A method for solving parameters of embedded air data system based on triangulation
By constructing parameter calculation coefficients and tetrahedral meshes based on triangulation, the stability and efficiency problems of existing embedded atmospheric data system calculation methods are solved, achieving efficient and accurate atmospheric parameter calculation.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
- Filing Date
- 2026-04-17
- Publication Date
- 2026-07-21
AI Technical Summary
Existing methods for solving embedded atmospheric data systems, such as neural networks and least squares, have problems with stability and convergence, and flight test calibration costs are high. The convergence of iterative lookup table methods depends on the initial value, which affects the accuracy and efficiency of the solution.
A triangulation-based method is adopted. By selecting the pressure measurement hole layout in the aerodynamic simulation, the parameter solution coefficients are constructed. Tetrahedral meshes are generated using Delaunay triangulation, and atmospheric parameters are solved by interpolation calculation, thus avoiding iterative initial values and iterative calculations.
It enables efficient and accurate calculation of atmospheric parameters under any environmental and climatic conditions, reducing flight test calibration costs and improving system stability and calculation efficiency.
Smart Images
Figure CN122432460A_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of atmospheric data technology, and specifically relates to a parameter calculation method for embedded atmospheric data systems based on triangulation. Background Technology
[0002] The atmospheric data system is one of the essential systems on board an aircraft. Throughout the entire lifecycle and within the entire flight envelope, it provides atmospheric data parameters such as pressure altitude, Mach number, angle of attack, and sideslip angle to the aircraft's flight control system, avionics mission system, and related electromechanical systems. This data is used for flight control, navigation displays, weapon control, and cockpit pressurization and temperature regulation. Reliable information is a prerequisite for the flight control system to improve flight quality, maximize overall aircraft performance, and ensure flight safety. The atmospheric data system should be designed to provide accurate and reliable atmospheric parameters under any environmental and climatic conditions.
[0003] Embedded atmospheric data systems eliminate the need for total static pressure sensors, angle-of-attack sensors, and sideslip angle sensors. They rely entirely on the correlation between pressure from multiple sensors and static pressure, Mach number, angle of attack, and sideslip angle to calculate flight atmospheric parameters. A solution model needs to be established based on the variation patterns between pressure measurements from embedded atmospheric pressure sensors and atmospheric parameters to achieve embedded atmospheric data calculation. Common methods for embedded atmospheric data system calculation include neural networks, least squares methods, and iterative lookup tables. Neural network algorithms can affect the learning results of already learned samples when new samples are added, and flight testing and calibration costs are very high, with unpredictable stability. Least squares methods obtain high-precision solutions by repeatedly linearizing aerodynamic models, a time-consuming process with potential stability issues; ensuring convergence requires high-quality initial values. Iterative lookup tables rely on repeated interpolation of initial values within a data table; their convergence depends on the initial values and data table settings, and convergence issues can adversely affect parameter calculation. Summary of the Invention
[0004] A method for parameter calculation in an embedded atmospheric data system based on triangulation, the method comprising:
[0005] Step S1: Perform aerodynamic simulation within the entire envelope range, and select the layout of pressure measurement holes on the aircraft surface based on the simulation results;
[0006] Step S2: For the pressure measuring hole layout, construct a set of parameter calculation coefficients that are one-to-one mapped to Mach number, angle of attack, and sideslip angle. and ;
[0007] Step S3: Based on the simulation results of step S1, calculate the parameter solution coefficients corresponding to multiple discrete flight states. , , This forms a solution coefficient table, which constitutes a set of coefficients. and A three-dimensional dataset with coordinate axes;
[0008] Step S4: Using the Delaunay triangulation method, spatially divide the scattered data points in the three-dimensional dataset obtained in step S3 to generate a three-dimensional tetrahedral mesh covering the dataset.
[0009] Step S5: Obtain the pressure measurement value of the real-time pressure measuring hole, and calculate the real-time solution coefficient according to the construction method in step S2. , , ;
[0010] Step S6: Use the real-time solution coefficients obtained in step S5 as query points, locate them in the tetrahedral mesh generated in step S4, and determine the specific tetrahedron to which they belong.
[0011] Step S7: Based on the known Mach number, angle of attack, and sideslip angle at each vertex of the specific tetrahedron, the atmospheric data parameters corresponding to the real-time measurement values are calculated by interpolation.
[0012] Preferably, in step S1, the selected pressure testing hole layout satisfies the following conditions:
[0013] Pressure measuring points are arranged on the top, bottom, left, and right sides of the fuselage;
[0014] All pressure measurement points are located in the stable flow field region;
[0015] There are at least two sets of pressure measurement points, and the pressure difference between them is sensitive to changes in Mach number;
[0016] There are at least two sets of pressure measurement points whose pressure difference is sensitive and monotonic to changes in angle of attack.
[0017] There are at least two sets of pressure measurement points, whose pressure difference is sensitive to and monotonic with changes in the sideslip angle.
[0018] Preferably, in step S2, the parameter calculation coefficients , and Pressure coefficient of each pressure measuring hole or pressure It is constructed by combination and satisfies the monotonicity condition: As the angle of attack changes monotonically, As the sideslip angle changes monotonically, It changes monotonically with Mach number.
[0019] Preferably, in step S4, the tetrahedral mesh generated by the Delaunay triangulation method does not contain other data points from the three-dimensional dataset inside the circumscribed sphere of any tetrahedron.
[0020] Preferably, in step S6, the location is determined by calculating the spatial relationship between the query point and each tetrahedron. Specifically, this is achieved by calling the pointLocation function in Matlab, which provides the tetrahedron to which the query point belongs and the corresponding centroid coordinates.
[0021] Preferably, in step S7, the interpolation calculation uses barycentric coordinates for linear interpolation.
[0022] An embedded atmospheric data processing system for implementing the method includes:
[0023] The preprocessing module stores the parameterized coefficients pre-established through aerodynamic simulation and triangulation. , , [Indexed tetrahedral mesh data and vertex atmospheric parameters;]
[0024] The data acquisition module is used to acquire pressure measurement values from multiple surface pressure testing holes in real time.
[0025] The coefficient calculation module is used to calculate the real-time solution coefficients according to the pressure measurement values and predetermined rules. , , ];
[0026] The grid positioning module is used to take the real-time solution coefficients as input and quickly locate the tetrahedron in the tetrahedral grid data.
[0027] The parameter calculation module is used to interpolate based on the located tetrahedral vertex data and output the real-time Mach number, angle of attack, and sideslip angle.
[0028] An aircraft comprising:
[0029] The fuselage has multiple pressure measuring holes arranged in the aforementioned pattern on its surface;
[0030] A pressure sensor is used to measure the pressure at the pressure measuring hole;
[0031] The embedded atmospheric data processing system is connected to the pressure sensor and is used to process pressure data and calculate atmospheric parameters.
[0032] Preferably, in step S3, the discrete flight state needs to cover the boundary and typical state of the flight envelope, and the solution coefficient table is scalable, allowing new simulation data points to be added based on the initial table, and the overall dataset to be retriangulated to update the mesh.
[0033] Preferably, the method does not require initial values for iteration or iterative calculations when solving atmospheric parameters; the solution is completed through a single grid positioning and interpolation.
[0034] A computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the steps of the method for solving parameters of an embedded atmospheric data system based on triangulation.
[0035] An electronic device includes a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the steps of the method for calculating parameters of an embedded atmospheric data system based on triangulation. Attached Figure Description
[0036] Figure 1 This is a flowchart illustrating the parameter calculation method for embedded atmospheric data systems based on triangulation provided by the present invention. Detailed Implementation
[0037] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings. Figure 1 This is a flowchart illustrating the parameter calculation method for an embedded atmospheric data system based on triangulation provided by this invention. Figure 1 As shown, the present invention provides a method for calculating parameters of an embedded atmospheric data system, comprising:
[0038] Perform aerodynamic simulation of the aircraft within its full envelope and select a suitable layout for surface pressure measurement holes;
[0039] For the pressure testing hole layout, parameter calculation coefficients are constructed. and ;
[0040] Establish parameter solution coefficients for a series of Mach numbers, angles of attack, and sideslip angles. , , The table of numbers forms a series of numbers. and This refers to the three-dimensional data of the coordinate axes;
[0041] The Delaunay triangulation method is used to analyze scattered data points. , , The space is divided to form a three-dimensional tetrahedral mesh;
[0042] The [measurement values obtained from the pressure testing hole] , , The location of the object is determined by using the DT.pointLocation method in Matlab, which identifies the tetrahedral mesh in which it is located.
[0043] The corresponding atmospheric data parameters are calculated by interpolation.
[0044] Perform aerodynamic simulation of the aircraft across its entire envelope, and select a suitable layout for surface pressure gauge holes. The location of the pressure gauge holes should generally meet the following conditions:
[0045] 1) The aerodynamic effects of engine air intake flow, light window, nose landing gear and doors, fuel probe, and bomb bay doors on the pressure measurement port should be avoided.
[0046] 2) Pressure measurement points must be located on the top, bottom, left, and right sides of the fuselage (the pressure difference between the top and bottom is used to calculate the angle of attack, and the pressure difference between the left and right sides is used to calculate the sideslip angle).
[0047] 3) All pressure measurement points should be located on the windward side as much as possible, and the selected locations should be in regions with stable, non-separated, and vortex-free flow fields;
[0048] 4) Under the same angle of attack and sideslip angle, at least two sets of points show pressure differences that are sensitive to Mach number changes and have large gradients;
[0049] 5) Under the same angle of attack and Mach number, at least two sets of points have pressure differences that change monotonically with sensitivity to sideslip angle, and the gradient is large. These are usually points on the left and right sides.
[0050] 6) Under the same slip angle and Mach number conditions, at least two sets of points have pressure differences that change monotonically with the angle of attack, and the gradient is large. These are usually points on the upper and lower sides.
[0051] When performing CFD simulations, this algorithm uses the Mach number... Angle of attack Sideslip angle These parameters are set at specific intervals and must include various extreme cases of the flight envelope. Atmospheric parameters include... , , , There are four quantities, so at least four pressure measuring holes need to be installed.
[0052] For the pressure testing hole layout, parameter calculation coefficients are constructed. , , The solution model incorporates the following formula for pressure measurement points:
[0053] ;
[0054] In the formula For flight pressure, The pressure measurement value of the pressure test hole. The pressure coefficient of the pressure measuring hole, For static pressure, ,in Total pressure.
[0055] Based on existing engineering experience Mainly with , , This algorithm is related to the pressure value embedded in the pressure measuring orifice, and is constructed from... or The three solution coefficients are composed of variables. , , To ensure the uniqueness of the solution, the following three conditions must be met when constructing the solution coefficients:
[0056] Given any specific Mach number and sideslip angle, It changes monotonically with the angle of attack;
[0057] Given any given Mach number and angle of attack, The sideslip angle changes monotonically;
[0058] Under any given angle of attack and sideslip angle, It changes monotonically with Mach number.
[0059] By applying the above three conditions, the coefficients of each solution group are guaranteed to be [ , , With a unique set of atmospheric parameters , , ]correspond.
[0060] Establish parameter solution coefficients for a series of Mach numbers, angles of attack, and sideslip angles. , , The table of numbers forms a series of numbers. and This represents the three-dimensional data of the coordinate axes. During the CFD simulation, different Mach numbers were simulated. Angle of attack Sideslip angle Calculate the aircraft's aerodynamic characteristics under all conditions. , , This forms a table of solution coefficients.
[0061] The Delaunay triangulation method is used to analyze scattered data points ( , , The space is divided to form a three-dimensional tetrahedral mesh. Through a parametric calculation table, a mesh is formed... and The data consists of three-dimensional scattered coordinate axes. To facilitate interpolation and reduce data storage, Delaunay triangulation is used for processing. and The resulting three-dimensional scattered data forms a series of tetrahedral meshes that do not intersect but are interconnected.
[0062] For the pressure measurement value of the pressure test hole, the corresponding... , , The location is determined by using the DT.pointLocation method in Matlab to locate the tetrahedral mesh in which it is located;
[0063] After confirming the location of the point on the tetrahedral mesh, the atmospheric parameters at that point are calculated using the atmospheric parameter values at the four vertices of the tetrahedral mesh through internal interpolation, thus completing the calculation and output of the atmospheric parameters.
[0064] The above description is merely a specific embodiment of this application, but the scope of protection of this application 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 this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. A parameter calculation method for an embedded atmospheric data system based on triangulation, characterized in that, The method includes: Step S1: Perform aerodynamic simulation within the entire envelope range, and select the layout of pressure measurement holes on the aircraft surface based on the simulation results; Step S2: For the pressure measuring hole layout, construct a set of parameter calculation coefficients that are one-to-one mapped to Mach number, angle of attack, and sideslip angle. and ; Step S3: Based on the simulation results of step S1, calculate the parameter solution coefficients corresponding to multiple discrete flight states. , , This forms a solution coefficient table, which constitutes a set of coefficients. and A three-dimensional dataset with coordinate axes; Step S4: Using the Delaunay triangulation method, spatially divide the scattered data points in the three-dimensional dataset obtained in step S3 to generate a three-dimensional tetrahedral mesh covering the dataset. Step S5: Obtain the real-time pressure measurement value from the pressure testing orifice, and calculate the real-time solution coefficients according to the construction method in step S2. , , ]; Step S6: Use the real-time solution coefficients obtained in step S5 as query points, locate them in the tetrahedral mesh generated in step S4, and determine the specific tetrahedron to which they belong. Step S7: Based on the known Mach number, angle of attack, and sideslip angle at each vertex of the specific tetrahedron, the atmospheric data parameters corresponding to the real-time measurement values are calculated by interpolation.
2. The parameter calculation method for an embedded atmospheric data system based on triangulation according to claim 1, characterized in that, In step S1, the selected pressure testing hole layout satisfies the following conditions: Pressure measuring points are arranged on the top, bottom, left, and right sides of the fuselage; All pressure measurement points are located in the stable flow field region; There are at least two sets of pressure measurement points, and the pressure difference between them is sensitive to changes in Mach number; There are at least two sets of pressure measurement points whose pressure difference is sensitive and monotonic to changes in angle of attack. There are at least two sets of pressure measurement points, whose pressure difference is sensitive to and monotonic with changes in the sideslip angle.
3. The parameter calculation method for an embedded atmospheric data system based on triangulation according to claim 1, characterized in that, In step S2, the parameter solution coefficients and Pressure coefficient of each pressure measuring hole or pressure It is constructed by combination and satisfies the monotonicity condition: As the angle of attack changes monotonically, As the sideslip angle changes monotonically, It changes monotonically with Mach number.
4. The parameter calculation method for an embedded atmospheric data system based on triangulation according to claim 1, characterized in that, In step S4, the tetrahedral mesh generated by the Delaunay triangulation method does not contain other data points from the three-dimensional dataset inside the circumscribed sphere of any tetrahedron.
5. The parameter calculation method for an embedded atmospheric data system based on triangulation according to claim 1, characterized in that, In step S6, the location is determined by calculating the spatial relationship between the query point and each tetrahedron. Specifically, this is achieved by calling the pointLocation function in Matlab, which provides the tetrahedron to which the query point belongs and the corresponding centroid coordinates.
6. The method for calculating parameters of an embedded atmospheric data system based on triangulation according to claim 1, characterized in that, In step S7, the interpolation calculation uses barycentric coordinates for linear interpolation.
7. An embedded atmospheric data processing system implementing the method according to any one of claims 1-6, characterized in that, include: The preprocessing module stores the parameterized coefficients pre-established through aerodynamic simulation and triangulation. , , The indexed tetrahedral mesh data and vertex atmospheric parameters; The data acquisition module is used to acquire pressure measurement values from multiple surface pressure testing holes in real time. The coefficient calculation module is used to calculate the real-time solution coefficients according to the pressure measurement values and predetermined rules. , , ; The grid positioning module is used to take the real-time solution coefficients as input and quickly locate the tetrahedron in the tetrahedral grid data. The parameter calculation module is used to interpolate based on the located tetrahedral vertex data and output the real-time Mach number, angle of attack, and sideslip angle.
8. An aircraft, characterized in that, include: The fuselage has a plurality of pressure measuring holes arranged on its surface according to the layout described in claim 2; A pressure sensor is used to measure the pressure at the pressure measuring hole; The embedded atmospheric data processing system as described in claim 7 is connected to the pressure sensor and is used to process pressure data and calculate atmospheric parameters.
9. The method for calculating parameters of an embedded atmospheric data system based on triangulation according to claim 1, characterized in that, In step S3, the discrete flight state needs to cover the boundary and typical state of the flight envelope. The solution coefficient table is scalable, allowing new simulation data points to be added based on the initial table, and the overall dataset is retriangulated to update the mesh.
10. The method for calculating parameters of an embedded atmospheric data system based on triangulation according to claim 1, characterized in that, The method described above does not require initial values for iteration or iterative calculations when solving atmospheric parameters; the solution is completed through a single grid positioning and interpolation.
11. A computer-readable storage medium having a computer program stored thereon, characterized in that, When executed by a processor, the program implements the steps of the method for calculating parameters of an embedded atmospheric data system based on triangulation as described in any one of claims 1-6 and 9-10.
12. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the program, it implements the steps of the embedded atmospheric data system parameter calculation method based on triangulation as described in any one of claims 1-6 and 9-10.