Multi-machine pneumatic compatibility rapid analysis method and system

Abstract

The invention belongs to the field of aviation aerodynamic force analysis, and particularly relates to a multi-aircraft aerodynamic compatibility rapid analysis method and system.The method comprises the steps that a numerical simulation mode is adopted, aerodynamic force data of a wake flow field of an oiling machine is obtained firstly, and then aerodynamic force data sets of an oil receiver aircraft in different flight attitudes are obtained through calculation simulation; determining an aerodynamic information statistical area of the oil receiver in the wake flow field of the oiling machine according to the flight path of the oil receiver in the oil receiving process, converting aerodynamic information into attitude data of the oil receiver through a statistical means, and obtaining aerodynamic force change data of the oil receiver in the wake flow field of the oiling machine through interpolation calculation; different machine types can be respectively analyzed to obtain multi-machine aerodynamic force deformation data, so that multi-machine aerodynamic compatibility rapid evaluation is completed. Multi-machine appearance mathematical models do not need to be provided at the same time, simulation analysis can be carried out on an oiling machine and an oil receiving machine, and multi-machine pneumatic compatibility rapid evaluation can be completed; the calculation efficiency is high, the calculation cost is low and calculation is accurate.

Description

Technical Field

[0001] The present application belongs to the field of aviation aerodynamic analysis, and in particular relates to a method and system for rapid analysis of multi-aircraft aerodynamic compatibility. Background Art

[0002] When multiple aircraft fly close together, such as in-flight refueling and formation flying, the wake flow field of the leading aircraft will have a certain aerodynamic interference on the following aircraft, which will affect the flight performance of the following aircraft and bring difficulties to the pilot in maneuvering the aircraft. For example, in special cases such as the following aircraft entering the core area of ​​the wing tip vortex of the leading aircraft, it may even endanger the flight safety of the following aircraft. Therefore, before executing such tasks, a large amount of simulation analysis is required to demonstrate the feasibility of the scheme and formulate a safe and reliable flight mission execution procedure. The commonly used numerical analysis method is to place the multi-machine calculation model in the calculation domain at the same time for grid division, and then perform calculation analysis at the same time. The disadvantages of this method are: 1) It is necessary to have multiple aircraft shape digital models at the same time, but in most cases, the aerodynamic shape of the leading and trailing aircraft is highly confidential and the intellectual property rights belong to different units, making it difficult to carry out simultaneous simulation analysis of multiple aircraft; 2) Simultaneous simulation analysis of multiple aircraft increases the difficulty of grid division, the difficulty of calculation analysis process, and the cost of calculation resources and time. Therefore, forming a fast aerodynamic compatibility evaluation method that can be completed by multi-aircraft distribution has become a technical problem to be solved in this field. Summary of the invention

[0003] The purpose of this application is to provide a multi-machine pneumatic compatibility rapid analysis method and system to solve the problem that the existing pneumatic compatibility evaluation method technology is inconvenient and difficult to simulate.

[0004] The technical solution of the present application is: a multi-machine aerodynamic compatibility rapid analysis method, including: selecting a type of tanker and a receiving aircraft to be analyzed, obtaining the size of the receiving aircraft and the calculation model of the tanker, dividing the tanker wake flow field calculation analysis grid, performing simulation analysis on the tanker flow field according to the tanker wake flow field calculation analysis grid, and obtaining the aerodynamic data of the tanker wake flow field;

[0005] Obtain the calculation model of the receiving aircraft, divide the aerodynamic calculation and analysis grid according to the calculation model of the receiving aircraft, and obtain the aerodynamic data of the receiving aircraft under different flight attitudes through numerical calculation methods;

[0006] Obtain the flight path of the receiving aircraft during the refueling process and select typical location points in the flight path;

[0007] According to the size of the receiving aircraft and the information of typical position points, the size and position of the statistical area of ​​the aerodynamic information of the wake field of the receiving aircraft are determined, and the aerodynamic characteristics of the statistical area of ​​the aerodynamic information of the wake field of the receiving aircraft are converted into the attitude data of the receiving aircraft through the data statistical method;

[0008] Based on the receiving aircraft attitude data and receiving aircraft aerodynamic data set obtained from the aerodynamic information statistical area of ​​the receiving aircraft wake field, the aerodynamic change data of the receiving aircraft in the tanker wake field are obtained; then other aircraft models are selected and analyzed in turn until the multi-aircraft aerodynamic compatibility assessment is completed.

[0009] Preferably, when dividing the grid for calculation and analysis of the wake field of the refueling machine, the grid size at the typical position point of the refueling machine is determined according to the size of the receiving machine, and the calculation and analysis grid is constructed.

[0010] Preferably, the data calculation method adopts the finite element method.

[0011] Preferably, the specific method for converting aerodynamic characteristics into attitude data of the receiving aircraft is as follows: a) the statistical area of ​​aerodynamic information of the wake field is selected with reference to the characteristic length of the receiving aircraft; b) the statistical area of ​​aerodynamic information of the wake field is selected with reference to the symmetry plane of the receiving aircraft, and statistics are performed on the left and right sides respectively; c) the flow field information is converted into attitude data of the receiving aircraft by using a statistical method.

[0012] Preferably, the characteristic length includes the span of the receiving aircraft, the fuselage length and the aircraft height.

[0013] Preferably, an interpolation method is used to compare and analyze the attitude data of the receiving aircraft, the aerodynamic data set of the receiving aircraft and the aerodynamic data of the wake field of the refueling aircraft to obtain the aerodynamic change data of the receiving aircraft in the wake field of the refueling aircraft.

[0014] As a specific implementation, a multi-machine aerodynamic compatibility rapid analysis system includes a tanker aerodynamic analysis module, a receiving machine aerodynamic data acquisition module, a wake field aerodynamic information statistical area analysis module, and a receiving machine aerodynamic change analysis module;

[0015] The tanker aerodynamic analysis module can select one of the aircraft models to be analyzed, obtain the tanker calculation model, divide the tanker wake field calculation analysis grid, analyze the tanker aerodynamic information based on the tanker wake field calculation analysis grid, and obtain the tanker wake field aerodynamic data;

[0016] The aerodynamic data acquisition module of the receiving aircraft can obtain the calculation model of the receiving aircraft, divide the aerodynamic calculation and analysis grid according to the calculation model of the receiving aircraft, and obtain the aerodynamic data of the receiving aircraft under different working conditions through numerical calculation methods;

[0017] The wake field aerodynamic information statistical area analysis module can determine the wake field aerodynamic information statistical area of ​​the receiving aircraft according to the size of the receiving aircraft and the information of the typical position point, and convert the aerodynamic characteristics of the wake field aerodynamic information statistical area of ​​the receiving aircraft into the local airflow angle of the receiving aircraft at the typical position point, that is, the attitude data of the receiving aircraft through data statistical methods;

[0018] The aerodynamic change analysis module of the receiving aircraft obtains the receiving aircraft attitude data and the receiving aircraft aerodynamic data set from the aerodynamic information statistical area of ​​the receiving aircraft wake field, and compares and analyzes the aerodynamic data of the tanker wake field to obtain the aerodynamic change data of the receiving aircraft in the tanker wake field.

[0019] Preferably, when dividing the grid for calculation and analysis of the wake field of the refueling machine, the grid size at the typical position point of the refueling machine is determined according to the size of the receiving machine, and the calculation and analysis grid is constructed.

[0020] Preferably, the data calculation method adopts the finite element method.

[0021] Preferably, the specific method for converting aerodynamic characteristics into attitude data of the receiving aircraft is as follows: a) the statistical area of ​​aerodynamic information of the wake field is selected with reference to the characteristic length of the receiving aircraft; b) the statistical area of ​​aerodynamic information of the wake field is selected with reference to the symmetry plane of the receiving aircraft, and statistics are performed on the left and right sides respectively; c) the flow field information is converted into attitude data of the receiving aircraft by using a statistical method.

[0022] Preferably, the characteristic length includes the span of the receiving aircraft, the fuselage length and the aircraft height.

[0023] Preferably, an interpolation method is used to compare and analyze the attitude data of the receiving aircraft, the aerodynamic data set of the receiving aircraft and the aerodynamic data of the wake field of the refueling aircraft to obtain the aerodynamic change data of the receiving aircraft in the wake field of the refueling aircraft.

[0024] The multi-aircraft aerodynamic compatibility rapid analysis method and system of the present application adopts a numerical simulation method to first obtain the aerodynamic data of the tanker wake field, and then adopts a numerical simulation method to obtain the aerodynamic characteristics database of the receiving aircraft, and then obtains the aerodynamic information statistical area of ​​the receiving aircraft in the tanker wake field according to the flight path of the receiving aircraft during the refueling process, and obtains the aerodynamic change data of the receiving aircraft in the tanker wake field through interpolation calculation; the aerodynamic deformation data of multiple aircraft can be analyzed separately for different aircraft models, thereby completing the aerodynamic compatibility rapid evaluation of multiple aircraft. It is not necessary to have multiple aircraft appearance digital models at the same time, and the simulation analysis of the tanker and the receiving aircraft can be distributed, and there is no need to analyze multiple aircraft at the same time to complete the aerodynamic compatibility rapid evaluation of multiple aircraft; the calculation efficiency is high, the calculation cost is low, and the calculation is accurate. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0026] Figure 1 This is a schematic diagram of the overall process of this application;

[0027] Figure 2 This is a schematic diagram of the refueling flight formation for this application;

[0028] Figure 3 This is a schematic diagram of the aerodynamic information statistics area of ​​the wake field for this application. DETAILED DESCRIPTION

[0029] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0030] A multi-machine pneumatic compatibility rapid analysis method comprises the following steps:

[0031] Step S100, select one of the aircraft types to be analyzed in the typical refueling flight formation, such as Figure 2 , obtain the size of the receiving aircraft and the calculation model of the tanker, divide the calculation and analysis grid of the tanker wake field, simulate and analyze the tanker flow field according to the calculation and analysis grid of the tanker wake field, and obtain the aerodynamic data of the tanker wake field.

[0032] Preferably, when dividing the grid for calculation and analysis of the fuel dispenser wake field, the grid size at the typical position of the fuel dispenser is determined according to the size of the receiving aircraft, and the aerodynamic information of the fuel dispenser wake field is obtained by numerical calculation method based on the grid size at the typical position of the fuel dispenser.

[0033] Step S200, obtaining a calculation model of the receiving aircraft, dividing an aerodynamic calculation analysis grid according to the calculation model of the receiving aircraft, and obtaining aerodynamic data of the receiving aircraft under different flight attitudes by a numerical calculation method.

[0034] Preferably, the data calculation method adopts the finite element method.

[0035] Step S300, obtaining the flight path of the receiving aircraft during the refueling process, and selecting typical position points in the flight path.

[0036] Step S400, according to the size of the receiving aircraft and the information of the typical position points, the aerodynamic information statistical area of ​​the wake flow field of the receiving aircraft is determined, and the aerodynamic characteristics of the aerodynamic information statistical area of ​​the wake flow field of the receiving aircraft are converted into the attitude data of the receiving aircraft by a data statistical method, such as Figure 3 ; The aerodynamic information in the aerodynamic information statistical area of ​​the tail flow field of the receiving aircraft is counted, and the aerodynamic characteristics are converted into the attitude data of the receiving aircraft.

[0037] The specific method for converting aerodynamic characteristics into the attitude data of the receiving aircraft is as follows: a) the statistical area of ​​the aerodynamic information of the wake field is selected with reference to the characteristic length of the receiving aircraft; b) the statistical area of ​​the aerodynamic information of the wake field is selected with reference to the symmetry plane of the receiving aircraft, and statistics are performed on the left and right sides respectively; c) the flow field information is converted into the attitude data of the receiving aircraft using a statistical method.

[0038] Step S500: Use the interpolation method to compare and analyze the attitude data of the receiving aircraft, the aerodynamic data set of the receiving aircraft, and the aerodynamic data of the wake field of the refueling aircraft to obtain the aerodynamic change data of the receiving aircraft in the wake field of the refueling aircraft. Then select other aircraft models and analyze them in turn until the multi-aircraft aerodynamic compatibility assessment is completed.

[0039] In summary, the present application adopts a numerical simulation method, firstly obtains the aerodynamic data of the wake field of the tanker, then obtains the aerodynamic data set of the receiving aircraft under different flight attitudes through computational simulation, and then determines the aerodynamic information statistical area of ​​the receiving aircraft in the wake field of the tanker according to the flight path of the receiving aircraft during the refueling process, converts the aerodynamic information into the attitude data of the receiving aircraft through statistical means, and obtains the aerodynamic change data of the receiving aircraft in the wake field of the tanker through interpolation calculation; the aerodynamic deformation data of multiple aircraft can be analyzed separately for different aircraft models, thereby completing the rapid evaluation of the aerodynamic compatibility of multiple aircraft. It is not necessary to have multiple aircraft appearance digital models at the same time, and the tanker and the receiving aircraft can be simulated and analyzed separately to complete the rapid evaluation of the aerodynamic compatibility of multiple aircraft; the calculation efficiency is high, the calculation cost is low, and the calculation is accurate.

[0040] As a specific implementation, it also includes a multi-machine aerodynamic compatibility rapid analysis system, which adopts the above design and includes a refueling aircraft aerodynamic analysis module, a receiving aircraft aerodynamic data acquisition module, a wake field aerodynamic information statistical area analysis module, and a receiving aircraft aerodynamic change analysis module.

[0041] The tanker aerodynamic analysis module can select one of the aircraft models to be analyzed, obtain the tanker calculation model, divide the tanker wake field calculation analysis grid, analyze the tanker aerodynamic information based on the tanker wake field calculation analysis grid, and obtain the tanker wake field aerodynamic data;

[0042] The aerodynamic data acquisition module of the receiving aircraft can obtain the calculation model of the receiving aircraft, divide the aerodynamic calculation and analysis grid according to the calculation model of the receiving aircraft, and obtain the aerodynamic data of the receiving aircraft under different working conditions through numerical calculation methods;

[0043] The wake field aerodynamic information statistical area analysis module can determine the wake field aerodynamic information statistical area of ​​the receiving aircraft according to the size of the receiving aircraft and the information of the typical position point, and convert the aerodynamic characteristics of the wake field aerodynamic information statistical area of ​​the receiving aircraft into the local airflow angle of the receiving aircraft at the typical position point, that is, the attitude data of the receiving aircraft through data statistical methods;

[0044] The aerodynamic change analysis module of the receiving aircraft obtains the attitude data of the receiving aircraft and the aerodynamic data set of the receiving aircraft in the aerodynamic information statistical area of ​​the receiving aircraft wake field, and compares and analyzes the aerodynamic data of the tanker wake field to obtain the aerodynamic change data of the receiving aircraft in the tanker wake field. Then, other aircraft models are selected and analyzed in turn until the aerodynamic compatibility assessment of multiple aircraft is completed.

[0045] Preferably, when dividing the grid for calculation and analysis of the wake field of the refueling machine, the grid size at the typical position point of the refueling machine is determined according to the size of the receiving machine, and the calculation and analysis grid is constructed.

[0046] Preferably, the data calculation method adopts the finite element method.

[0047] Preferably, the specific method for converting aerodynamic characteristics into attitude data of the receiving aircraft is as follows: a) the statistical area of ​​aerodynamic information of the wake field is selected with reference to the characteristic length of the receiving aircraft; b) the statistical area of ​​aerodynamic information of the wake field is selected with reference to the symmetry plane of the receiving aircraft, and statistics are performed on the left and right sides respectively; c) the flow field information is converted into attitude data of the receiving aircraft by using a statistical method.

[0048] Preferably, the characteristic length includes the span of the receiving aircraft, the fuselage length and the aircraft height.

[0049] Preferably, an interpolation method is used to compare and analyze the attitude data of the receiving aircraft, the aerodynamic data set of the receiving aircraft and the aerodynamic data of the wake field of the refueling aircraft to obtain the aerodynamic change data of the receiving aircraft in the wake field of the refueling aircraft.

[0050] Finally, it should be noted that: the drawings of the embodiments disclosed in the present invention only involve structures related to the embodiments disclosed in the present invention, and other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of the present invention can be combined with each other;

[0051] Finally: The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A multi-machine pneumatic compatibility rapid analysis method, characterized in that: include: Select a type of tanker and receiver to be analyzed, obtain the size of the receiver and the calculation model of the tanker, divide the tanker wake flow field calculation and analysis grid, simulate and analyze the tanker flow field based on the tanker wake flow field calculation and analysis grid, and obtain the aerodynamic data of the tanker wake flow field; Obtain the calculation model of the receiving aircraft, divide the aerodynamic calculation and analysis grid according to the calculation model of the receiving aircraft, and obtain the aerodynamic data of the receiving aircraft under different flight attitudes through numerical calculation methods; Obtain the flight path of the receiving aircraft during the refueling process and select typical location points in the flight path; According to the size of the receiving aircraft and the information of the typical position point, the size and position of the statistical area of ​​the aerodynamic information of the tail flow field of the receiving aircraft are determined, and the aerodynamic characteristics of the statistical area of ​​the aerodynamic information of the tail flow field of the tanker are converted into the local airflow angle of the receiving aircraft at the typical position point, that is, the attitude data of the receiving aircraft through the data statistical method; Based on the receiving aircraft attitude data and receiving aircraft aerodynamic data set obtained from the aerodynamic information statistical area of ​​the receiving aircraft wake field, the aerodynamic change data of the receiving aircraft in the tanker wake field are obtained; then other aircraft models are selected and analyzed in turn until the multi-aircraft aerodynamic compatibility assessment is completed.

2. The multi-machine pneumatic compatibility rapid analysis method according to claim 1, characterized in that: When dividing the grid for calculation and analysis of the wake field of the refueling machine, the grid size at the typical location of the refueling machine is determined according to the size of the receiving machine, and the calculation and analysis grid is constructed.

3. The multi-machine pneumatic compatibility rapid analysis method according to claim 2, characterized in that: The data calculation method adopts the finite element method.

4. The multi-machine pneumatic compatibility rapid analysis method according to claim 1, characterized in that: The specific method for converting aerodynamic characteristics into the attitude data of the receiving aircraft is as follows: a) the statistical area of ​​the aerodynamic information of the wake field is selected with reference to the characteristic length of the receiving aircraft; b) the statistical area of ​​the aerodynamic information of the wake field is selected with reference to the symmetry plane of the receiving aircraft, and statistics are performed on the left and right sides respectively; c) the flow field information is converted into the attitude data of the receiving aircraft using a statistical method.

5. The multi-machine pneumatic compatibility rapid analysis method as claimed in claim 4, characterized in that: Characteristic lengths include the span of the receiving aircraft, fuselage length and aircraft height.

6. The multi-machine pneumatic compatibility rapid analysis method according to claim 1, characterized in that: The interpolation method is used to compare and analyze the attitude data of the receiving aircraft, the aerodynamic data set of the receiving aircraft and the aerodynamic data of the tanker wake field, and the aerodynamic change data of the receiving aircraft in the tanker wake field are obtained.

7. A multi-machine pneumatic compatibility rapid analysis system, using the method according to any one of claims 1 to 6, characterized in that: It includes a refueling aircraft aerodynamic analysis module, a receiving aircraft aerodynamic data acquisition module, a wake field aerodynamic information statistical area analysis module, and a receiving aircraft aerodynamic change analysis module. The tanker aerodynamic analysis module can select one of the aircraft models to be analyzed, obtain the tanker calculation model, divide the tanker wake field calculation analysis grid, analyze the tanker aerodynamic information based on the tanker wake field calculation analysis grid, and obtain the tanker wake field aerodynamic data; The aerodynamic data acquisition module of the receiving aircraft can obtain the calculation model of the receiving aircraft, divide the aerodynamic calculation and analysis grid according to the calculation model of the receiving aircraft, and obtain the aerodynamic data of the receiving aircraft under different flight attitudes through numerical calculation methods; The wake field aerodynamic information statistical area analysis module can determine the size and position of the wake field aerodynamic information statistical area of ​​the receiving aircraft according to the size of the receiving aircraft and the information of the typical position point, and convert the aerodynamic characteristics of the wake field aerodynamic information statistical area of ​​the receiving aircraft into the local airflow angle of the receiving aircraft at the typical position point, that is, the attitude data of the receiving aircraft through data statistical methods; The aerodynamic change analysis module of the receiving aircraft obtains the receiving aircraft attitude data and the receiving aircraft aerodynamic data set from the aerodynamic information statistical area of ​​the receiving aircraft wake field, and compares and analyzes the aerodynamic data of the tanker wake field to obtain the aerodynamic change data of the receiving aircraft in the tanker wake field.

8. The multi-machine pneumatic compatibility rapid analysis system as claimed in claim 7, characterized in that: When dividing the grid for calculation and analysis of the wake field of the refueling machine, the grid size at the typical location of the refueling machine is determined according to the size of the receiving machine, and the calculation and analysis grid is constructed.

9. The multi-machine pneumatic compatibility rapid analysis system as claimed in claim 8, characterized in that: The data calculation method adopts the finite element method.

10. The multi-machine pneumatic compatibility rapid analysis system according to claim 7, characterized in that: The specific method for converting aerodynamic characteristics into the attitude data of the receiving aircraft is as follows: a) the statistical area of ​​the aerodynamic information of the wake field is selected with reference to the characteristic length of the receiving aircraft; b) the statistical area of ​​the aerodynamic information of the wake field is selected with reference to the symmetry plane of the receiving aircraft, and statistics are performed on the left and right sides respectively; c) the flow field information is converted into the attitude data of the receiving aircraft using a statistical method.

11. The multi-machine pneumatic compatibility rapid analysis system as claimed in claim 10, characterized in that: Characteristic lengths include the span of the receiving aircraft, fuselage length and aircraft height.

12. The multi-machine pneumatic compatibility rapid analysis system according to claim 7, characterized in that: The interpolation method is used to compare and analyze the attitude data of the receiving aircraft, the aerodynamic data set of the receiving aircraft and the aerodynamic data of the tanker wake field, and the aerodynamic change data of the receiving aircraft in the tanker wake field are obtained.

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