Aircraft aerodynamic data publishing system and method

Abstract

The application provides an aircraft aerodynamic data publishing system and method, comprising the following modules: an aerodynamic mathematical model solving module: performing dimension reduction and interpolation on aerodynamic original data; a source data management module: performing driving, organization, conversion on the aerodynamic original data, and generating a customized data structure and data interpolation boundary; a data response module: performing out-of-bound checking on an input customized data structure using the data interpolation boundary, performing solving through the aerodynamic mathematical model solving module, and returning the result to a user. The system provided by the application has the advantages of simple use, wide application range and good robustness.

Description

TECHNICAL FIELD

[0001] The present application relates to an aircraft aerodynamic data processing method, in particular to an aircraft aerodynamic data publishing system and method. BACKGROUND

[0002] Aircraft aerodynamic data is data describing the aerodynamic characteristics of an aircraft, which is used by related professionals in aircraft design and manufacturing. Generally, aerodynamic data is composed of a number of discrete data sources and corresponding aerodynamic mathematical models. Through fitting and interpolation of the aerodynamic mathematical models, continuous aerodynamic data can be obtained for use by related downstream professionals.

[0003] The traditional method of using matching data is that each professional in aircraft design must first understand and master the principles of aerodynamic mathematical models, develop computer programs corresponding to the models, copy data sources into the programs, and run the programs to obtain aerodynamic data when using aerodynamic data. The traditional method of use faces many problems, such as differences in model understanding, difficulties in program development, data access boundary overflow, multiple version data confusion, source data copying errors, etc., resulting in low data use efficiency and high error rate.

[0004] In Chinese patent document CN109871643A, a flight aerodynamic data processing method and device are disclosed. The method is applied to an upper terminal and includes receiving a data packet sent by a flight aerodynamic data acquisition system, decoding encoded data in the data packet to obtain decoded data, converting the decoded data into a second voltage signal, converting the second voltage signal into a physical quantity corresponding to a first voltage signal, and outputting the physical quantity. However, the patent document fails to solve the problem of low efficiency of downstream professionals using aerodynamic data. SUMMARY

[0005] In view of the defects in the prior art, the purpose of the present application is to provide an aircraft aerodynamic data publishing system and method.

[0006] According to the aircraft aerodynamic data publishing system provided by the present application, the following modules are included:

[0007] The aerodynamic mathematical model solving module reduces the dimensionality and interpolates the aerodynamic raw data;

[0008] The source data management module drives, organizes, converts and generates a customized data structure and data interpolation boundary for the aerodynamic raw data;

[0009] The data response module uses the data interpolation boundary to perform an out-of-bound check on the input customized data structure, solves it through the aerodynamic mathematical model solving module, and returns the result to the user.

[0010] Preferably, the aerodynamic mathematical model solving module uses an aerodynamic mathematical model based on cardinal expansion, and the aerodynamic mathematical model solving module represents the normal force N, the lateral force Z, the axial force A, the pitching moment MZ, the yawing moment MY and the rolling moment MX borne by the aircraft as functions of the Mach number M a , the airflow rolling angle , the attack angle a, the elevator deflection angle d A , the rudder deflection angle d B and the aileron deflection angle d RA , d RB .

[0011] Preferably, the aerodynamic raw data is composed of a plurality of two-dimensional data tables DT and an index file IT.

[0012] Preferably, the lateral parameter of the two-dimensional data table DT is the Mach number M a , and the longitudinal parameter of the two-dimensional data table DT is the attack angle a, and the index file IT organizes and manages the two-dimensional data table DT through the file name and the corresponding state.

[0013] Preferably, the data response module includes a dynamic library and a corresponding header file, and the dynamic library and the corresponding header file can be embedded in an application program for direct calling.

[0014] According to the aerodynamic data publishing method of the present application, the method comprises the following steps:

[0015] The aerodynamic mathematical model solving step: reducing the dimension and interpolating the aerodynamic raw data;

[0016] The source data management step: driving, organizing, converting the aerodynamic raw data and generating a customized data structure and a data interpolation boundary;

[0017] The data response step: using the data interpolation boundary to perform an out-of-bound checking on the input customized data structure, performing a calculation through the aerodynamic mathematical model solving step, and returning the result to the user.

[0018] Preferably, the aerodynamic mathematical model solving step uses an aerodynamic mathematical model based on cardinal expansion, and the aerodynamic mathematical model solving step represents the normal force N, the lateral force Z, the axial force A, the pitching moment MZ, the yawing moment MY and the rolling moment MX borne by the aircraft as functions of the Mach number M a , the airflow rolling angle , the attack angle a, the elevator deflection angle d A , the rudder deflection angle d B and the aileron deflection angle d RA , d RB .

[0019] Preferably, the aerodynamic raw data is composed of a plurality of two-dimensional data tables DT and an index file IT.

[0020] Preferably, the transverse parameter of the two-dimensional data table DT is Mach number M a , the longitudinal parameter of the two-dimensional data table DT is attack angle a, and the index file IT is organized and managed by the file name of the two-dimensional data table DT and the corresponding state.

[0021] Preferably, the data response step includes operating by using a dynamic library and a corresponding header file, which can be embedded in an application program for direct calling.

[0022] Compared with the prior art, the present application has the following beneficial effects:

[0023] 1. The aircraft aerodynamic data publishing system provided by the present application is simple to operate, making it easier for downstream users to use aerodynamic data and improving the convenience and accuracy of aerodynamic data use;

[0024] 2. The aircraft aerodynamic data publishing system provided by the present application has the advantage of wide application range and can be flexibly used according to the needs of downstream users;

[0025] 3. The aircraft aerodynamic data publishing system provided by the present application has the advantage of high robustness. BRIEF DESCRIPTION OF DRAWINGS

[0026] Other features, objects and advantages of the present application will become more apparent from the following detailed description of non-limiting embodiments, made with reference to the accompanying drawings:

[0027] Figure 1 is a structural block diagram of the aircraft aerodynamic data publishing system of the embodiment of the present application;

[0028] Figure 2 is a flowchart of the aircraft aerodynamic data publishing system of the embodiment of the present application;

[0029] Figure 3 is a schematic diagram of the two-dimensional data table DT and the index file table IT in the embodiment of the present application. DETAILED DESCRIPTION

[0030] The present application will be described in detail below with reference to specific embodiments. The following embodiments will help those skilled in the art to further understand the present application, but do not limit the present application in any form. It should be noted that, for those skilled in the art, without departing from the concept of the present application, a number of changes and improvements can be made. These all belong to the protection scope of the present application.

[0031] The aircraft aerodynamic data publishing system provided by the embodiment comprises an aerodynamic mathematical model solving module, a source data management module and a data response module, and a system structure block diagram is as shown in the figure Figure 1 .

[0032] The aerodynamic mathematical model solving module: dimension reduction and interpolation are performed on the aerodynamic original data. The aerodynamic mathematical model solving method embedded in the system of the present application has wide applicability and can be directly used. If the user has a special model solving method, the system default can be replaced by loading and replacing in the form of a dynamic library.

[0033] The aerodynamic mathematical model solving module uses an aerodynamic mathematical model based on base expansion, and the aerodynamic mathematical model solving module expresses the normal force N, the lateral force Z, the axial force A, the pitching moment MZ, the yawing moment MY and the rolling moment MX borne by the aircraft as a function of the Mach number M a , the airflow roll angle , the attack angle α, the elevator deflection angle δ A , the rudder deflection angle δ B and the aileron deflection angle δ RA and δ RB , that is

[0034]

[0035] C k () of the C represents the dimensionless coefficient of the normal force N, the lateral force Z, the axial force A, the pitching moment MZ, the yawing moment MY and the rolling moment MX with respect to the Mach number M

[0036] H represents the height;

[0037] δ T represents the elevator deflection angle δ A , the rudder deflection angle δ B , and T ∈ (δ A , δ B );

[0038] represents the contribution of δ A or δ B to C k () after the deflection when the aileron deflection angle δ R = 0;

[0039] represents the contribution of δ RA and δ RB to C k () after the deflection when the elevator deflection angle δ A = 0 or the rudder deflection angle δ B = 0;

[0040] ∑(...) represents delta T or delta TR C k 's contribution under second or higher order derivative;

[0041] Equation (1) represents six components of aerodynamic data (normal force, axial force, lateral force and corresponding moments) to fully describe the aerodynamic characteristics of an aircraft. Generally, the above data involves at least 5-dimensional data, and more than 8-10 dimensional data processing. Therefore, it is difficult for non-aerodynamic professionals to understand and master the above mathematical model. The present application uses software technology to write the above model into a module for embedded or dynamic loading processing data.

[0042] Source data management module: driving, organizing, converting and generating custom data structure and data interpolation boundary for aerodynamic raw data, as shown in Figure 2 .

[0043] The source data management module realizes reading, organizing and converting of data source points in the aerodynamic raw data. The source data is composed of multiple two-dimensional data tables DT and an index file IT. Generally, the horizontal parameter of the two-dimensional data table DT is Mach number M a , and the vertical parameter of the two-dimensional data table DT is angle of attack α, and the index file IT is organized and managed by the two-dimensional data table DT file name and the corresponding state, as shown in Figure 3 . The management module parses the relationship between the two-dimensional data tables DT by reading the index file IT, and processes multiple two-dimensional data tables DT according to equation (1) to reduce the dimension.

[0044] The present application designs a script-based source data reading and an improved binary tree data structure for dimension reduction processing, which realizes variable dimension (more than 5 dimensions) of aerodynamic source data processing. At the same time, according to the characteristics of the source data, the aerodynamic data use boundary is generated to facilitate the data response module to generate input constraints.

[0045] Data response module: using data interpolation boundary to perform out-of-boundary check of input custom data structure, solving through aerodynamic mathematical model solving module, and returning the result to the user.

[0046] The data response module accepts state input and outputs aerodynamic data of the corresponding state, and the interface includes:

[0047] 1) normal force N and pitch moment MZ;

[0048] 2) lateral force Z and yaw moment MY;

[0049] 3) axial force A;

[0050] 4) roll moment MX;

[0051] 5) Other aerodynamic related data.

[0052] Interface state input parameters include: M a , alpha, delta A , delta B , delta RA , delta RB , H, etc.

[0053] The data response module performs out-of-bound checking on the input data according to the data use boundary generated by the source data management module, and after passing, it is solved by the dynamically loaded aerodynamic mathematical model solving module. The aerodynamic mathematical model solving module acquires all the required source data according to the solving rules to perform dimension reduction interpolation processing, and returns the result to the user after the data response module.

[0054] In actual application, the data response module can be a dynamic library (.dll file / windows or.so file / linux) and a corresponding header file (cpp, hpp), and the user can directly embed it into the user's own application to directly use the data response module interface.

[0055] After receiving the user's data request through the interface of the embedded user program, the data response module performs data interpolation and fitting processing on the customized data structure through the aerodynamic mathematical model solving module after data out-of-bound and legality checking, and finally generates the result and returns it to the user. The whole process is shown in Figure 2 .

[0056] In this process, the user only needs to use the interface provided by the data response module to obtain the required aerodynamic data, without worrying about the data processing process, and the whole process is fast, easy to use and efficient.

[0057] Those skilled in the art know that in addition to implementing the system provided by the present application and each device, module, unit thereof in a pure computer readable program code manner, the same function can also be realized by logically programming the method steps in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers and embedded microcontrollers. Therefore, the system provided by the present application and each device, module, unit thereof can be considered as a hardware component, and the devices, modules, units included therein for realizing various functions can also be considered as structures within the hardware component; the devices, modules, units for realizing various functions can also be considered as both software modules realizing methods and structures within the hardware component.

[0058] The specific embodiments of the present application are described above. It needs to be understood that the present application is not limited to the specific embodiments described above, and various changes or modifications can be made by those skilled in the art within the scope of the claims, which does not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be combined with each other at will without conflict.

Claims

1. An aircraft aerodynamic data publishing system, characterized by, The application comprises the following modules: a module for solving aerodynamic mathematical model: reducing dimension and interpolating aerodynamic original data; a module for managing source data: reading, organizing, converting and generating customized data structure and data interpolation boundary of data source points in aerodynamic original data; the source data is composed of multiple two-dimensional data tables DT and an index file IT; the horizontal parameter of the two-dimensional data table DT is Mach number, the vertical parameter of the two-dimensional data table DT is angle of attack, and the index file IT is organized and managed by the file name of the two-dimensional data table DT and the corresponding state; a data response module: using the data interpolation boundary to check the out-of-boundary of the input customized data structure, solving by embedding the module for solving aerodynamic mathematical model, and returning the result to the user; the data response module has an interface for embedding user program, and the user can obtain the required aerodynamic data by calling the interface provided by the data response module.

2. The aircraft aerodynamic data publishing system of claim 1, wherein: The module for solving aerodynamic mathematical model uses a base expansion-based aerodynamic mathematical model, and the module for solving aerodynamic mathematical model expresses the normal force, lateral force, axial force, pitch moment, yaw moment and roll moment of the aircraft as functions of Mach number, airflow roll angle, angle of attack, pitch rudder deflection angle, yaw rudder deflection angle and roll rudder deflection angle respectively.

3. The aircraft aerodynamic data publishing system of Claim 1, wherein: The data response module comprises a dynamic library and a corresponding header file, and the dynamic library and the corresponding header file can be embedded in an application program for direct calling.

4. An aircraft aerodynamic data publishing method, characterized in that, The application comprises the following steps: a step for solving aerodynamic mathematical model: reducing dimension and interpolating aerodynamic original data; a step for managing source data: reading, organizing, converting and generating customized data structure and data interpolation boundary of data source points in aerodynamic original data; the source data is composed of multiple two-dimensional data tables DT and an index file IT; the horizontal parameter of the two-dimensional data table DT is Mach number, the vertical parameter of the two-dimensional data table DT is angle of attack, and the index file IT is organized and managed by the file name of the two-dimensional data table DT and the corresponding state; a step for responding data: using the data interpolation boundary to check the out-of-boundary of the input customized data structure, solving by embedding the step for solving aerodynamic mathematical model, and returning the result to the user; the step for responding data has an interface for embedding user program, and the user can obtain the required aerodynamic data by calling the interface provided by the step for responding data.

5. The aircraft aerodynamic data publication method of claim 4, wherein: The step for solving aerodynamic mathematical model uses a base expansion-based aerodynamic mathematical model, and the step for solving aerodynamic mathematical model expresses the normal force, lateral force, axial force, pitch moment, yaw moment and roll moment of the aircraft as functions of Mach number, airflow roll angle, angle of attack, pitch rudder deflection angle, yaw rudder deflection angle and roll rudder deflection angle respectively.

6. The aircraft aerodynamic data publication method of claim 4, wherein: The step for responding data comprises using a dynamic library and a corresponding header file, and the dynamic library and the corresponding header file can be embedded in an application program for direct calling.

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