Method, device, medium and equipment for configuring wing profile of flight device
Patent Information
- Application Number
- CN202611203983.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-08-10
- Publication Date
- 2026-10-30
AI Technical Summary
现有飞行装置的机翼轮廓的配置依赖直接CFD数值模拟，存在计算成本高、优化效率低、参数化建模精度不足的问题
[0014]本发明实施例上述第一方面提供的方案中，通过接收用户输入的高原适配的期望机翼轮廓的配置参数，根据轮廓配置模型和优化模型协同优化期望机翼轮廓升力、升阻比和力矩，以得到表征所述期望机翼轮廓升力、升阻比和力矩的优化参数集合，再通过验证操作，可快速生成适配高原作业的最优机翼轮廓，大幅提升优化效率与配置精度，解决现有技术无法兼顾高原工况与多目标气动性能的缺陷，增强无人机高原飞行的续航能力与稳定性。
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Figure CN123013288A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the technical field of wing configuration, and more specifically, to a method, apparatus, medium, and device for configuring the wing profile of a flight device. Background Technology
[0002] With the increasing demand for high-altitude operations, electric unmanned aerial vehicles (UAVs) are widely used in high-altitude plateau regions. These regions are characterized by low atmospheric density, low air pressure, large temperature differences, and complex airflow, placing extremely high demands on the aerodynamic performance of UAV wing profiles. Current methods for configuring the wing profiles of flight devices rely on direct CFD numerical simulation, which suffers from high computational costs, low optimization efficiency, and insufficient accuracy in parametric modeling. Summary of the Invention
[0003] To address the aforementioned problems, the present invention aims to provide a method, apparatus, storage medium, and electronic device for configuring the wing profile of a flight device.
[0004] In a first aspect, embodiments of the present invention provide a method for configuring the wing profile of a flight device, including: Receive configuration parameters for the desired wing profile input by the user; The configuration parameters are input into a preset profile configuration model to obtain an initial set of parameters characterizing the lift, lift-to-drag ratio, and moment of the desired wing profile. The initial parameter set is input into a preset optimization model to obtain an optimized parameter set characterizing the lift, lift-to-drag ratio, and torque of the desired wing profile. A preset verification operation is performed on the optimized parameter set to determine the verification reference value of the desired wing; wherein the verification reference value is used to measure the adaptability of the desired wing.
[0005] In some optional implementations, the configuration parameters include position parameters of the contour control points; the contour configuration model includes a control point configuration model and a prediction model; the step of inputting the configuration parameters into a preset contour configuration model to obtain an initial set of parameters characterizing the lift, lift-to-drag ratio, and moment of the desired wing contour includes: The position parameters of the contour control points are input into the control point configuration model to obtain a set of control point positions; The set of control point locations is input into a preset prediction model to obtain a prediction function, which serves as the initial parameter set characterizing the lift, lift-to-drag ratio, and torque of the desired wing profile.
[0006] In some optional implementations, the control point model includes an upper surface configuration model and a lower surface configuration model; the step of inputting the position parameters of the contour control points into the control point configuration model to obtain a set of control point positions includes: The leading edge control point, upper surface control point, lower surface control point and trailing edge control point in the contour control points are determined, and the position parameters of the leading edge control point, the upper surface control point, the lower surface control point and the trailing edge control point are normalized to obtain normalized parameters. The preset mapping parameters and the position parameters of the upper surface control points are input into the upper surface configuration model to obtain the first position value of the upper surface control points in the desired wing profile height direction; The mapping parameters and the position parameters of the lower surface control points are input into the preset lower surface configuration model to obtain the second position value of the lower surface control points in the desired wing profile height direction; Based on the first position value and the second position value, construct a set of control point positions.
[0007] In some optional implementations, the prediction model includes a lift prediction model, a lift-to-drag ratio prediction model, and a torque prediction model; the step of inputting the set of control point positions into a preset prediction model to obtain a prediction function includes: The set of control point locations is used as input and fed into the lift prediction model, the lift-to-drag ratio prediction model, and the torque prediction model, respectively, to obtain the lift response value, lift-to-drag ratio response value, and torque response value, which are then used as prediction functions.
[0008] In some optional implementations, the step of inputting the initial parameter set into a preset optimization model to obtain an optimized parameter set characterizing the lift, lift-to-drag ratio, and moment of the desired wing profile includes: Set the initial parameter set as the optimized expression set; By using a pre-set optimization model and under set constraints, a set of optimized parameters characterizing the lift, lift-to-drag ratio, and torque of the desired wing profile is obtained.
[0009] In some optional implementations, before performing a preset verification operation on the optimized parameter set to determine the verification reference value of the desired wing, the method further includes: Based on preset airfoil preference conditions, target optimization parameters that match the set of optimization parameters are selected; wherein, the airfoil preference conditions include the lift parameter of the target optimization parameter being greater than or equal to a first preset threshold and the torque parameter of the target optimization parameter being less than or equal to a second preset threshold.
[0010] In some optional implementations, before inputting the configuration parameters into a preset profile configuration model to obtain an initial set of parameters characterizing the lift, lift-to-drag ratio, and moment of the desired wing profile, the method further includes: Based on the preset parameter baseline structure, determine the configuration type of the configuration parameter and the parameter set corresponding to the configuration type; If there is no takeoff type and / or landing type in the configuration type, the second parameter set corresponding to the takeoff type and / or landing type is estimated using the first parameter set corresponding to the cruise type in the configuration type, and the first parameter set and the second parameter set are used as the initial parameter set; If the configuration type does not have a cruise type, determine whether the configuration type has a takeoff type and a landing type; In the case where the configuration type includes the takeoff type and the landing type, the fourth parameter set corresponding to the cruise type is estimated using the third parameter set corresponding to the takeoff type and the landing type; If the configuration type does not simultaneously have the takeoff type and the landing type, an error message will be displayed to the user indicating that the data is abnormal.
[0011] Secondly, embodiments of the present invention also provide a wing profile configuration device for a flight device, comprising: The receiving module is used to receive configuration parameters of the desired wing profile input by the user; The first obtaining module is used to input the configuration parameters into a preset profile configuration model to obtain an initial parameter set characterizing the lift, lift-to-drag ratio and torque of the desired wing profile. The second obtaining module is used to input the initial parameter set into a preset optimization model to obtain an optimized parameter set characterizing the lift, lift-to-drag ratio and torque of the desired wing profile; The determination module is used to perform a preset verification operation on the set of optimization parameters to determine the verification reference value of the desired wing; wherein the verification reference value is used to measure the adaptability of the desired wing.
[0012] Thirdly, embodiments of the present invention also provide a computer storage medium storing computer-executable instructions for use in the wing profile configuration method of the flight device described in any one of the above claims.
[0013] Fourthly, embodiments of the present invention also provide an electronic device, comprising: At least one processor; and, A memory communicatively connected to the at least one processor; wherein, The memory stores instructions that can be executed by the at least one processor, which, when executed, enable the at least one processor to perform the wing profile configuration method of the flight device described in any of the preceding descriptions.
[0014] In the solution provided by the first aspect of the present invention, by receiving the configuration parameters of the desired wing profile for high-altitude adaptation input by the user, the lift, lift-drag ratio and torque of the desired wing profile are optimized collaboratively according to the profile configuration model and the optimization model to obtain a set of optimized parameters characterizing the lift, lift-drag ratio and torque of the desired wing profile. Then, through the verification operation, the optimal wing profile adapted to high-altitude operations can be quickly generated, which greatly improves the optimization efficiency and configuration accuracy, solves the defect of the prior art that cannot take into account both high-altitude working conditions and multi-target aerodynamic performance, and enhances the endurance and stability of UAV flight at high altitudes.
[0015] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, preferred embodiments are described below in detail with reference to the accompanying drawings. Attached Figure Description
[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention 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 some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0017] Figure 1 A flowchart illustrating a wing profile configuration method for a flight device provided by an embodiment of the present invention is shown; Figure 2 This diagram illustrates the structure of a wing profile configuration device for a flight apparatus provided in an embodiment of the present invention. Figure 3 A schematic diagram of the structure of an electronic device for performing a wing profile configuration method for a flight device, provided by an embodiment of the present invention, is shown. Detailed Implementation
[0018] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.
[0019] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.
[0020] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.
[0021] This invention provides a method for configuring the wing profile of a flight device, see [link to relevant documentation]. Figure 1 As shown, the execution subject of this method can be a smart terminal, such as a personal computer, mobile phone, tablet, or server. The method includes: Step 101: Receive the configuration parameters of the desired wing profile input by the user.
[0022] In this embodiment, the configuration parameters of the desired wing profile can be the two-dimensional coordinates of several upper surface control points and several lower surface control points artificially set on the desired wing profile. Here, the horizontal axis of the two-dimensional coordinates represents the forward and backward direction of the desired wing, and the vertical axis represents the height direction of the desired wing. The configuration parameters may also include dimensional constraints, such as chord length, relative thickness, camber, leading edge radius range, etc., which are not limited here.
[0023] Step 102: Input the configuration parameters into the preset profile configuration model to obtain the initial parameter set characterizing the lift, lift-to-drag ratio and torque of the desired wing profile.
[0024] Specifically, step 102 above, "inputting the configuration parameters into the preset profile configuration model to obtain the initial parameter set characterizing the lift, lift-to-drag ratio and torque of the desired wing profile," includes steps A1 and A2.
[0025] Step A1: Input the position parameters of the contour control points into the control point configuration model to obtain the control point position set.
[0026] Step A2: Input the set of control point locations into the preset prediction model to obtain the prediction function, which serves as the initial parameter set characterizing the lift, lift-to-drag ratio, and moment of the desired wing profile.
[0027] In this embodiment, by setting a control point configuration model and a prediction model, the two models are configured with each other to obtain an initial set of parameters characterizing the lift, lift-to-drag ratio, and torque of the desired wing profile, thereby further improving the accuracy of obtaining the desired wing profile in the future.
[0028] Specifically, the control point model includes an upper surface configuration model and a lower surface configuration model; the above step A1 "inputting the position parameters of the contour control points into the control point configuration model to obtain the control point position set" includes steps A11 to A15.
[0029] Step A11: Determine the leading edge control point, upper surface control point, lower surface control point, and trailing edge control point among the contour control points, and normalize the position parameters of the leading edge control point, upper surface control point, lower surface control point, and trailing edge control point to obtain normalized parameters.
[0030] In this embodiment, the desired wing profile is determined by the abscissa along the chord length direction. x-axis Normalized to values in [0,1], x-axis A value of 0 corresponds to the leading edge control point and its x-coordinate. Let 1 correspond to the trailing edge control point, and let the x-coordinate be... and ordinate It can be used to represent the positional parameters of control points on the upper surface. and represent the position parameters of the control points on the lower surface. .
[0031] Step A12: Input the preset mapping parameters and the position parameters of the upper surface control points into the preset upper surface configuration model to obtain the first position value of the upper surface control points in the desired wing profile height direction.
[0032] In this embodiment, a general model based on cubic Bézier curves is used:
[0033] in, Curve parameters (and x-axis) Mapping), that is, mapping parameters. The two-dimensional coordinates (xi, yi) correspond to the leading edge control point, the two upper (or lower) surface control points, and the trailing edge control point, respectively. , is the basis function of the cubic Bézier curve, ensuring that the curve is smooth and passes through the leading and trailing control points.
[0034] In this embodiment, the Bézier curve parameter t is mapped to the chord length coordinate x (to avoid trailing edge stretching distortion), that is... , .
[0035] The first point of overlap between the upper and lower surface control points and the leading edge point The last control point on the upper and lower surfaces coincides with the trailing edge point. Intermediate control point: Upper surface control point: Lower surface control points: .
[0036] Step A13: Input the preset mapping parameters and the position parameters of the upper surface control points into the upper surface configuration model to obtain the first position value of the upper surface control points in the desired wing profile height direction.
[0037] In this embodiment, the upper surface configuration model is as follows: .
[0038] Step A14: Input the mapping parameters and the position parameters of the lower surface control points into the lower surface configuration model to obtain the second position values of the lower surface control points in the desired wing profile height direction.
[0039] In this embodiment, the lower surface configuration model is as follows: .
[0040] Step A15: Construct a set of control point locations based on the first and second position values.
[0041] In this embodiment, Depend on Inverse solution (e.g.) ,correspond It can constrain the x-coordinates of control points on the upper (or lower) surface (e.g.) , Only optimize the ordinate. , , , This effectively reduces the number of parameters and ensures the desired smoothness of the wing profile.
[0042] In this embodiment, based on the parameterization results of the Bézier curve, 4 to 6 key variables are ultimately selected, namely... .in, and This represents the ordinate of the control point on the upper surface (range [0.02, 0.15]). and Indicates the ordinate of the control points on the upper surface (range [ 0.1, 0.05]), For the angle of attack, the range is [ [2°, 8°]. In other words, by setting the upper surface configuration model and the lower surface configuration model, the configuration parameters of the desired wing profile can be converted into curves that meet the requirements, so that the constructed desired wing profile has high stability.
[0043] In some examples, geometric and aerodynamic constraints are set to ensure that the final set of control point locations conforms to the maximum airfoil thickness. Geometric constraints, lift coefficient (Avoid stalling), drag coefficient The aerodynamic constraints are determined. N sample points are generated within the variable range using Latin hypercube sampling. For each sample point (i.e., the configuration parameters of the sample properties), perform the following operations: generate an airfoil coordinate file (.dat format) from the configuration parameters using Bézier curves, and calculate the airfoil profile lift of the sample airfoil profile using CFD software (such as Fluent, XFOIL, etc.). wing profile drag wing profile moment , obtain sample set ,in The atmospheric conditions for calculating anisotropic performance parameters using CFD software were set as follows: air density... The value corresponding to an altitude of 8000 meters (e.g., 0.525 kg / m³), air temperature. The altitude corresponding to 8000 meters (e.g., 236.15K) is set, and the speed is set to the vacuum speed corresponding to the airspeed indicator airspeed (e.g., 30.6m / s) to obtain sample data. The contour configuration model is then trained using the sample data to obtain a trained contour configuration model.
[0044] Specifically, the prediction model includes a lift prediction model, a lift-to-drag ratio prediction model, and a torque prediction model; the above step A2, "inputting the set of control point positions into the preset prediction model to obtain the prediction function," includes step A21.
[0045] Step A21: The set of control point locations is used as input and fed into the lift prediction model, lift-to-drag ratio prediction model, and torque prediction model respectively to obtain the lift response value, lift-to-drag ratio response value, and torque response value, which are then used as prediction functions.
[0046] In this embodiment, based on the Kriging model, the lift response value, lift-to-drag ratio response value, and torque response value can be obtained. The Kriging model is as follows: , in, The global mean. It is a Gaussian random process with covariance. ( For related functions, (Parameters to be estimated), input sample set For the three optimization objectives, namely lift response value Boost-to-drag ratio response value Torque response value , construct an independent Kriging model.
[0047] In this embodiment, the accuracy of the Kriging model is verified using cross-validation, requiring... (Determination coefficient), if the accuracy is insufficient, additional sample points are added to obtain the final prediction function for the lift response value. Prediction function of lift-to-drag ratio response Prediction function of torque response value .
[0048] Specifically, after step 102 above, "inputting the configuration parameters into the preset profile configuration model to obtain the initial parameter set characterizing the lift, lift-to-drag ratio and torque of the desired wing profile", the method further includes the following steps D1 to D5.
[0049] Step D1: Based on the preset parameter baseline structure, determine the configuration type of the configuration parameter and the parameter set corresponding to the configuration type.
[0050] In this embodiment, the parameter reference structure can be [normal, , , , ]; [up, , , , ]; [down, , , , ],in, , , , These represent the desired wing profile lift, desired wing profile drag, desired wing profile moment, and desired wing cruise speed, respectively, under cruise mode. , , , These represent the desired wing profile lift, desired wing profile drag, desired wing profile moment, and desired wing takeoff acceleration, respectively, under each takeoff type. , , , These represent the desired wing profile lift, desired wing profile drag, desired wing profile moment, and desired wing landing acceleration, respectively, under different landing types.
[0051] Step D2: If there is no takeoff type and / or landing type in the configuration type, estimate the second parameter set corresponding to the takeoff type and / or landing type using the first parameter set corresponding to the cruise type in the configuration type, and use the first parameter set and the second parameter set as the initial parameter set.
[0052] In this embodiment, the configuration type does not include takeoff and / or landing types, i.e., [up, , , , ]; [down, , , , At least one is an empty set, and through a pre-defined prediction model, with [normal, , , , [Input condition] is used to estimate the second set of parameters corresponding to the takeoff type and / or landing type. The estimation model here can be an existing general model that can convert the parameter set of the cruise type into the parameter set of the takeoff type and landing type.
[0053] If the configuration type does not have a cruise type, step D3 determines whether the configuration type has a takeoff type and a landing type.
[0054] Step D4: If the configuration type includes takeoff type and landing type, estimate the fourth parameter set corresponding to the cruise type using the third parameter set corresponding to the takeoff type and landing type.
[0055] In this embodiment, the configuration type does not include [normal, , , , The prediction model needs to simultaneously possess [up, , , , ]; [down, , , , ], through a pre-set prediction model, with [up, , , , ]; [down, , , , Using [] as input conditions, the third parameter set corresponding to the cruise type is estimated. This general model also has the ability to convert the parameter sets of takeoff type and landing type into the parameter set of cruise type.
[0056] Step D5: If the configuration type does not simultaneously include both takeoff and landing types, output an error message to the user indicating data anomalies.
[0057] In this embodiment, the configuration type may not simultaneously have a takeoff type and a landing type; it may only have a takeoff type or a landing type. If the configuration type does not simultaneously have a takeoff type and a landing type, the prediction model cannot generate the corresponding parameter set.
[0058] In this embodiment, by setting the prediction model, the initial parameter set can be further improved, thereby further enhancing the accuracy of the subsequently obtained desired wing profile.
[0059] Step 103: Input the initial parameter set into the preset optimization model to obtain the optimized parameter set characterizing the lift, lift-to-drag ratio and torque of the desired wing profile.
[0060] Specifically, step 103 above, "inputting the initial parameter set into the preset optimization model to obtain the optimized parameter set characterizing the lift, lift-to-drag ratio and torque of the desired wing profile," includes steps B1 and B2.
[0061] Step B1: Set the initial parameter set to the optimized expression set.
[0062] In this embodiment, the expression for optimizing the expression set is as follows:
[0063] Step B2: Using a pre-set optimization model and under set constraints, obtain a set of optimized parameters characterizing the lift, lift-to-drag ratio, and torque of the desired wing profile.
[0064] In this embodiment, the optimization model employs NSGA-II (Non-dominated sorting genetic algorithm) to randomly generate an optimization expression set of N=200 individuals. Each individual is sorted according to three objectives, and a Pareto front is defined to ensure the diversity of the solution set. The next generation is generated through genetic operations, iterating for 50-100 generations until the Pareto front stabilizes. The optimization model uses a penalty function method to penalize individuals that violate constraints, ensuring that the optimization parameter set satisfies geometric and aerodynamic constraints.
[0065] Step 104: Perform a preset verification operation on the optimized parameter set to determine the verification reference value of the desired wing; wherein, the verification reference value is used to measure the adaptability of the desired wing.
[0066] Specifically, before step 104, "perform a preset verification operation on the optimized parameter set to determine the verification reference value of the desired wing", the method also includes step C1.
[0067] Step C1: Based on the preset airfoil optimization conditions, select the target optimization parameters that match the set of optimization parameters; wherein, the airfoil optimization conditions include the lift parameter of the target optimization parameter being greater than or equal to a first set threshold and the torque parameter of the target optimization parameter being less than or equal to a second set threshold.
[0068] In this embodiment, the lift parameter of the target optimization parameter being greater than or equal to the first preset threshold can be... The torque parameter of the target optimization parameter being less than or equal to the second set threshold can be... And also take into account the lift-to-drag ratio ( This meets the endurance requirements of high-altitude drones.
[0069] In this embodiment, the verification operation may involve re-performing a high-precision CFD simulation on the selected target optimization parameters to verify the prediction error value of the target optimization parameters, i.e., verifying the reference value. (At that time, the target optimization parameters are qualified). The final qualified target optimization parameters are used to generate the desired wing profile.
[0070] This invention provides a method for configuring the wing profile of a flight device. By receiving configuration parameters of a desired wing profile suitable for high-altitude operations input by a user, the method collaboratively optimizes the lift, lift-drag ratio, and torque of the desired wing profile based on a profile configuration model and an optimization model to obtain a set of optimized parameters characterizing the lift, lift-drag ratio, and torque of the desired wing profile. Through verification operations, the method can quickly generate an optimal wing profile suitable for high-altitude operations, significantly improving optimization efficiency and configuration accuracy. This addresses the shortcomings of existing technologies that cannot simultaneously consider high-altitude operating conditions and multi-target aerodynamic performance, thereby enhancing the endurance and stability of UAVs flying at high altitudes.
[0071] The above details the method and process for configuring the wing profile of the flight device. This method can also be implemented using a corresponding device, the structure and function of which will be described in detail below.
[0072] Based on the same inventive concept, embodiments of the present invention also provide a wing profile configuration device for a flight device, see [link to relevant documentation]. Figure 2 As shown, the device includes: The receiving module 201 is used to receive configuration parameters of the desired wing profile input by the user; The first module 202 is used to input configuration parameters into a preset profile configuration model to obtain an initial parameter set characterizing the lift, lift-to-drag ratio and torque of the desired wing profile. The second module 203 is used to input the initial parameter set into the preset optimization model to obtain the optimized parameter set characterizing the lift, lift-to-drag ratio and torque of the desired wing profile. The determination module 204 is used to perform a preset verification operation on the set of optimized parameters to determine the verification reference value of the desired wing; wherein, the verification reference value is used to measure the adaptability of the desired wing.
[0073] In some optional implementations, the first obtaining module 202 is further configured to input the position parameters of the contour control points into the control point configuration model to obtain a set of control point positions; input the set of control point positions into a preset prediction model to obtain a prediction function, which serves as an initial parameter set characterizing the lift, lift-to-drag ratio, and moment of the desired wing profile.
[0074] In some optional implementations, the first obtaining module 202 is further configured to determine the leading edge control point, upper surface control point, lower surface control point, and trailing edge control point among the contour control points, and normalize the position parameters of the leading edge control point, upper surface control point, lower surface control point, and trailing edge control point to obtain normalized parameters; input the preset mapping parameters and the position parameters of the upper surface control point into a preset upper surface configuration model to obtain a first position value of the upper surface control point in the desired wing contour height direction; input the preset mapping parameters and the position parameters of the upper surface control point into a preset upper surface configuration model to obtain a first position value of the upper surface control point in the desired wing contour height direction; input the mapping parameters and the position parameters of the lower surface control point into a preset lower surface configuration model to obtain a second position value of the lower surface control point in the desired wing contour height direction; and construct a control point position set based on the first position value and the second position value.
[0075] In some optional implementations, the first obtaining module 202 is further configured to take the set of control point positions as input and input them into the lift prediction model, lift-to-drag ratio prediction model and torque prediction model respectively to obtain the lift response value, lift-to-drag ratio response value and torque response value, and use them as prediction functions.
[0076] In some optional implementations, the second obtaining module 203 is further configured to set the initial parameter set as an optimized expression set; and to obtain an optimized parameter set characterizing the lift, lift-to-drag ratio and torque of the desired wing profile through a preset optimization model and under set constraints.
[0077] In some optional embodiments, the device further includes a screening module for screening target optimization parameters that match the set of optimization parameters based on preset airfoil preference conditions; wherein the airfoil preference conditions include the lift parameter of the target optimization parameter being greater than or equal to a first preset threshold and the torque parameter of the target optimization parameter being less than or equal to a second preset threshold.
[0078] In some optional embodiments, the device further includes an output module for determining, based on a preset parameter reference structure, the configuration type of the configuration parameters and the parameter set corresponding to the configuration type; if the configuration type does not have a takeoff type and / or a landing type, estimating the second parameter set corresponding to the takeoff type and / or landing type using the first parameter set corresponding to the cruise type in the configuration type, and using the first and second parameter sets as initial parameter sets; if the configuration type does not have a cruise type, determining whether the configuration type has a takeoff type and a landing type; if the configuration type has a takeoff type and a landing type, estimating the fourth parameter set corresponding to the cruise type using the third parameter set corresponding to the takeoff type and a landing type; and if the configuration type does not simultaneously have a takeoff type and a landing type, outputting a prompt message indicating abnormal data to the user.
[0079] This invention also provides a computer storage medium storing computer-executable instructions, including a program for executing the above-described method for configuring the wing profile of a flight device. These computer-executable instructions can execute the methods in any of the above-described method embodiments.
[0080] The computer storage medium can be any available medium or data storage device that a computer can access, including but not limited to magnetic storage (e.g., floppy disk, hard disk, magnetic tape, magneto-optical disk (MO)), optical storage (e.g., CD, DVD, BD, HVD), and semiconductor storage (e.g., ROM, EPROM, EEPROM, non-volatile memory (NAND FLASH), solid-state drive (SSD)).
[0081] Figure 3 A structural block diagram of an electronic device according to another embodiment of the present invention is shown. The electronic device 1100 may be a host server with computing capabilities, a personal computer (PC), or a portable computer or terminal, etc. The specific embodiments of the present invention do not limit the specific implementation of the electronic device.
[0082] The electronic device 1100 includes at least one processor 1110, a communications interface 1120, a memory array 1130, and a bus 1140. The processor 1110, the communications interface 1120, and the memory 1130 communicate with each other via the bus 1140.
[0083] The communication interface 1120 is used to communicate with network elements, including, for example, virtual machine management centers and shared storage.
[0084] Processor 1110 is used to execute programs. Processor 1110 may be a central processing unit (CPU), an application-specific integrated circuit (ASIC), or one or more integrated circuits configured to implement embodiments of the present invention.
[0085] Memory 1130 is used for executable instructions. Memory 1130 may include high-speed RAM memory and may also include non-volatile memory, such as at least one disk storage device. Memory 1130 may also be a memory array. Memory 1130 may also be divided into blocks, and the blocks may be combined into virtual volumes according to certain rules. The instructions stored in memory 1130 can be executed by processor 1110 to enable processor 1110 to execute the wing profile configuration method of the flight device in any of the above method embodiments.
[0086] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.
Claims
1. A method for configuring the wing profile of a flight device, characterized in that, The method includes: Receive configuration parameters for the desired wing profile input by the user; The configuration parameters are input into a preset profile configuration model to obtain an initial set of parameters characterizing the lift, lift-to-drag ratio, and moment of the desired wing profile. The initial parameter set is input into a preset optimization model to obtain an optimized parameter set characterizing the lift, lift-to-drag ratio, and torque of the desired wing profile. A preset verification operation is performed on the optimized parameter set to determine the verification reference value of the desired wing; wherein the verification reference value is used to measure the adaptability of the desired wing.
2. The method according to claim 1, characterized in that, The configuration parameters include the position parameters of the contour control points; the contour configuration model includes a control point configuration model and a prediction model; the configuration parameters are input into a preset contour configuration model to obtain an initial set of parameters characterizing the lift, lift-to-drag ratio, and moment of the desired wing contour, including: The position parameters of the contour control points are input into the control point configuration model to obtain a set of control point positions; The set of control point locations is input into a preset prediction model to obtain a prediction function, which serves as the initial parameter set characterizing the lift, lift-to-drag ratio, and torque of the desired wing profile.
3. The method according to claim 2, characterized in that, The control point model includes an upper surface configuration model and a lower surface configuration model; the step of inputting the position parameters of the contour control points into the control point configuration model to obtain a set of control point positions includes: The leading edge control point, upper surface control point, lower surface control point and trailing edge control point in the contour control points are determined, and the position parameters of the leading edge control point, the upper surface control point, the lower surface control point and the trailing edge control point are normalized to obtain normalized parameters. The preset mapping parameters and the position parameters of the upper surface control points are input into the upper surface configuration model to obtain the first position value of the upper surface control points in the desired wing profile height direction; The mapping parameters and the position parameters of the lower surface control points are input into the preset lower surface configuration model to obtain the second position value of the lower surface control points in the desired wing profile height direction; Based on the first position value and the second position value, construct a set of control point positions.
4. The method according to claim 2, characterized in that, The prediction model includes a lift prediction model, a lift-to-drag ratio prediction model, and a torque prediction model; the step of inputting the set of control point positions into the preset prediction model to obtain the prediction function includes: The set of control point locations is used as input and fed into the lift prediction model, the lift-to-drag ratio prediction model, and the torque prediction model, respectively, to obtain the lift response value, lift-to-drag ratio response value, and torque response value, which are then used as prediction functions.
5. The method according to claim 1, characterized in that, The step of inputting the initial parameter set into a preset optimization model to obtain an optimized parameter set characterizing the lift, lift-to-drag ratio, and moment of the desired wing profile includes: Set the initial parameter set as the optimized expression set; By using a pre-set optimization model and under set constraints, a set of optimized parameters characterizing the lift, lift-to-drag ratio, and torque of the desired wing profile is obtained.
6. The method according to claim 1, characterized in that, Before performing a preset verification operation on the optimized parameter set to determine the verification reference value of the desired wing, the method further includes: Based on preset airfoil preference conditions, target optimization parameters that match the set of optimization parameters are selected; wherein, the airfoil preference conditions include the lift parameter of the target optimization parameter being greater than or equal to a first preset threshold and the torque parameter of the target optimization parameter being less than or equal to a second preset threshold.
7. The method according to any one of claims 1-6, characterized in that, After inputting the configuration parameters into a preset profile configuration model to obtain an initial set of parameters characterizing the lift, lift-to-drag ratio, and moment of the desired wing profile, the method further includes: Based on the preset parameter baseline structure, determine the configuration type of the configuration parameter and the parameter set corresponding to the configuration type; If there is no takeoff type and / or landing type in the configuration type, the second parameter set corresponding to the takeoff type and / or landing type is estimated using the first parameter set corresponding to the cruise type in the configuration type, and the first parameter set and the second parameter set are used as the initial parameter set; If the configuration type does not have a cruise type, determine whether the configuration type has a takeoff type and a landing type; In the case where the configuration type includes the takeoff type and the landing type, the fourth parameter set corresponding to the cruise type is estimated using the third parameter set corresponding to the takeoff type and the landing type; If the configuration type does not simultaneously have the takeoff type and the landing type, an error message will be displayed to the user indicating that the data is abnormal.
8. A wing profile configuration device for a flight apparatus, characterized in that, The device includes: The receiving module is used to receive configuration parameters of the desired wing profile input by the user; The first obtaining module is used to input the configuration parameters into a preset profile configuration model to obtain an initial parameter set characterizing the lift, lift-to-drag ratio and torque of the desired wing profile. The second obtaining module is used to input the initial parameter set into a preset optimization model to obtain an optimized parameter set characterizing the lift, lift-to-drag ratio and torque of the desired wing profile; The determination module is used to perform a preset verification operation on the set of optimization parameters to determine the verification reference value of the desired wing; wherein the verification reference value is used to measure the adaptability of the desired wing.
9. A computer storage medium, characterized in that, The computer storage medium stores computer-executable instructions for executing the wing profile configuration method of the flight device according to any one of claims 1 to 7.
10. An electronic device, characterized in that, include: At least one processor; as well as, A memory communicatively connected to the at least one processor; wherein, The memory stores instructions that can be executed by the at least one processor to enable the at least one processor to perform the wing profile configuration method of the flight device according to any one of claims 1 to 7.