in order to generate the flow field file of the refueling aircraft wake.

[0013] Optionally, the aerodynamic database for obtaining the reference configuration and rudder configuration of the active control cone under different incoming flow conditions includes:

[0014] A six-component aerodynamic / torque database of the baseline and yaw configurations of the active control cone under different incoming flow conditions was obtained using CFD calculation software or wind tunnel testing methods.

[0015] Optionally, after acquiring the aerodynamic database of the reference configuration and rudder configuration of the active control cone under different incoming flow conditions, the method further includes:

[0016] Based on the aerodynamic database, and using preset aerodynamic coefficient difference expressions and preset aerodynamic torque coefficient difference expressions, the control surface effect of each control surface is determined.

[0017] Optionally, the process of simulating the active control cone sleeve by using the aerodynamic damping coefficient as an input parameter and based on the multibody dynamics solver, the preset wake flow field sampling interpolation program, the preset control command, and the preset control algorithm further includes:

[0018] The multibody dynamics solver transmits the centroid position of the active control cone at the current moment to the preset wake flow field sampling and interpolation program, so that the preset wake flow field sampling and interpolation program can perform spatial sampling and interpolation based on the centroid position and in the fuel tanker wake flow field file to obtain the incoming flow velocity vector at the current spatial position, and then return the incoming flow velocity vector to the multibody dynamics solver.

[0019] The multibody dynamics solver uses the incoming flow velocity vector to interpolate the aerodynamic database to obtain the aerodynamic force / torque of the active control cone under rudder deflection. Then, combined with the preset control command and the control surface effect, the six-component force / torque coefficients of the active control cone under rudder deflection are determined, and the motion parameters of the current time step are updated so that the updated motion parameters can be used to enter the coupling calculation of the next time step.

[0020] Optionally, the coupled simulation of the unsteady URANS flow field solver and the multibody dynamics solver, combined with the aerodynamic database, to determine the aerodynamic damping coefficient of the active control cone sleeve includes:

[0021] An unsteady URANS flow field solver including a dynamically overlapping structured mesh was determined, and the unsteady URANS flow field solver and the multibody dynamics solver were coupled and simulated to obtain the motion law of the active control cone sleeve in the unsteady flow field.

[0022] Based on the motion law and the aerodynamic database, the aerodynamic damping coefficient and aerodynamic torque damping coefficient of the active control cone sleeve are determined.

[0023] Optionally, the simulation method for the hose-active control cone sleeve further includes:

[0024] A preset control algorithm is determined for obtaining the rudder deflection law based on the motion parameters of the active controller and through a control solver, and a preset control command is determined for controlling the active control cone sleeve according to the rudder deflection law.

[0025] Secondly, this application discloses a simulation device for a hose-active control cone sleeve, comprising:

[0026] The flow field calculation module is used to calculate the flow field of the fuel dispenser wake to generate a fuel dispenser wake flow field file;

[0027] The aerodynamic database acquisition module is used to acquire the aerodynamic database of the reference configuration and rudder configuration of the active control cone under different incoming flow conditions.

[0028] The damping coefficient determination module is used to perform coupled simulation of the unsteady URANS flow field solver and the multibody dynamics solver, and combine the aerodynamic database to determine the aerodynamic damping coefficient of the active control cone sleeve.

[0029] The simulation calculation module is used to take the aerodynamic damping coefficient as an input parameter and perform simulation calculations on the active control cone sleeve based on the multibody dynamics solver, the preset wake flow field sampling interpolation program, the preset control command and the preset control algorithm to obtain the control coupling dynamic response of the active control cone sleeve.

[0030] The display file acquisition module is used to post-process the fuel tanker wake flow field file using the wake flow field post-processing program to obtain a flow field display file that meets the preset readable conditions. Based on the motion parameter files of the cone sleeve rigid body and hose output by the multibody dynamics solver and the pre-determined surface mesh file of the active control cone sleeve, the module uses the multibody dynamics post-processing program to generate an animation display file of hose-active control cone sleeve.

[0031] Thirdly, this application discloses an electronic device, comprising:

[0032] Memory, used to store computer programs;

[0033] A processor is used to execute the computer program to implement the steps of the aforementioned disclosed simulation method for a hose-active control cone sleeve.

[0034] Fourthly, this application discloses a computer-readable storage medium for storing a computer program; wherein, when the computer program is executed by a processor, it implements the steps of the aforementioned simulation method for a hose-active control cone sleeve.

[0035] As can be seen, this application calculates the wake flow field of the refueling aircraft to generate a wake flow field file, and obtains aerodynamic databases of the baseline configuration and rudder configuration of the active control cone under different incoming flow conditions; it performs coupled simulations of the unsteady URANS flow field solver and the multibody dynamics solver, and determines the aerodynamic damping coefficient of the active control cone by combining the aerodynamic database; it uses the aerodynamic damping coefficient as an input parameter, and performs simulation calculations on the active control cone based on the multibody dynamics solver, a preset wake flow field sampling interpolation program, a preset control command, and a preset control algorithm to obtain the control coupling dynamic response of the active control cone; it uses a wake flow field post-processing program to post-process the refueling aircraft wake flow field file to obtain a flow field display file that meets preset readable conditions, and uses the multibody dynamics post-processing program to generate an animation display file of the hose-active control cone based on the motion parameter files of the cone rigid body and the hose output by the multibody dynamics solver and the pre-determined surface mesh file of the active control cone. Therefore, this application calculates the wake flow field of the refueling aircraft and obtains aerodynamic databases of the baseline and rudder configurations of the active control cone under different incoming flow conditions. Then, it combines unsteady computational fluid dynamics, steady computational fluid dynamics, multibody dynamics, and control theory to perform multidisciplinary coupled simulations of the active control cone, obtaining the control-coupled dynamic response of the active control cone under different incoming flow conditions, and displaying it through corresponding files. The above technical solution can achieve high-precision and high-computational-efficiency simulation calculations of the hose-active control cone and meets engineering design requirements. Attached Figure Description

[0036] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0037] Figure 1 This is a flowchart of a simulation method for a hose-active control cone sleeve disclosed in this application;

[0038] Figure 2 This is a schematic diagram of a multidisciplinary coupling analysis process for active control cone sleeve disclosed in this application;

[0039] Figure 3 This is a schematic diagram of a data interface between a multibody dynamics program and control code disclosed in this application;

[0040] Figure 4 This is a schematic diagram of the active control cone sleeve of a cross-shaped aerodynamic control surface disclosed in this application;

[0041] Figure 5 This is a schematic diagram showing the numbering of a cone-shaped control surface disclosed in this application;

[0042] Figure 6 This is a schematic diagram of the rudder effect curve of the active control cone sleeve deflection torque coefficient disclosed in this application;

[0043] Figure 7 This application discloses a relative rotational angular velocity-time curve for a 1 / 3 rudder surface.

[0044] Figure 8 This is a graph showing the displacement of the centroid of a conical sleeve in the X direction over time, as disclosed in this application.

[0045] Figure 9 This is a graph showing the displacement of the centroid of a conical sleeve in the Y direction as a function of time, as disclosed in this application.

[0046] Figure 10 This is a graph showing the displacement of the centroid of a conical sleeve in the Z direction over time, as disclosed in this application.

[0047] Figure 11 This is a graph showing the change of the active control cone yaw angle over time, as disclosed in this application.

[0048] Figure 12 This is a graph showing the change of the pitch angle of an active control cone sleeve over time, as disclosed in this application.

[0049] Figure 13 This is a graph showing the velocity of an active control cone sleeve in the x, y, and z directions as a function of time, as disclosed in this application.

[0050] Figure 14 This application discloses a hose-actively controlled cone sleeve with controlled movement in the xy plane;

[0051] Figure 15 This is a schematic diagram of the simulation device structure of a hose-active control cone sleeve disclosed in this application;

[0052] Figure 16 This is a structural diagram of an electronic device disclosed in this application. Detailed Implementation

[0053] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0054] Existing research methods for active control cone sleeves mainly fall into two categories: wind tunnel testing and numerical simulation. However, due to the size limitations of wind tunnel test sections, it is difficult to simultaneously place a refueling cone sleeve with multiple control surfaces and a correspondingly scaled hose into the wind tunnel for scaled-down and full-scale tests. Therefore, while numerical simulation methods can simulate the actual shape and parameters of a flexible active control cone sleeve refueling device, the simulation process still suffers from low accuracy and computational efficiency. To address this, this application discloses a simulation method, apparatus, equipment, and medium for a hose-active control cone sleeve, enabling high-precision and high-efficiency simulation calculations to meet engineering design requirements.

[0055] See Figure 1 and Figure 2 As shown in the figure, this application discloses a simulation method for a hose-active control cone sleeve, the method comprising:

[0056] Step S11: Calculate the wake flow field of the refueling aircraft to generate a wake flow field file, and obtain the aerodynamic database of the reference configuration and rudder configuration of the active control cone under different incoming flow conditions.

[0057] In this embodiment, the above-mentioned calculation of the fuel tanker wake flow field to generate a fuel tanker wake flow field file includes: performing CFD (Computational Fluid Dynamics) parallel calculations on the fuel tanker wake flow field using a computational fluid dynamics solver based on a structured mesh and a RANS model to generate the fuel tanker wake flow field file. That is, the computational fluid dynamics solver is specifically built based on a structured mesh and a RANS model, and the generated fuel tanker wake flow field file also needs to be saved as a Para.dat file.

[0058] In this embodiment, obtaining the aerodynamic database of the reference configuration and rudder configuration of the active control cone under different incoming flow conditions includes: obtaining a six-component aerodynamic force / moment database of the reference configuration and rudder configuration of the active control cone under different incoming flow conditions using CFD calculation software or wind tunnel testing methods. Further, after obtaining the aerodynamic database of the reference configuration and rudder configuration of the active control cone under different incoming flow conditions, the method further includes: determining the control surface effectiveness of each control surface based on the aerodynamic database and using preset aerodynamic force coefficient difference expressions and preset aerodynamic moment coefficient difference expressions. The preset aerodynamic force coefficient difference expressions and preset aerodynamic moment coefficient difference expressions are specifically as follows:

[0059]

[0060]

[0061] in, The aerodynamic coefficients representing the refueling cone sleeve reference configuration in the j-th coordinate axis direction (x, y, and z represent the 1st, 2nd, and 3rd coordinate axis directions, respectively) are... Represents the deflection Δδ of the i-th control rudder. i Aerodynamic coefficients in the j-axis direction after the angle. The difference in aerodynamic coefficients along the j-axis is the unit angle of deflection of the i-th control rudder. The aerodynamic moment coefficient representing the reference configuration of the refueling cone sleeve in the j-th coordinate axis direction. Represents the deflection Δδ of the i-th control rudder. i The aerodynamic moment coefficient in the j-axis direction after the angle. The difference in aerodynamic torque coefficient along the j-axis is the unit angle of deflection of the i-th control rudder.

[0062] In the linear segment of the control surface, This constitutes the control surface effect of the i-th control surface.

[0063] Step S12: Perform coupled simulation of the unsteady URANS flow field solver and the multibody dynamics solver, and combine the aerodynamic database to determine the aerodynamic damping coefficient of the active control cone sleeve.

[0064] In this embodiment, the coupled simulation of the unsteady URANS flow field solver and the multibody dynamics solver, combined with the aerodynamic database, determines the aerodynamic damping coefficient of the active control cone. This includes: determining an unsteady URANS flow field solver including a dynamically overlapping mesh, and performing coupled simulation of the unsteady URANS flow field solver and the multibody dynamics solver to obtain the motion law of the active control cone in the unsteady flow field; based on the motion law and the aerodynamic database, determining the aerodynamic damping coefficient and aerodynamic moment damping coefficient of the active control cone. That is, this step is a fluid-structure interaction simulation of the aerial refueling hose cone in an unsteady flow field. By coupling the unsteady URANS flow field solver including a dynamically overlapping mesh and the multibody dynamics solver for simulation calculation, the motion law of the active control cone in the unsteady flow field can be obtained. Then, combined with the aerodynamic database of the active control cone obtained above, its aerodynamic damping coefficient and aerodynamic moment damping coefficient are obtained. These aerodynamic damping coefficients can be used as partial input parameters for subsequent multibody dynamics calculations to construct unsteady aerodynamic models of the conical sleeve motion in multibody dynamics simulations, thereby improving the calculation accuracy of actively controlling the conical sleeve motion.

[0065] Step S13: Using the aerodynamic damping coefficient as an input parameter, and based on the multibody dynamics solver, the preset wake flow field sampling interpolation program, the preset control command, and the preset control algorithm, the active control cone sleeve is simulated and calculated to obtain the control coupling dynamic response of the active control cone sleeve.

[0066] In this embodiment, by combining a multibody dynamics solver with a preset wake flow field sampling and interpolation program, preset control commands, and preset control algorithms, numerical simulation calculations of aerodynamic / kinematic / control coupling can be performed on a hose-active control cone device under a given control surface rotation law, obtaining the control coupling dynamic response of the active control cone. It should be noted that the above method also includes: determining a preset control algorithm for obtaining the rudder deflection law based on the motion parameters of the active controller and through a control solver, and determining a preset control command for controlling the active control cone according to the rudder deflection law. That is, the preset control command refers to controlling the active control cone according to a preset rudder deflection law, and the preset control algorithm obtains the rudder deflection law based on the motion parameters of the active control cone through a control solver. In this way, the manipulation law of a given aerodynamic control surface can be realized, and the motion and dynamic response of the hose-active control cone under the incoming flow conditions can be obtained. For the preset control algorithm, the data interface between the multibody dynamics program and the control code can be specifically as follows: Figure 3 As shown, Figure 3 The control code is transferred from the dynamics program through a universal data adapter, which can handle the cases of multiple control channels and a single control channel corresponding to multiple control surfaces. The control code calculates the control feedback quantity and then passes it to the dynamics program.

[0067] Furthermore, the above process may specifically include: transmitting the centroid position of the active control cone at the current moment to a preset wake flow field sampling interpolation program through the multibody dynamics solver, so that the preset wake flow field sampling interpolation program can perform spatial sampling interpolation based on the centroid position and in the refueling aircraft wake flow field file to obtain the incoming flow velocity vector at the current spatial position, and then returning the incoming flow velocity vector to the multibody dynamics solver; using the incoming flow velocity vector to perform interpolation calculations on the aerodynamic database through the multibody dynamics solver to obtain the aerodynamic force / torque of the active control cone under rudder deflection, and then combining the preset control command and the control surface effect to determine the six-component force / torque coefficients of the active control cone under rudder deflection, and updating the motion parameters of the current time step so as to use the updated motion parameters to enter the coupling calculation of the next time step. Understandably, the multibody dynamics solver passes the current centroid position vector of the cone to a preset wake flow field sampling and interpolation program. The program then obtains the incoming velocity vector at that spatial location through spatial sampling and interpolation of the refueling aircraft's wake flow field file and returns it to the multibody dynamics solver. This velocity vector is then used for interpolation in the aerodynamic database of the active control cone to obtain the real-time aerodynamic forces / torques acting on the active control cone with rudder deflection. Combined with preset control surface commands and control surface effects, the multibody dynamics solver can calculate the six-component force / torque coefficients of the cone after rudder deflection and update the cone's position, attitude, velocity, and other kinematic parameters at the current time step before proceeding to the next time step for coupled calculations.

[0068] Step S14: Use the wake flow field post-processing program to post-process the fuel tanker wake flow field file to obtain a flow field display file that meets the preset readability conditions. Based on the motion parameter files of the cone sleeve rigid body and hose output by the multibody dynamics solver, as well as the pre-determined surface mesh file of the active control cone sleeve, use the multibody dynamics post-processing program to generate an animation display file of hose-active control cone sleeve.

[0069] In this embodiment, the wake flow field file of the refueling aircraft is post-processed using a wake flow field post-processing program to obtain a flow field display file readable by Tecplot software. A multibody dynamics post-processing program is then used to read in the motion parameter files of the cone-shaped rigid body and the hose and the surface mesh file of the active control cone output at each time iteration step of the multibody dynamics kinematics, and to generate an animation display file of the hose-active control cone.

[0070] As can be seen, this application calculates the wake flow field of the refueling aircraft to generate a wake flow field file, and obtains aerodynamic databases of the baseline configuration and rudder configuration of the active control cone under different incoming flow conditions; it performs coupled simulations of the unsteady URANS flow field solver and the multibody dynamics solver, and determines the aerodynamic damping coefficient of the active control cone by combining the aerodynamic database; it uses the aerodynamic damping coefficient as an input parameter, and performs simulation calculations on the active control cone based on the multibody dynamics solver, a preset wake flow field sampling interpolation program, a preset control command, and a preset control algorithm to obtain the control coupling dynamic response of the active control cone; it uses a wake flow field post-processing program to post-process the refueling aircraft wake flow field file to obtain a flow field display file that meets preset readable conditions, and uses the multibody dynamics post-processing program to generate an animation display file of the hose-active control cone based on the motion parameter files of the cone rigid body and the hose output by the multibody dynamics solver and the pre-determined surface mesh file of the active control cone. Therefore, this application calculates the wake flow field of the refueling aircraft and obtains aerodynamic databases of the baseline and rudder configurations of the active control cone under different incoming flow conditions. Then, it combines unsteady computational fluid dynamics, steady computational fluid dynamics, multibody dynamics, and control theory to perform multidisciplinary coupled simulations of the active control cone, obtaining the control-coupled dynamic response of the active control cone under different incoming flow conditions, and displaying it through corresponding files. The above technical solution can achieve high-precision and high-computational-efficiency simulation calculations of the hose-active control cone and meets engineering design requirements.

[0071] The following is based on Figure 4 Taking a specific example of a cross-shaped aerodynamic control surface active control cone sleeve disclosed in the previous paper, the simulation method of the hose-active control cone sleeve in this application is explained in detail:

[0072] Figure 4 The active control cone sleeve and the refueling hose connected to its front end together constitute the hose-cone sleeve active stabilizing refueling device. At the X-axis coordinate position of the cone sleeve's center of mass, four sets of control surfaces are arranged at 90° intervals around the circumference of the cone sleeve. The airfoil of the control surfaces is the NACA0012 symmetrical airfoil, arranged without sweep angle. The control surfaces are numbered in the following order: Figure 5As shown, viewed from the rear of the cone sleeve, control surfaces 1 and 3 are arranged vertically, meaning the axis of rotation is the z-axis, with the -z direction as the positive direction of rotation. Control surfaces 2 and 4 are arranged laterally, meaning the axis of rotation is the y-axis, with the +y direction as the positive direction of rotation. When control surface 1 or 3 rotates in the positive direction, it will experience an aerodynamic force in the +y direction, causing the cone sleeve to move to the right. When control surface 2 or 4 rotates in the positive direction, it will experience an aerodynamic force in the +z direction, causing the cone sleeve to move upward. By controlling the differential motion of each control surface, the rolling motion of the cone sleeve can also be controlled. Furthermore, the geometric parameters and mass characteristics of the refueling cone sleeve and refueling hose are shown in Table 1.

[0073] Table 1

[0074] Mass of the tapered sleeve (kg) 40 Diameter of the conical umbrella canopy (m) 1 <![CDATA[Pitch principal moment of inertia of the tapered sleeve (kg·m 2 ) Jy]]> 6 <![CDATA[Main inertia moment of the tapered sleeve yaw (kg·m 2 ) Jz]]> 6 <![CDATA[Hose material density (kg / m 3 )]]> <![CDATA[1.16455*10 3 ]]> The tensile elastic modulus E (Pa) of the hose <![CDATA[2.0*10 10 ]]> <![CDATA[Cross-sectional area A of the hose (m 2 )]]> <![CDATA[2.5761*10 -3 ]]> <![CDATA[Moment of inertia I of the hose cross-section (kg·m 4 )]]> <![CDATA[2.19742*10 -6 ]]> Total length of hose (m) 24 Hose diameter (mm) 92

[0075] For the active control hose-cone stabilization system with the cruciform aerodynamic control surface, six-component aerodynamic data were calculated for the baseline configuration, the 1-3 control surface synchronous deflection configuration, and the 2-4 control surface synchronous deflection configuration, under the conditions of incoming flow angle of attack α = 0°, 5°, 10°, 15°, 20°, 25°, 30°, 35°, 40°, 50°, and sideslip angle beta = 0°, 4°, respectively. The active control cone deflection moment coefficient rudder effect curve was obtained as shown in Figure 6.

[0076] The height of the fuel tanker wake field is h = 4000m, the incoming flow velocity is 99m / s, and the incoming flow angle of attack α = 2°. In the simulation, the release and stabilization process of the active control cone is first calculated. In the first 40s of the calculation, the active control cone is gradually released at a release rate of 1m / s and stabilizes to the convergent configuration position.

[0077] Then the cone sleeve control surfaces begin to rotate according to the command: the control command is applied to control surfaces 1 and 3, and they rotate synchronously. Figure 7 The angular velocity pattern shown indicates that the rudder deflection angle reaches 30° within approximately 1 second, is maintained for 0.5 seconds, and then rotates at the opposite angular velocity, returning to the initial rudder deflection angle within 1 second. Based on rudder deflection efficiency and direction, the control objective is to make the active control cone first move in the -y direction and then return to the center position.

[0078] Figures 8 to 10 The curves of the X, Y, and Z coordinates of the centroid of the actively controlled cone sleeve as a function of time are presented. Figure 11 The active control cone yaw angle-time curve is given; Figure 12 The active control cone sleeve pitch angle-time curve is given; Figure 13 The velocity-time t curves of the actively controlled cone sleeve in the x, y, and z directions are given.

[0079] like Figure 14As shown, the active control cone is initially positioned in the horizontal plane at t=43.97s. At t=47.47s, under the aerodynamic force of the control surfaces, the cone deflects to its maximum value in the +y direction. At t=49.57s, under the action of the restoring lateral force, the cone deflects to its maximum value in the -y direction. At t=59.97s, the active control cone stabilizes to a central convergent configuration.

[0080] See Figure 15 As shown in the figure, this application discloses a simulation device for a hose-active control cone sleeve, the device comprising:

[0081] Flow field calculation module 11 is used to calculate the flow field of the fuel dispenser wake to generate a fuel dispenser wake flow field file;

[0082] The aerodynamic database acquisition module 12 is used to acquire the aerodynamic database of the reference configuration and rudder configuration of the active control cone under different incoming flow conditions.

[0083] The damping coefficient determination module 13 is used to perform coupled simulation of the unsteady URANS flow field solver and the multibody dynamics solver, and combine the aerodynamic database to determine the aerodynamic damping coefficient of the active control cone sleeve.

[0084] The simulation calculation module 14 is used to take the aerodynamic damping coefficient as an input parameter and perform simulation calculations on the active control cone sleeve based on the multibody dynamics solver, the preset wake flow field sampling interpolation program, the preset control command and the preset control algorithm to obtain the control coupling dynamic response of the active control cone sleeve.

[0085] The display file acquisition module 15 is used to post-process the fuel tanker wake flow field file using the wake flow field post-processing program to obtain a flow field display file that meets the preset readable conditions. Based on the motion parameter files of the cone sleeve rigid body and hose output by the multibody dynamics solver and the pre-determined surface mesh file of the active control cone sleeve, the multibody dynamics post-processing program is used to generate an animation display file of hose-active control cone sleeve.

[0086] As can be seen, this application calculates the wake flow field of the refueling aircraft to generate a wake flow field file, and obtains aerodynamic databases of the baseline configuration and rudder configuration of the active control cone under different incoming flow conditions; it performs coupled simulations of the unsteady URANS flow field solver and the multibody dynamics solver, and determines the aerodynamic damping coefficient of the active control cone by combining the aerodynamic database; it uses the aerodynamic damping coefficient as an input parameter, and performs simulation calculations on the active control cone based on the multibody dynamics solver, a preset wake flow field sampling interpolation program, a preset control command, and a preset control algorithm to obtain the control coupling dynamic response of the active control cone; it uses a wake flow field post-processing program to post-process the refueling aircraft wake flow field file to obtain a flow field display file that meets preset readable conditions, and uses the multibody dynamics post-processing program to generate an animation display file of the hose-active control cone based on the motion parameter files of the cone rigid body and the hose output by the multibody dynamics solver and the pre-determined surface mesh file of the active control cone. Therefore, this application calculates the wake flow field of the refueling aircraft and obtains aerodynamic databases of the baseline and rudder configurations of the active control cone under different incoming flow conditions. Then, it combines unsteady computational fluid dynamics, steady computational fluid dynamics, multibody dynamics, and control theory to perform multidisciplinary coupled simulations of the active control cone, obtaining the control-coupled dynamic response of the active control cone under different incoming flow conditions, and displaying it through corresponding files. The above technical solution can achieve high-precision and high-computational-efficiency simulation calculations of the hose-active control cone and meets engineering design requirements.

[0087] Figure 16 This is a schematic diagram of the structure of an electronic device provided in an embodiment of this application. Specifically, it may include: at least one processor 21, at least one memory 22, a power supply 23, a communication interface 24, an input / output interface 25, and a communication bus 26. The memory 22 stores a computer program, which is loaded and executed by the processor 21 to implement the relevant steps in the simulation method of the hose-active control cone sleeve performed by the electronic device disclosed in any of the foregoing embodiments.

[0088] In this embodiment, the power supply 23 is used to provide operating voltage for each hardware device on the electronic device 20; the communication interface 24 can create a data transmission channel between the electronic device 20 and external devices, and the communication protocol it follows can be any communication protocol applicable to the technical solution of this application, and is not specifically limited here; the input / output interface 25 is used to acquire external input data or output data to the outside world, and its specific interface type can be selected according to specific application needs, and is not specifically limited here.

[0089] The processor 21 may include one or more processing cores, such as a quad-core processor or an octa-core processor. The processor 21 may be implemented using at least one hardware form selected from DSP (Digital Signal Processing), FPGA (Field-Programmable Gate Array), and PLA (Programmable Logic Array). The processor 21 may also include a main processor and a coprocessor. The main processor, also known as a CPU (Central Processing Unit), is used to process data in the wake-up state; the coprocessor is a low-power processor used to process data in the standby state. In some embodiments, the processor 21 may integrate a GPU (Graphics Processing Unit), which is responsible for rendering and drawing the content to be displayed on the screen. In some embodiments, the processor 21 may also include an AI (Artificial Intelligence) processor, which is used to handle computational operations related to machine learning.

[0090] In addition, the memory 22, as a carrier for resource storage, can be a read-only memory, random access memory, disk or optical disk, etc. The resources stored on it include operating system 221, computer program 222 and data 223, etc., and the storage method can be temporary storage or permanent storage.

[0091] The operating system 221 manages and controls the various hardware devices on the electronic device 20 and the computer program 222 to enable the processor 21 to perform calculations and processing on the massive amount of data 223 in the memory 22. The operating system can be Windows, Unix, Linux, etc. The computer program 222, in addition to including a computer program capable of performing the simulation method of the hose-active control cone sleeve executed by the electronic device 20 as disclosed in any of the foregoing embodiments, may further include computer programs capable of performing other specific tasks. The data 223 may include data received by the electronic device from external devices, as well as data collected by its own input / output interface 25.

[0092] Furthermore, embodiments of this application also disclose a computer-readable storage medium storing a computer program. When the computer program is loaded and executed by a processor, it implements the method steps performed during the simulation process of the hose-active control cone sleeve disclosed in any of the foregoing embodiments.

[0093] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since it corresponds to the method disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to in the method section.

[0094] Those skilled in the art will further recognize that the units and algorithm steps of the various 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 various examples have been generally described in terms of functionality in the foregoing description. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of this application.

[0095] The steps of the methods or algorithms described in conjunction with the embodiments disclosed herein can be implemented directly by hardware, a software module executed by a processor, or a combination of both. The software module can be located in random access memory (RAM), main memory, read-only memory (ROM), electrically programmable ROM, electrically erasable programmable ROM, registers, hard disk, removable disk, CD-ROM, or any other form of storage medium known in the art.

[0096] Finally, it should be noted that in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0097] The above provides a detailed description of the simulation method, apparatus, device, and storage medium for a flexible hose-active control cone sleeve provided by the present invention. Specific examples have been used to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the present invention. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of the present invention. Therefore, the content of this specification should not be construed as a limitation of the present invention.

Claims

1. A simulation method for a flexible hose-active control cone sleeve, characterized in that, include: Calculate the wake flow field of the refueling aircraft to generate a refueling aircraft wake flow field file, and obtain the aerodynamic database of the reference configuration and rudder configuration of the active control cone under different incoming flow conditions; Coupled simulations were performed on the unsteady URANS flow field solver and the multibody dynamics solver, and the aerodynamic damping coefficient of the active control cone was determined by combining the aerodynamic database. The aerodynamic damping coefficient is used as an input parameter, and the active control cone sleeve is simulated and calculated based on the multibody dynamics solver, the preset wake flow field sampling interpolation program, the preset control command and the preset control algorithm to obtain the control coupling dynamic response of the active control cone sleeve. The wake flow field file of the refueling machine is post-processed using a wake flow field post-processing program to obtain a flow field display file that meets the preset readability conditions. Based on the motion parameter files of the cone sleeve rigid body and hose output by the multibody dynamics solver, as well as the pre-determined surface mesh file of the active control cone sleeve, an animation display file of hose-active control cone sleeve is generated using the multibody dynamics post-processing program. After acquiring the aerodynamic database of the reference configuration and rudder configuration of the active control cone under different incoming flow conditions, the method further includes: Based on the aerodynamic database, and using the preset aerodynamic coefficient difference expression and the preset aerodynamic torque coefficient difference expression, the control surface effect of each control surface is determined. The process of simulating the active control cone sleeve by using the aerodynamic damping coefficient as an input parameter and based on the multibody dynamics solver, the preset wake flow field sampling interpolation program, the preset control command, and the preset control algorithm also includes: The multibody dynamics solver transmits the centroid position of the active control cone at the current moment to the preset wake flow field sampling and interpolation program, so that the preset wake flow field sampling and interpolation program can perform spatial sampling and interpolation based on the centroid position and in the fuel tanker wake flow field file to obtain the incoming flow velocity vector at the current spatial position, and then return the incoming flow velocity vector to the multibody dynamics solver. The multibody dynamics solver uses the incoming flow velocity vector to interpolate the aerodynamic database to obtain the aerodynamic force / torque of the active control cone under rudder deflection. Then, combined with the preset control command and the control surface effect, the six-component force / torque coefficients of the active control cone under rudder deflection are determined, and the motion parameters of the current time step are updated so that the updated motion parameters can be used to enter the coupling calculation of the next time step. The method further includes: A preset control algorithm is determined for obtaining the rudder deflection law through a control solver based on the motion parameters of the active control cone sleeve, and a preset control command is determined for controlling the active control cone sleeve according to the rudder deflection law; the control solver is used to interact with a multibody dynamics program through a universal data adapter.

2. The simulation method for the hose-active control cone sleeve according to claim 1, characterized in that, The calculation of the fuel dispenser wake flow field to generate a fuel dispenser wake flow field file includes: We used a computational fluid dynamics solver based on structured meshes and RANS models to perform parallel CFD calculations on the flow field of the refueling aircraft wake, in order to generate the flow field file of the refueling aircraft wake.

3. The simulation method for the hose-active control cone sleeve according to claim 1, characterized in that, The aerodynamic database for acquiring the reference configuration and rudder configuration of the active control cone under different incoming flow conditions includes: A six-component aerodynamic / torque database of the baseline and yaw configurations of the active control cone under different incoming flow conditions was obtained using CFD calculation software or wind tunnel testing methods.

4. The simulation method for the hose-active control cone sleeve according to claim 1, characterized in that, The coupled simulation of the unsteady URANS flow field solver and the multibody dynamics solver, combined with the aerodynamic database, to determine the aerodynamic damping coefficient of the active control cone sleeve includes: An unsteady URANS flow field solver including a dynamically overlapping structured mesh was determined, and the unsteady URANS flow field solver and the multibody dynamics solver were coupled and simulated to obtain the motion law of the active control cone sleeve in the unsteady flow field. Based on the motion law and the aerodynamic database, the aerodynamic damping coefficient and aerodynamic torque damping coefficient of the active control cone sleeve are determined.

5. A simulation device for a flexible hose-active control cone sleeve, characterized in that, include: The flow field calculation module is used to calculate the flow field of the fuel dispenser wake to generate a fuel dispenser wake flow field file; The aerodynamic database acquisition module is used to acquire the aerodynamic database of the reference configuration and rudder configuration of the active control cone under different incoming flow conditions. The damping coefficient determination module is used to perform coupled simulation of the unsteady URANS flow field solver and the multibody dynamics solver, and combine the aerodynamic database to determine the aerodynamic damping coefficient of the active control cone sleeve. The simulation calculation module is used to take the aerodynamic damping coefficient as an input parameter and perform simulation calculations on the active control cone sleeve based on the multibody dynamics solver, the preset wake flow field sampling interpolation program, the preset control command and the preset control algorithm to obtain the control coupling dynamic response of the active control cone sleeve. The display file acquisition module is used to post-process the fuel tanker wake flow field file using the wake flow field post-processing program to obtain a flow field display file that meets the preset readable conditions. Based on the motion parameter files of the cone sleeve rigid body and hose output by the multibody dynamics solver and the pre-determined surface mesh file of the active control cone sleeve, the multibody dynamics post-processing program is used to generate an animation display file of hose-active control cone sleeve. After acquiring the aerodynamic database of the reference configuration and rudder configuration of the active control cone under different incoming flow conditions, the device is further used to determine the control surface effect of each control surface based on the aerodynamic database and using the preset aerodynamic coefficient difference expression and the preset aerodynamic torque coefficient difference expression. The simulation calculation module is also used to transmit the centroid position of the active control cone at the current moment to the preset wake flow field sampling interpolation program through the multibody dynamics solver, so that the preset wake flow field sampling interpolation program can perform spatial sampling interpolation based on the centroid position and in the fuel tanker wake flow field file to obtain the incoming flow velocity vector at the current spatial position, and then return the incoming flow velocity vector to the multibody dynamics solver; The multibody dynamics solver uses the incoming flow velocity vector to interpolate the aerodynamic database to obtain the aerodynamic force / torque of the active control cone under rudder deflection. Then, combined with the preset control command and the control surface effect, the six-component force / torque coefficients of the active control cone under rudder deflection are determined, and the motion parameters of the current time step are updated so that the updated motion parameters can be used to enter the coupling calculation of the next time step. The device is also used to determine a preset control algorithm for obtaining the rudder deflection law through a control solver based on the motion parameters of the active control cone sleeve, and to determine a preset control command for controlling the active control cone sleeve according to the rudder deflection law.

6. An electronic device, characterized in that, include: Memory, used to store computer programs; A processor for executing the computer program to implement the steps of the simulation method for the hose-active control cone sleeve as described in any one of claims 1 to 4.

7. A computer-readable storage medium, characterized in that, Used to store a computer program; wherein, when executed by a processor, the computer program implements the steps of the simulation method of the hose-active control cone sleeve as described in any one of claims 1 to 4.

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