A multi-machine pneumatic compatibility rapid analysis method and system

Abstract

The application belongs to the field of aviation aerodynamic analysis, and particularly relates to a multi-aircraft aerodynamic compatibility rapid analysis method and system. The application adopts a numerical simulation mode to obtain aerodynamic force data of a tanker aircraft wake field, and then obtains an aerodynamic force data set of a receiver aircraft under different flight postures through calculation simulation. Then, an aerodynamic information statistical region of the receiver aircraft in the tanker aircraft wake field is determined according to a flight path of the receiver aircraft in a refueling process. Aerodynamic information is converted into receiver aircraft posture data through statistical means, and aerodynamic force change data of the receiver aircraft in the tanker aircraft wake field is obtained through interpolation calculation. The aerodynamic force deformation data of the multi-aircraft can be obtained by analyzing different aircraft types, so that the multi-aircraft aerodynamic compatibility rapid evaluation is completed. The multi-aircraft aerodynamic compatibility rapid evaluation can be completed without simultaneously having multi-aircraft shape numerical models, and the tanker aircraft and the receiver aircraft can be simulated and analyzed respectively. The calculation efficiency is high, the calculation cost is low, and the calculation is accurate.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of aviation aerodynamic analysis, and particularly relates to a multi-aircraft aerodynamic compatibility rapid analysis method and system. BACKGROUND

[0002] When multi-aircrafts fly close to each other, such as air refueling and formation flight, the wake field of the front aircraft has certain aerodynamic interference on the rear aircraft, which affects the flight performance of the rear aircraft and brings difficulties to the pilot in controlling the aircraft. In special cases such as the rear aircraft entering the wing tip vortex core area of the front aircraft, sometimes even the flight safety of the rear aircraft is endangered. Therefore, before performing such tasks, a large amount of simulation analysis needs to be carried out to demonstrate the feasibility of the scheme and to develop a safe and reliable flight task execution procedure. The commonly used numerical analysis method at present is to divide the grid in the calculation domain by placing the multi-aircraft calculation models in the calculation domain at the same time, and then to carry out calculation and analysis at the same time. The disadvantages of this method are: 1) it is necessary to have multi-aircraft shape models at the same time, while in most cases, the aerodynamic shape of the front and rear aircrafts is highly classified and the intellectual property belongs to different units, making it difficult to carry out multi-aircraft simulation analysis at the same time; 2) multi-aircraft simulation analysis at the same time increases the difficulty of dividing the grid, the difficulty of calculation and analysis process, and the cost of calculation resources and time. Therefore, it has become a technical problem to be solved in the field to form a rapid aerodynamic compatibility evaluation method which can be completed in a distributed manner. SUMMARY

[0003] The purpose of the present application is to provide a multi-aircraft aerodynamic compatibility rapid analysis method and system to solve the problem of inconvenient and difficult technical simulation of the existing aerodynamic compatibility evaluation method.

[0004] The technical solution of the present application is: a multi-aircraft aerodynamic compatibility rapid analysis method, comprising: selecting a type of tanker and a receiver aircraft required for analysis, obtaining the size of the receiver aircraft and the calculation model of the tanker, dividing the tanker wake field calculation and analysis grid, simulating and analyzing the flow field of the tanker according to the tanker wake field calculation and analysis grid, and obtaining the aerodynamic force data of the tanker wake field;

[0005] obtaining the calculation model of the receiver aircraft, dividing the aerodynamic force calculation and analysis grid according to the calculation model of the receiver aircraft, and obtaining the aerodynamic force data of the receiver aircraft under different flight attitudes by a numerical calculation method;

[0006] obtaining the flight path of the receiver aircraft during the refueling process, and selecting a typical position point in the flight path;

[0007] determining the size and position of the aerodynamic information statistical area of the receiver aircraft wake field according to the size of the receiver aircraft and the typical position point information, and converting the aerodynamic characteristics of the aerodynamic information statistical area of the receiver aircraft wake field into receiver aircraft attitude data by a data statistical method;

[0008] According to the attitude data and aerodynamic force data set of the receiver aircraft obtained from the tail flow field aerodynamic information statistical area of the receiver aircraft, the aerodynamic force change data of the receiver aircraft in the tanker tail flow field is obtained; then other aircraft models are selected for sequential analysis until the multi-aircraft aerodynamic compatibility evaluation is completed.

[0009] Preferably, when the tanker tail flow field calculation analysis grid is divided, the grid size at the typical position point of the tanker is determined according to the size of the receiver aircraft, and the calculation analysis grid is constructed.

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

[0011] Preferably, the specific method of converting the aerodynamic characteristics into the attitude data of the receiver aircraft is: a) the tail flow field aerodynamic information statistical area is selected with the characteristic length of the receiver aircraft as the reference; b) the tail flow field aerodynamic information statistical area is statistically analyzed on the left and right sides with the symmetry plane of the receiver aircraft as the reference; and c) the flow field information is converted into the attitude data of the receiver aircraft by using the statistical method.

[0012] Preferably, the characteristic length includes the span length, the body length and the height of the receiver aircraft.

[0013] Preferably, the interpolation method is used to compare and analyze the attitude data of the receiver aircraft, the aerodynamic force data set of the receiver aircraft and the aerodynamic force data of the tanker tail flow field, so as to obtain the aerodynamic force change data of the receiver aircraft in the tanker tail flow field.

[0014] As a specific embodiment, a multi-aircraft aerodynamic compatibility rapid analysis system includes a tanker aerodynamic force analysis module, a receiver aircraft aerodynamic force data acquisition module, a tail flow field aerodynamic information statistical area analysis module, and a receiver aircraft aerodynamic force change analysis module.

[0015] The tanker aerodynamic force analysis module can select one of the required analysis aircraft models, obtain a tanker calculation model, divide a tanker tail flow field calculation analysis grid, analyze the tanker aerodynamic force information according to the tanker tail flow field calculation analysis grid, and obtain tanker tail flow field aerodynamic force data.

[0016] The receiver aircraft aerodynamic force data acquisition module can obtain a receiver aircraft calculation model, divide an aerodynamic force calculation analysis grid according to the receiver aircraft calculation model, and obtain receiver aircraft aerodynamic force data under different conditions by using a numerical calculation method.

[0017] The tail flow field aerodynamic information statistical area analysis module can determine the tail flow field aerodynamic information statistical area of the receiver aircraft according to the size of the receiver aircraft and the information of the typical position point, and convert the aerodynamic characteristics of the tail flow field aerodynamic information statistical area of the receiver aircraft into the local flow angle of the receiver aircraft at the typical position point, i.e. the attitude data of the receiver aircraft, by using a data statistical method.

[0018] The aerodynamic force change analysis module of the receiver aircraft obtains receiver aircraft attitude data and receiver aircraft aerodynamic force data set according to the aerodynamic information statistical area of the receiver aircraft wake field, and compares and analyzes the data in combination with the aerodynamic force data of the tanker aircraft, to obtain the aerodynamic force change data of the receiver aircraft in the tanker aircraft wake field.

[0019] Preferably, when the tanker aircraft wake field calculation and analysis grid is divided, the grid size at the typical position point of the tanker aircraft is determined according to the size of the tanker aircraft, and the calculation and analysis grid is constructed.

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

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

[0022] Preferably, the characteristic length includes the span length, the body length and the height of the receiver aircraft.

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

[0024] The multi-aircraft aerodynamic compatibility rapid analysis method and system provided in the application adopts a numerical simulation method to obtain the aerodynamic force data of the tanker aircraft wake field, and then obtains the aerodynamic force characteristics database of the receiver aircraft by using the numerical simulation method, and further obtains the aerodynamic information statistical area of the receiver aircraft in the tanker aircraft wake field according to the flight path of the receiver aircraft during the refueling process, and finally obtains the aerodynamic force change data of the receiver aircraft in the tanker aircraft wake field by using the interpolation calculation. The aerodynamic force deformation data of the multi-aircraft can be obtained by analyzing different aircraft models respectively, so that the multi-aircraft aerodynamic compatibility rapid evaluation can be completed. The multi-aircraft aerodynamic compatibility rapid evaluation can be completed without simultaneously having the multi-aircraft shape numerical model, without simultaneously analyzing the multi-aircraft, and without simultaneously analyzing the multi-aircraft. The calculation efficiency is high, the calculation cost is low, and the calculation is accurate. BRIEF DESCRIPTION OF DRAWINGS

[0025] In order to more clearly illustrate the technical solutions provided in the application, the following will briefly introduce the drawings. Obviously, the drawings described below are only some embodiments of the application.

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

[0027] Figure 2 It is a schematic diagram of the tanker-receiver aircraft formation of the application;

[0028] Figure 3 Figure 1 is a schematic diagram of a wake field aerodynamic information statistical region according to the present application. DETAILED DESCRIPTION

[0029] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by a person of ordinary skill in the art without creative work fall within the protection scope of the present application.

[0030] A multi-aircraft aerodynamic compatibility rapid analysis method, comprising the following steps:

[0031] Step S100, selecting one of the aircraft types required to be analyzed in a typical refueling formation, such as Figure 2 , obtaining the size of the receiver aircraft and the calculation model of the receiver aircraft, dividing the calculation and analysis grid of the receiver aircraft wake field, simulating and analyzing the flow field of the receiver aircraft according to the calculation and analysis grid of the receiver aircraft wake field, and obtaining the aerodynamic force data of the receiver aircraft wake field.

[0032] Preferably, when the calculation and analysis grid of the receiver aircraft wake field is divided, the grid size at the typical position point of the receiver aircraft is determined according to the size of the receiver aircraft, and the aerodynamic information of the receiver aircraft wake field is obtained by a numerical calculation method based on the grid size at the typical position point of the receiver aircraft.

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

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

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

[0036] Step S400, determining the aerodynamic information statistical region of the receiver aircraft wake field according to the size of the receiver aircraft and the typical position point information, converting the aerodynamic characteristics of the aerodynamic information statistical region of the receiver aircraft wake field into receiver aircraft attitude data by a data statistical method, such as Figure 3 ; and statistically analyzing the aerodynamic information in the aerodynamic information statistical region of the receiver aircraft wake field, and converting the aerodynamic characteristics into receiver aircraft attitude data.

[0037] The specific method of converting the aerodynamic characteristics into the receiver aircraft attitude data is: a) selecting the wake field aerodynamic information statistical region with the receiver aircraft characteristic length as the reference; b) selecting the wake field aerodynamic information statistical region with the receiver aircraft symmetry plane as the reference, and statistically selecting the left and right sides respectively; and c) converting the flow field information into the receiver aircraft attitude data by using the statistical method.

[0038] In step S500, the receiver aircraft attitude data, the receiver aircraft aerodynamic force data set and the tanker wake field aerodynamic force data are compared and analyzed by using the interpolation method, so as to obtain the aerodynamic force change data of the receiver aircraft in the tanker wake field. Then, other aircraft types are selected for sequential analysis until the multi-aircraft aerodynamic compatibility evaluation is completed.

[0039] In summary, in the application, the aerodynamic force data of the tanker wake field is obtained by using the numerical simulation method, the aerodynamic force data set of the receiver aircraft under different flight attitudes is obtained by simulation calculation, the aerodynamic information statistical region of the receiver aircraft in the tanker wake field is determined according to the flight path of the receiver aircraft during the refueling process, the aerodynamic information is converted into the receiver aircraft attitude data by statistical means, and the aerodynamic force change data of the receiver aircraft in the tanker wake field is obtained by interpolation calculation. The aerodynamic force deformation data of the multi-aircraft can be obtained by analyzing different aircraft types, so as to complete the rapid evaluation of the multi-aircraft aerodynamic compatibility. The simulation analysis of the tanker and the receiver aircraft can be performed without simultaneously having the multi-aircraft shape numerical model, so that the rapid evaluation of the multi-aircraft aerodynamic compatibility can be completed, and the calculation efficiency is high, the calculation cost is low, and the calculation is accurate.

[0040] As a specific embodiment, the application further includes a multi-aircraft aerodynamic compatibility rapid analysis system, which adopts the above design and includes a tanker aerodynamic force analysis module, a receiver aircraft aerodynamic force data acquisition module, a wake field aerodynamic information statistical region analysis module and a receiver aircraft aerodynamic force change analysis module.

[0041] The tanker aerodynamic force analysis module can select one of the aircraft types required for analysis, obtain the tanker calculation model, divide the tanker wake field calculation and analysis grid, analyze the tanker aerodynamic force information according to the tanker wake field calculation and analysis grid, and obtain the tanker wake field aerodynamic force data.

[0042] The receiver aircraft aerodynamic force data acquisition module can obtain the receiver aircraft calculation model, divide the aerodynamic force calculation and analysis grid according to the receiver aircraft calculation model, and obtain the receiver aircraft aerodynamic force data under different working conditions by using the numerical calculation method.

[0043] The wake field aerodynamic information statistical region analysis module can determine the receiver aircraft wake field aerodynamic information statistical region according to the receiver aircraft size and the typical position point information, and convert the aerodynamic characteristics of the receiver aircraft wake field aerodynamic information statistical region into the local flow angle of the receiver aircraft at the typical position point, i.e. the receiver aircraft attitude data, by using the data statistical method.

[0044] The oil receiver aerodynamic force change analysis module obtains the oil receiver attitude data and the oil receiver aerodynamic force data set according to the oil receiver wake field aerodynamic information statistical region, and compares and analyzes the data in combination with the tanker wake field aerodynamic force data, to obtain the oil receiver aerodynamic force change data in the tanker wake field. Then other models are selected for sequential analysis until the multi-aircraft aerodynamic compatibility evaluation is completed.

[0045] Preferably, when the tanker wake field calculation and analysis grid is divided, the grid size at the typical position point of the tanker is determined according to the size of the oil receiver, 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 the aerodynamic characteristics into the oil receiver attitude data is: a) the wake field aerodynamic information statistical region is selected with the characteristic length of the oil receiver as the reference; b) the wake field aerodynamic information statistical region is selected with the symmetry plane of the oil receiver as the reference, and the left and right sides are counted respectively; and c) the flow field information is converted into the oil receiver attitude data by using the statistical method.

[0048] Preferably, the characteristic length includes the oil receiver span, the fuselage length and the aircraft height.

[0049] Preferably, the interpolation method is used to compare and analyze the oil receiver attitude data, the oil receiver aerodynamic force data set and the tanker wake field aerodynamic force data, to obtain the oil receiver aerodynamic force change data in the tanker wake field.

[0050] Finally, it should be noted that the present application discloses the structure involved in the embodiment, and other structures can be referred to the general design, and the same embodiment and different embodiments of the present application can be combined with each other under the condition of no conflict.

[0051] Finally, the above only describes the preferred embodiments of the present application, and is not used to limit the present application, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.

Claims

1. A multi-machine pneumatic compatibility rapid analysis method, characterized in that, The method comprises the following steps: selecting a type of refueling machine and a receiver aircraft for analysis, obtaining the size of the receiver aircraft and a calculation model of the refueling machine, dividing a calculation and analysis grid of the tail flow field of the refueling machine, simulating and analyzing the flow field of the refueling machine according to the calculation and analysis grid of the tail flow field of the refueling machine, and obtaining aerodynamic force data of the tail flow field of the refueling machine; obtaining a calculation model of the receiver aircraft, dividing an aerodynamic force calculation and analysis grid according to the calculation model of the receiver aircraft, and obtaining aerodynamic force data of the receiver aircraft under different flight attitudes by a numerical calculation method; obtaining a flight path of the receiver aircraft in the refueling process, and selecting a typical position point in the flight path; determining the size and position of an aerodynamic information statistical region of the tail flow field of the receiver aircraft according to the size of the receiver aircraft and the information of the typical position point, and converting the aerodynamic characteristics of the aerodynamic information statistical region of the tail flow field of the receiver aircraft into a local airflow angle of the receiver aircraft at the typical position point, i.e., attitude data of the receiver aircraft by a data statistical method; obtaining aerodynamic force change data of the receiver aircraft in the tail flow field of the refueling machine according to the attitude data of the receiver aircraft obtained from the aerodynamic information statistical region of the tail flow field of the receiver aircraft and a set of aerodynamic force data of the receiver aircraft; and then selecting other types of aircraft for analysis in sequence until the aerodynamic compatibility evaluation of multiple aircraft is completed.

2. The multi-machine aerodynamic compatibility quick analysis method of claim 1, wherein: When the calculation and analysis grid of the tail flow field of the refueling machine is divided, the grid size at the typical position point of the refueling machine is determined according to the size of the receiver aircraft, and a calculation and analysis grid is constructed.

3. The multi-machine aerodynamic compatibility quick analysis method of claim 2, wherein: The data calculation method adopts a finite element method.

4. The multi-machine aerodynamic compatibility quick analysis method of claim 1, wherein: The specific method of converting the aerodynamic characteristics into the attitude data of the receiver aircraft is as follows: a) the aerodynamic information statistical region of the tail flow field is selected with reference to the characteristic length of the receiver aircraft; b) the aerodynamic information statistical region of the tail flow field is taken as a reference, and the left and right sides are counted respectively; and c) the flow field information is converted into the attitude data of the receiver aircraft by a statistical method.

5. The multi-machine aerodynamic compatibility quick analysis method of claim 4, wherein: The characteristic length includes the span of the receiver aircraft, the length of the fuselage and the height of the aircraft.

6. The multi-machine aerodynamic compatibility quick analysis method of claim 1, wherein: The attitude data of the receiver aircraft, the set of aerodynamic force data of the receiver aircraft and the aerodynamic force data of the tail flow field of the refueling machine are compared and analyzed by an interpolation method, and aerodynamic force change data of the receiver aircraft in the tail flow field of the refueling machine are obtained.

7. A multi-machine aerodynamic compatibility rapid analysis system using the method according to any one of claims 1-6, characterized in that: The method comprises a refueling machine aerodynamic force analysis module, a receiver aircraft aerodynamic force data acquisition module, a tail flow field aerodynamic information statistical region analysis module and a receiver aircraft aerodynamic force change analysis module. The refueling machine aerodynamic force analysis module can select one type of aircraft for analysis, obtain a calculation model of the refueling machine, divide a calculation and analysis grid of the tail flow field of the refueling machine, analyze the aerodynamic force information of the refueling machine according to the calculation and analysis grid of the tail flow field of the refueling machine, and obtain aerodynamic force data of the tail flow field of the refueling machine. The receiver aircraft aerodynamic force data acquisition module can obtain a calculation model of the receiver aircraft, divide an aerodynamic force calculation and analysis grid according to the calculation model of the receiver aircraft, and obtain aerodynamic force data of the receiver aircraft under different flight attitudes by a numerical calculation method. The tail flow field aerodynamic information statistical region analysis module can determine the size and position of an aerodynamic information statistical region of the tail flow field of the receiver aircraft according to the size of the receiver aircraft and the information of the typical position point, and convert the aerodynamic characteristics of the aerodynamic information statistical region of the tail flow field of the receiver aircraft into a local airflow angle of the receiver aircraft at the typical position point, i.e., attitude data of the receiver aircraft by a data statistical method. The aerodynamic force change analysis module obtains the attitude data of the receiver aircraft and the receiver aircraft aerodynamic force data set according to the aerodynamic information statistical area of the receiver aircraft wake field, and performs comparative analysis combined with the aerodynamic force data of the receiver aircraft, to obtain the aerodynamic force change data of the receiver aircraft in the receiver aircraft wake field.

8. The multi-machine aerodynamic compatibility quick analysis system of claim 7, wherein: When the receiver aircraft wake field calculation analysis grid is divided, the grid size at the typical position point of the receiver aircraft is determined according to the size of the receiver aircraft, and the calculation analysis grid is constructed.

9. The multi-machine aerodynamic compatibility quick analysis system of claim 8, wherein: The data calculation method adopts the finite element method.

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

11. The multi-machine pneumatic compatibility rapid analysis system of claim 10, wherein: The characteristic length includes the span of the receiver aircraft, the length of the fuselage and the height of the aircraft.

12. The multi-machine pneumatic compatibility rapid analysis system of claim 7, wherein: The interpolation method is used to perform comparative analysis on the attitude data of the receiver aircraft, the receiver aircraft aerodynamic force data set and the aerodynamic force data of the receiver aircraft, to obtain the aerodynamic force change data of the receiver aircraft in the receiver aircraft wake field.

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