CN114330154A - Aircraft aerodynamic data distribution system and method - Google Patents
Aircraft aerodynamic data distribution system and method Download PDFInfo
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- CN114330154A CN114330154A CN202111444558.5A CN202111444558A CN114330154A CN 114330154 A CN114330154 A CN 114330154A CN 202111444558 A CN202111444558 A CN 202111444558A CN 114330154 A CN114330154 A CN 114330154A
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Abstract
The invention provides an aircraft pneumatic data publishing system and method, which comprises the following modules: pneumatic mathematical model resolving module: carrying out dimensionality reduction and interpolation on pneumatic original data; a source data management module: driving, organizing and converting the pneumatic original data to generate a customized data structure and a data interpolation boundary; a data response module: and performing border crossing check of the input customized data structure by using the data interpolation border, resolving by using a pneumatic mathematical model resolving module, and returning a generated result to a user. The system provided by the invention has the advantages of simple use, wide application range and good robustness.
Description
Technical Field
The invention relates to an aircraft pneumatic data processing method, in particular to an aircraft pneumatic data publishing system and method.
Background
Aircraft aerodynamic data is data describing the aerodynamic characteristics of an aircraft for use by the relevant profession in aircraft design and manufacture. In general, pneumatic data is composed of several discrete data source points and corresponding pneumatic mathematical models. Continuous pneumatic data can be obtained through fitting and interpolation of the pneumatic mathematical model for use by relevant downstream professionals.
The traditional method for using the matched data is as follows: when each profession of aircraft design uses pneumatic data, the profession must first understand and master the principle of the pneumatic mathematical model, program a computer program corresponding to the model, copy a data source point into the program, and operate the program to obtain the pneumatic data. The traditional method faces a plurality of problems, such as model understanding difference, programming difficulty, data access boundary border crossing, multi-version data confusion, source data copying error and the like, so that the data use efficiency is low, and the error rate is high.
In chinese patent publication No. CN109871643A, a method and an apparatus for processing flight aerodynamic data are disclosed, the method applied to a higher-level terminal, including: receiving a data packet sent by a flight pneumatic data acquisition system; decoding the encoded data in the data packet to obtain decoded data; wherein the decoded data corresponds to the encoded data; converting the decoded data into a second voltage signal; converting the second voltage signal into a physical quantity corresponding to the first voltage signal; wherein the physical quantity comprises a temperature value and a pressure value; and outputting the physical quantity. However, this patent document fails to address the inefficiency of downstream professionals in using pneumatic data.
Disclosure of Invention
In view of the deficiencies in the prior art, it is an object of the present invention to provide an aircraft aerodynamic data distribution system and method.
The invention provides an aircraft aerodynamic data distribution system, which comprises the following modules:
pneumatic mathematical model resolving module: carrying out dimensionality reduction and interpolation on pneumatic original data;
a source data management module: driving, organizing and converting the pneumatic original data to generate a customized data structure and a data interpolation boundary;
a data response module: and performing border crossing check of the input customized data structure by using the data interpolation border, resolving by using a pneumatic mathematical model resolving module, and returning a generated result to a user.
Preferably, the aerodynamic mathematical model calculation module uses an aerodynamic mathematical model based on radix expansion, and the aerodynamic mathematical model calculation module respectively 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 Mach number MaAngle of air flow roll
Attack angle alpha and pitching rudder deflection angle deltaAYaw rudder deflection angle deltaBAnd rolling rudder deflection angle deltaRA、δRBAs a function of (c).
Preferably, the pneumatic raw data is composed of a plurality of two-dimensional data tables DT and an index file IT.
Preferably, the transverse parameter of the two-dimensional data table DT is Mach number MaThe longitudinal parameter of the two-dimensional data table DT is the attack angle alpha, and the index file IT is organized and managed through the file name and the corresponding state of the two-dimensional data table DT.
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 directly called by being embedded in the application program.
The invention provides an aircraft aerodynamic data publishing method, which comprises the following steps:
a pneumatic mathematical model resolving step: carrying out dimensionality reduction and interpolation on pneumatic original data;
a source data management step: driving, organizing and converting the pneumatic original data to generate a customized data structure and a data interpolation boundary;
a data response step: and performing border crossing check of the input customized data structure by using the data interpolation border, resolving by using a pneumatic mathematical model resolving step, and returning a generated result to a user.
Preferably, the aerodynamic mathematical model based on radix expansion is used in the aerodynamic mathematical model calculation step, and 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 are respectively expressed as Mach number M in the aerodynamic mathematical model calculation stepaAngle of air flow roll
Attack angle alpha and pitching rudder deflection angle deltaAYaw rudder deflection angle deltaBAnd rolling rudder deflection angle deltaRA、δRBAs a function of (c).
Preferably, the pneumatic raw data is composed of a plurality of two-dimensional data tables DT and an index file IT.
Preferably, the transverse parameter of the two-dimensional data table DT is Mach number MaThe longitudinal parameter of the two-dimensional data table DT is the attack angle alpha, and the index file IT is organized and managed through the file name and the corresponding state of the two-dimensional data table DT.
Preferably, the data response step includes operating with a dynamic library and a corresponding header file, and the dynamic library and the corresponding header file can be directly called by being embedded in an application program.
Compared with the prior art, the invention has the following beneficial effects:
1. the aircraft pneumatic data issuing system provided by the invention is simple to operate, so that a downstream user can use pneumatic data more simply, and the use convenience and accuracy of the pneumatic data are improved;
2. the aircraft pneumatic data issuing system provided by the invention has the advantage of wide application range, and can be flexibly used according to the requirements of downstream users;
3. the aircraft pneumatic data release system provided by the invention has the advantage of high robustness.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a block diagram of an aircraft aerodynamic data distribution system according to an embodiment of the present invention;
FIG. 2 is a flow chart of an aircraft aerodynamic data distribution system according to an embodiment of the present invention;
fig. 3 is a schematic diagram of the two-dimensional data table DT and the index file table IT according to the embodiment of the present invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The aircraft pneumatic data issuing system provided by the embodiment comprises a pneumatic mathematical model resolving module, a source data management module and a data answering module, and the structural block diagram of the system is shown in fig. 1.
Pneumatic mathematical model resolving module: and performing dimensionality reduction and interpolation on the pneumatic raw data. The method for calculating the pneumatic mathematical model embedded in the system has wide applicability and can be directly used. If the user has a special model calculation method, the default of the replacement system can be loaded in a mode of generating a dynamic library.
The aerodynamic mathematical model calculation module uses an aerodynamic mathematical model based on radix expansion, and expresses normal force N, lateral force Z, axial force A, pitching moment MZ, yawing moment MY and rolling moment MX borne by the aircraft as Mach number MaAngle of air flow roll
Attack angle alpha and pitching rudder deflection angle deltaAYaw rudder deflection angle deltaBAnd rolling rudder deflection angle deltaRAAnd deltaRBA function of, i.e.
Ck() C denotes dimensionless coefficients for normal force N, lateral force Z, axial force a, pitching moment MZ, yawing moment MY and rolling moment MX, subscript k denotes the class, k e (N, Z, MZ, MY, a, MX);
h represents height;
δTrepresenting pitch rudder deflection angle deltaAYaw rudder deflection angle deltaB，T∈(δA，δB)；
expressed in rudder deflection angle delta A0 or deltaBWhen equal to 0, the rudder deflection angle deltaRAAnd deltaRBPost-deflection pair Ck() The contribution of (1);
sigmaTOr deltaTRFor C at second or higher derivativek() The contribution of (1);
formula (1) shows that six-component aerodynamic data (normal force, axial force, lateral force and corresponding moment) can completely describe the aerodynamic characteristics of the aircraft. Generally, the data relates to at least 5 dimensional data, and more 8-10 dimensional data is processed. Therefore, it is difficult for non-pneumatic professionals to understand and master the mathematical model. The invention uses software technology to write the model into module embedded or dynamic loading processing data.
A source data management module: the pneumatic raw data is driven, organized, transformed and generates custom data structures and data interpolation boundaries, as shown in fig. 2.
The source data management module is used for reading, organizing and converting data source points in pneumatic original data. The source data is composed of a plurality of two-dimensional data tables DT and an index file IT. In general, the transverse parameter of the two-dimensional data table DT is Mach number MaThe longitudinal parameter of the two-dimensional data table DT is the angle of attack α, and the index file IT is organized and managed by the file name of the two-dimensional data table DT and the corresponding state, as shown in fig. 3. The management module analyzes the relationship between the data tables of the two-dimensional data tables DT by reading the index file IT, and performs dimension reduction processing on the plurality of two-dimensional data tables DT in a formula (1) mode.
The invention designs a processing mode of reading source data based on script and reducing dimension by using an improved binary tree data structure, and realizes variable pneumatic source data processing dimension (more than 5 dimensions). Meanwhile, a pneumatic data use boundary is generated according to the source data characteristics, so that the data response module can generate input constraint conditions conveniently.
A data response module: and performing border crossing check of the input customized data structure by using the data interpolation border, resolving by using a pneumatic mathematical model resolving module, and returning a generated result to a user.
The data response module receives the state input and outputs the pneumatic data of the corresponding state, and the interface comprises:
1) normal force N and pitching moment MZ;
2) lateral force Z and yaw moment MY;
3) an axial force A;
4) a rolling moment MX;
5) other projectile pneumatics related data.
The interface state input parameters include: ma,α,
δA,δB,δRA,δRBH, etc
The data response module performs border crossing check on input data according to the data use border generated by the source data management module, the data cross check is performed through a pneumatic mathematical model calculation module which is then sent to a dynamic loading device for calculation, the pneumatic mathematical model calculation module calls the source data management module to acquire all required source data according to a calculation rule for dimension reduction interpolation processing, and the data response module returns the generated result to a user.
In practical 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 a user can be directly embedded into the user's own application program to directly use the data response module interface.
The data response module receives a data request of a user through an interface embedded with a user program, performs data interpolation and fitting processing on a customized data structure through a pneumatic mathematical model resolving module after data cross-border and legality checking, and finally generates a result to return to the user. The whole flow diagram is shown in figure 2.
In the process, a user can obtain required pneumatic data only by calling an interface provided by the data response module without concerning the data processing process, and the whole process is quick, easy to use and efficient.
Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, units provided by the present invention as pure computer readable program code, the system and its various devices, modules, units provided by the present invention can be fully implemented by logically programming method steps in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system and various devices, modules and units thereof provided by the invention can be regarded as a hardware component, and the devices, modules and units included in the system for realizing various functions can also be regarded as structures in the hardware component; means, modules, units for performing the various functions may also be regarded as structures within both software modules and hardware components for performing the method.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. An aircraft aerodynamic data distribution system, comprising the following modules:
pneumatic mathematical model resolving module: carrying out dimensionality reduction and interpolation on pneumatic original data;
a source data management module: driving, organizing and converting the pneumatic original data to generate a customized data structure and a data interpolation boundary;
a data response module: and performing border crossing check of the input customized data structure by using the data interpolation border, resolving by using a pneumatic mathematical model resolving module, and returning a generated result to a user.
2. The aircraft aerodynamic data distribution system of claim 1, wherein: the aerodynamic mathematical model calculation module uses an aerodynamic mathematical model based on radix expansion, and respectively 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 Mach number MaAngle of air flow roll
Attack angle alpha and pitching rudder deflection angle deltaAYaw rudder deflection angle deltaBAnd rolling rudder deflection angle deltaRA、δRBAs a function of (c).
3. The aircraft aerodynamic data distribution system of claim 1, wherein: the pneumatic original data is composed of a plurality of two-dimensional data tables DT and an index file IT.
4. The aircraft aerodynamic data distribution system of claim 3, wherein: the transverse parameter of the two-dimensional data table DT is Mach number MaThe longitudinal parameter of the two-dimensional data table DT is an attack angle alpha, index textThe piece IT is organized and managed by the file name and the corresponding state of the two-dimensional data table DT.
5. The aircraft aerodynamic data distribution 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 into an application program to be directly called.
6. An aircraft aerodynamic data distribution method, characterized by comprising the steps of:
a pneumatic mathematical model resolving step: carrying out dimensionality reduction and interpolation on pneumatic original data;
a source data management step: driving, organizing and converting the pneumatic original data to generate a customized data structure and a data interpolation boundary;
a data response step: and performing border crossing check of the input customized data structure by using the data interpolation border, resolving by using a pneumatic mathematical model resolving step, and returning a generated result to a user.
7. The aircraft aerodynamic data distribution method of claim 6, wherein: the method comprises the following steps that a pneumatic mathematical model based on radix expansion is used in the pneumatic mathematical model calculating step, and 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 are respectively expressed into Mach number M in the pneumatic mathematical model calculating stepaAngle of air flow roll
Attack angle alpha and pitching rudder deflection angle deltaAYaw rudder deflection angle deltaBAnd rolling rudder deflection angle deltaRA、δRBAs a function of (c).
8. The aircraft aerodynamic data distribution method of claim 6, wherein: the pneumatic original data is composed of a plurality of two-dimensional data tables DT and an index file IT.
9. The aircraft aerodynamic data distribution method of claim 8, wherein: the transverse parameter of the two-dimensional data table DT is Mach number MaThe longitudinal parameter of the two-dimensional data table DT is the attack angle alpha, and the index file IT is organized and managed through the file name and the corresponding state of the two-dimensional data table DT.
10. The aircraft aerodynamic data distribution method of claim 6, wherein: the data response step comprises the operation of a dynamic library and a corresponding header file, and the dynamic library and the corresponding header file can be embedded into an application program to be directly called.
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| CN115017842A (en) * | 2022-08-09 | 2022-09-06 | 北京星途探索科技有限公司 | Pneumatic data interpolation method and device, electronic equipment and storage medium |
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| CN115017842A (en) * | 2022-08-09 | 2022-09-06 | 北京星途探索科技有限公司 | Pneumatic data interpolation method and device, electronic equipment and storage medium |
| CN115017842B (en) * | 2022-08-09 | 2022-12-02 | 北京星途探索科技有限公司 | Pneumatic data interpolation method and device, electronic equipment and storage medium |
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