CN114168796B - Method for establishing high-altitude aerodynamic database of aircraft - Google Patents

Method for establishing high-altitude aerodynamic database of aircraft Download PDF

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CN114168796B
CN114168796B CN202210125796.8A CN202210125796A CN114168796B CN 114168796 B CN114168796 B CN 114168796B CN 202210125796 A CN202210125796 A CN 202210125796A CN 114168796 B CN114168796 B CN 114168796B
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aircraft
macroscopic
space grid
aerodynamic
physical space
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CN114168796A (en
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江定武
王沛
李锦�
万钊
郭勇颜
毛枚良
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Computational Aerodynamics Institute of China Aerodynamics Research and Development Center
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    • G06F16/00—Information retrieval; Database structures therefor; File system structures therefor
    • G06F16/90—Details of database functions independent of the retrieved data types
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
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    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
    • G—PHYSICS
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    • G06—COMPUTING; CALCULATING OR COUNTING
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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces

Abstract

The invention discloses a method for establishing an aircraft high-altitude aerodynamic database, which relates to the field of aircraft research and comprises the following steps: obtaining the appearance parameters of the aircraft; setting state parameters, and generating a plurality of virtual flight states based on the state parameters; performing numerical simulation calculation on each virtual flight state based on the aircraft shape parameters, and correspondingly obtaining corresponding aerodynamic force data for each virtual flight state; acquiring an aircraft high-altitude aerodynamic database based on aerodynamic data corresponding to all the virtual flight states; according to the method, the generalized minimum residual error is adopted for macroscopic quantity estimation, the calculation efficiency of the implicit method is improved, and the construction cost of the high-altitude aerodynamic database can be greatly reduced.

Description

Method for establishing high-altitude aerodynamic database of aircraft
Technical Field
The invention relates to the field of aircraft research, in particular to a method for establishing an aircraft high aerodynamic force database.
Background
During the flying process of an aircraft, the force and moment borne by the aircraft in a specific state often need to be known, so that a control system can reasonably control the flying attitude and ensure the flying safety. The control system stores aerodynamic data of a large number of flight states in advance, and the aerodynamic data are an aerodynamic database. Common methods for obtaining the aerodynamic force of each state in the database include wind tunnel tests, numerical simulation and flight tests.
Under the condition of high altitude (70 km and above), the incoming flow is relatively thin, and the ground wind tunnel test cannot reproduce the incoming flow condition under the real flight condition. The method using flight tests is too costly. The construction of high-precision high-altitude aerodynamic databases basically depends on a numerical simulation method. Due to the rarity of incoming high altitude flows, the flow around the aircraft tends to be multi-flow domain coexisting. Conventional methods of solving the NS equations are not applicable here. The current relatively reliable method is to use a uniform gas kinetics method.
The unified gas dynamics method is based on product decomposition of a Boltzmann model equation, and is a cross-basin and multi-scale method. The method solves the evolution process of the distribution function in a three-dimensional physical space and a three-dimensional speed space. And integrating the distribution function in the convergence state to obtain the pressure and the friction resistance of the surface of the aircraft, and further summing the pressure and the friction resistance of all surface units of the aircraft to obtain the force and the moment applied to the aircraft. In order to obtain the aerodynamic characteristics of a state more quickly, an implicit method is generally used. The existing implicit method with higher efficiency is a method for carrying out macroscopic quantity estimation based on LUSGS (lower and upper triangular matrix symmetric Gauss Seidel) and then carrying out implicit iteration on a distribution function. See in particular: construction and application of hidden algorithm in unified aerodynamic theory format of the Zhuasjun-doctor thesis-northwest industry university-2016.
The establishment of the high-altitude aerodynamic database of the aircraft requires basic data of a large number of states, including combinations of parameters such as different incoming flow Mach numbers, incoming flow heights, aircraft attack angles, aircraft sideslip angles and the like. The total amount of computation is large and the computation cost is also high.
Disclosure of Invention
In order to improve the calculation efficiency and reduce the construction cost of the high-altitude aerodynamic database, the invention provides a method for establishing the high-altitude aerodynamic database of the aircraft.
The method comprises the following steps:
obtaining the appearance parameters of the aircraft;
setting state parameters, wherein the state parameters comprise: flight altitude range and interval, flight mach number range and interval, aircraft angle of attack range and interval, aircraft sideslip angle range and interval;
generating a number of virtual flight states based on the state parameters, the virtual flight states including: flight altitude, flight mach number, aircraft angle of attack, and aircraft sideslip angle;
performing numerical simulation calculation on each virtual flight state based on the aircraft shape parameters, and correspondingly obtaining corresponding aerodynamic force data for each virtual flight state;
acquiring an aircraft high-altitude aerodynamic database based on aerodynamic data corresponding to all the virtual flight states;
wherein, the process of performing numerical simulation calculation on the single virtual flight state comprises the following steps:
step 1: generating an aircraft physical space grid based on the aircraft shape parameters;
step 2: setting the inflow condition, initial iteration condition and iteration of numerical simulation calculationTime step of generation
Figure 100002_DEST_PATH_IMAGE001
；
And step 3: the current time is
Figure 100002_DEST_PATH_IMAGE002
The last moment is
Figure 100002_DEST_PATH_IMAGE003
At the current time, for each physical space grid cell in the aircraft physical space grid, a distribution function on each interface surrounding the physical space grid cell is obtained
Figure 100002_DEST_PATH_IMAGE004
；
And 4, step 4: based on
Figure 259594DEST_PATH_IMAGE004
Calculating the flux of the distribution function
Figure 100002_DEST_PATH_IMAGE005
And macroscopic constant flux
Figure 100002_DEST_PATH_IMAGE006
；
And 5: based on
Figure 317680DEST_PATH_IMAGE006
、
Figure 831838DEST_PATH_IMAGE001
And calculating the corresponding interface area to obtain the residual vector of each physical space grid unit
Figure 100002_DEST_PATH_IMAGE007
；
Step 6: based on
Figure 538632DEST_PATH_IMAGE001
、
Figure 100002_DEST_PATH_IMAGE008
Volume of physical space grid cells and
Figure 680900DEST_PATH_IMAGE007
the Jacobian matrix calculates to obtain the variation of the macroscopic conservation quantity from the last moment to the current moment
Figure 100002_DEST_PATH_IMAGE009
；
And 7: based on
Figure 519674DEST_PATH_IMAGE009
And macro conservation of previous time
Figure 100002_DEST_PATH_IMAGE010
Estimating to obtain the macroscopic conservation quantity estimated quantity of the current moment;
and 8: obtaining a balanced state distribution function of the current moment based on macroscopic conservation quantity pre-estimation calculation of the current moment
Figure 100002_DEST_PATH_IMAGE011
；
And step 9: based on
Figure 645762DEST_PATH_IMAGE011
Obtaining a collision generator in a distributed function control equation for a current time
Figure 100002_DEST_PATH_IMAGE012
；
Step 10: based on
Figure 350720DEST_PATH_IMAGE012
The distribution function control equation is iteratively solved to obtain the variation of the distribution function
Figure 100002_DEST_PATH_IMAGE013
Based on the distribution function at the previous moment
Figure 100002_DEST_PATH_IMAGE014
And
Figure 878653DEST_PATH_IMAGE013
calculating to obtain the distribution function of the current moment
Figure 100002_DEST_PATH_IMAGE015
；
Step 11: based on
Figure 685066DEST_PATH_IMAGE015
Calculating to obtain the macroscopic conservation quantity of the current moment
Figure 100002_DEST_PATH_IMAGE016
；
Step 12: judging whether the current time corresponds to
Figure 704975DEST_PATH_IMAGE008
If the current time is less than the set value, executing a step 13, otherwise, adding 1 at the moment and returning to execute a step 3;
step 13: corresponding aerodynamic force data are obtained based on all macroscopic conservation quantities obtained by calculation.
The applicant researches and discovers that the efficiency of the unified gas dynamics implicit method has a decisive influence on the construction cost of the high-altitude gas dynamics database, and a little improvement on the efficiency brings great benefits, so that the unified gas dynamics implicit method for simulating the aerodynamic characteristic value of the aircraft under the high-altitude condition is improved, and mass state source data required for constructing the gas dynamics database can be obtained more efficiently.
In the process of obtaining aerodynamic characteristics of the aircraft by using the unified gas dynamics method, the generalized minimum residual error method is adopted to estimate macroscopic quantity, and then the implicit iterative solution of the distribution function is carried out. The time consumption of the method is about one order of magnitude less than that of the conventional method. The cost for establishing the high-altitude aerodynamic database can be greatly reduced.
Preferably, the method for obtaining corresponding aerodynamic force data based on macroscopic conservation quantity comprises the following steps:
obtaining the pressure and friction force of the surface of the aircraft based on the macroscopic conservation quantity;
the pressure and friction of all physical space grid cells on the aircraft surface are summed to obtain aerodynamic data.
Conventional aerodynamic force data includes, among other things, axial force, normal force, and pitching moment.
Preferably, the flux of the function is distributed
Figure 973145DEST_PATH_IMAGE005
The calculation method is as follows:
Figure 100002_DEST_PATH_IMAGE017
wherein the content of the first and second substances,
Figure 100002_DEST_PATH_IMAGE018
is the normal velocity at the interface.
Preferably, macroscopically conserved flux
Figure 100002_DEST_PATH_IMAGE019
The calculation method is as follows:
Figure 100002_DEST_PATH_IMAGE020
wherein the content of the first and second substances,
Figure 100002_DEST_PATH_IMAGE021
representing the traversal summation of all velocity space grid points,
Figure 100002_DEST_PATH_IMAGE022
is a vector of the moment of the force,
Figure 100002_DEST_PATH_IMAGE023
respectively the coordinates of a three-dimensional velocity space grid point,
Figure 100002_DEST_PATH_IMAGE024
is a transposed matrix.
Preferably, the physical space grid cell is represented as (i, j, k), the residual vector
Figure 214640DEST_PATH_IMAGE008
The calculation method is as follows:
Figure 100002_DEST_PATH_IMAGE025
wherein i is the number of the physical space grid cell in the first direction, j is the number of the physical space grid cell in the second direction, k is the number of the physical space grid cell in the third direction, (i-1/2, j, k), (i +1/2, j, k), (i, j-1/2, k), (i, j +1/2, k), (i, j, k-1/2), (i, j, k + 1/2) respectively represent the left interface, the right interface, the lower interface, the upper interface, the rear interface and the front interface surrounding the physical space grid cell,
Figure 100002_DEST_PATH_IMAGE026
in terms of the area of the interface,
Figure 100002_DEST_PATH_IMAGE027
is an integral variable.
Preferably, the amount of change from the last time to the present time in macroscopic conservation quantity
Figure 755736DEST_PATH_IMAGE009
The calculation method is as follows:
Figure 100002_DEST_PATH_IMAGE028
wherein the content of the first and second substances,
Figure 100002_DEST_PATH_IMAGE029
is the volume of the physical space grid cell,
Figure 100002_DEST_PATH_IMAGE030
is a matrix of the units,
Figure 100002_DEST_PATH_IMAGE031
is formed by density
Figure 100002_DEST_PATH_IMAGE032
Momentum in x direction
Figure 100002_DEST_PATH_IMAGE033
Momentum in y direction
Figure 100002_DEST_PATH_IMAGE034
Z direction momentum
Figure 100002_DEST_PATH_IMAGE035
And energy
Figure 100002_DEST_PATH_IMAGE036
The conservation variable of the composition is changed,
Figure 100002_DEST_PATH_IMAGE037
is composed of
Figure 669465DEST_PATH_IMAGE008
The jacobian matrix of.
Preferably, a macroscopic conservative estimate of the current time
Figure 100002_DEST_PATH_IMAGE038
The calculation method is as follows:
Figure 100002_DEST_PATH_IMAGE039
。
preferably, the distribution function of the equilibrium state at the current moment
Figure 100002_DEST_PATH_IMAGE040
The calculation method is as follows:
Figure 100002_DEST_PATH_IMAGE041
wherein the content of the first and second substances,
Figure 100002_DEST_PATH_IMAGE042
，
Figure 100002_DEST_PATH_IMAGE043
in order to be the pressure, the pressure is,
Figure 318490DEST_PATH_IMAGE023
respectively the coordinates of a three-dimensional velocity space grid point,
Figure 100002_DEST_PATH_IMAGE044
is the component of the macroscopic velocity in the x-direction,
Figure 100002_DEST_PATH_IMAGE045
is the component of the macroscopic velocity in the y-direction,
Figure 100002_DEST_PATH_IMAGE046
is the component of the macroscopic velocity in the z direction. Note the book
Figure 571748DEST_PATH_IMAGE038
Are respectively five components of
Figure 100002_DEST_PATH_IMAGE047
、
Figure 100002_DEST_PATH_IMAGE048
、
Figure 100002_DEST_PATH_IMAGE049
、
Figure 100002_DEST_PATH_IMAGE050
、
Figure 100002_DEST_PATH_IMAGE051
Then, there are:
Figure 100002_DEST_PATH_IMAGE052
，
Figure 100002_DEST_PATH_IMAGE053
，
Figure 100002_DEST_PATH_IMAGE054
，
Figure DEST_PATH_IMAGE055
，
Figure DEST_PATH_IMAGE056
，
Figure DEST_PATH_IMAGE057
is the specific heat ratio of the gas.
Preferably, the collision generating term
Figure 159112DEST_PATH_IMAGE012
The calculation method is as follows:
Figure DEST_PATH_IMAGE058
Figure DEST_PATH_IMAGE059
wherein the content of the first and second substances,
Figure DEST_PATH_IMAGE060
is the number of the prandtl number,
Figure DEST_PATH_IMAGE061
is the speed of the thermal movement of the molecules,
Figure DEST_PATH_IMAGE062
as a vector of the heat flow,
Figure 465197DEST_PATH_IMAGE024
is a transposed matrix.
Preferably, the macroscopic conservation quantity of the current time
Figure 75170DEST_PATH_IMAGE016
The calculation method is as follows:
Figure DEST_PATH_IMAGE063
Figure DEST_PATH_IMAGE064
wherein the content of the first and second substances,
Figure DEST_PATH_IMAGE065
is a moment vector.
One or more technical schemes provided by the invention at least have the following technical effects or advantages:
the invention improves the conventional unified gas kinetics implicit method, adopts the technical means of Generalized Minimum RESidual Error (GMRES) to estimate the macroscopic quantity, and improves the calculation efficiency of the implicit method. The construction cost of the high-altitude aerodynamic database can be greatly reduced.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention;
FIG. 1 is a schematic flow diagram of a method of building a high altitude aerodynamic database for an aircraft;
FIG. 2 is a schematic diagram of a physical space grid in the shape of a blunt cone;
fig. 3 is a schematic diagram of the convergence course of the pitching moment calculated by different implicit methods.
Detailed Description
In order that the above objects, features and advantages of the present invention can be more clearly understood, a more particular description of the invention will be rendered by reference to the appended drawings. It should be noted that the embodiments of the present invention and features of the embodiments may be combined with each other without conflicting with each other.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, however, the present invention may be practiced in other ways than those specifically described and thus the scope of the present invention is not limited by the specific embodiments disclosed below.
Examples
Referring to fig. 1, fig. 1 is a schematic flow chart of a method for building an aircraft high-altitude aerodynamic database, the invention provides a method for building an aircraft high-altitude aerodynamic database, the method includes:
obtaining the appearance parameters of the aircraft;
setting state parameters, wherein the state parameters comprise: flight altitude range and interval, flight mach number range and interval, aircraft angle of attack range and interval, aircraft sideslip angle range and interval;
generating a number of virtual flight states based on the state parameters, the virtual flight states including: flight altitude, flight mach number, aircraft angle of attack, and aircraft sideslip angle;
performing numerical simulation calculation on each virtual flight state based on the aircraft shape parameters, and correspondingly obtaining corresponding aerodynamic force data for each virtual flight state;
and obtaining an aircraft high-altitude aerodynamic database based on aerodynamic data corresponding to all the virtual flight states.
The method in this embodiment is described in detail below, and the specific implementation steps are as follows:
step 1: for a particular profile (including shape and size) of an aircraft, the range of angles of attack and sideslip of the aircraft is determined according to the given altitude, mach number, angle of attack and sideslip of the aircraft. Determining the flight altitude interval, the flight Mach number interval, the aircraft attack angle interval and the aircraft sideslip angle interval. And obtaining a plurality of states which need to be subjected to numerical simulation when the high-altitude aerodynamic database is built. Each state is identified by (altitude, mach number, angle of attack, angle of sideslip). The specific parameter range size and the interval size may be set and adjusted according to actual needs, and embodiments of the present invention are not specifically limited.
Step 2: for each state in step 1, a numerical simulation of step 3-step 12 is performed.
And step 3: generating an aircraft physical space grid; in practical application, generating an aircraft physical space grid by using grid generation software based on the shape and size of an aircraft;
and 4, step 4: setting the incoming flow conditions (including height, Mach number, attack angle and sideslip angle) of the numerical simulation of the conventional gas dynamics;
and 5: setting initial iteration conditions of the conventional gas dynamic simulation, wherein the initial iteration conditions generally have the same density, speed and pressure as those of the incoming flow;
step 6: setting iterative time step
Figure DEST_PATH_IMAGE066
；
And 7: remember the current time as
Figure 917355DEST_PATH_IMAGE002
The last moment is
Figure 485740DEST_PATH_IMAGE003
. At the current moment, for each physical space grid cell, the distribution function on each interface surrounding the physical space grid cell is obtained
Figure 170799DEST_PATH_IMAGE004
。
Figure 850042DEST_PATH_IMAGE004
The method is based on integral solution of a distribution function control equation, and the specific solving step is referred to the section 2.3.1 of the following documents.
Jiangdu-gas dynamic algorithm research based on model equation analytic solution-Chinese air power research and development center doctor's paper-2016 month 6.
According to
Figure 936947DEST_PATH_IMAGE004
Calculating the flux of the distribution function
Figure 662850DEST_PATH_IMAGE005
And macroscopic constant flux
Figure 897523DEST_PATH_IMAGE019
。
Distribution function flux
Figure 52561DEST_PATH_IMAGE005
The calculation formula is as follows:
Figure 56289DEST_PATH_IMAGE017
wherein
Figure 966476DEST_PATH_IMAGE018
Is the normal velocity at the interface.
Macroscopic conservation of constant flux
Figure 626127DEST_PATH_IMAGE019
The calculation formula is as follows:
Figure 397905DEST_PATH_IMAGE020
wherein
Figure 990561DEST_PATH_IMAGE021
Representing the traversal summation of all velocity space grid points,
Figure DEST_PATH_IMAGE067
is a vector of the moment of the force,
Figure 540491DEST_PATH_IMAGE023
respectively, three-dimensional velocity space grid point coordinates.
And 8: obtaining residual vectors of each physical space grid cell
Figure 749755DEST_PATH_IMAGE008
. The physical space grid cell is denoted (i, j, k). Residual vectors for structural meshes
Figure 512175DEST_PATH_IMAGE008
The calculation formula is as follows:
Figure DEST_PATH_IMAGE068
wherein the subscripts (i-1/2, j, k), (i +1/2, j, k), (i, j-1/2, k), (i, j +1/2, k), (i, j, k-1/2), (i, j, k + 1/2) represent the left interface, the right interface, the lower interface, the upper interface, the rear interface, and the front interface, respectively, surrounding the physical space grid cell,
Figure 270921DEST_PATH_IMAGE026
is the interfacial area.
And step 9: the variable quantity of the macroscopic conservation quantity is obtained by solving the following equation set by adopting GMRES technical means
Figure 195015DEST_PATH_IMAGE009
：
Figure DEST_PATH_IMAGE069
Wherein
Figure 422734DEST_PATH_IMAGE029
Is the volume of a physical space grid cell (i, j, k).
Figure 723265DEST_PATH_IMAGE030
Is a matrix of the units,
Figure 572404DEST_PATH_IMAGE031
is formed by density
Figure 667399DEST_PATH_IMAGE032
Momentum in x direction
Figure 851255DEST_PATH_IMAGE033
Momentum in y direction
Figure 955477DEST_PATH_IMAGE034
Z direction momentum
Figure 377232DEST_PATH_IMAGE035
And energy
Figure 971024DEST_PATH_IMAGE036
Conservation variables (vectors) of composition.
Figure DEST_PATH_IMAGE070
Figure 109355DEST_PATH_IMAGE024
Is a transposed matrix.
Figure DEST_PATH_IMAGE071
As a residual vector
Figure 814006DEST_PATH_IMAGE008
The jacobian matrix of.
Figure DEST_PATH_IMAGE072
Wherein, in the step (A),
Figure DEST_PATH_IMAGE073
the sign of the partial derivative operation.
For unified gas dynamics, direct solution
Figure 434474DEST_PATH_IMAGE071
It is very difficult.
Figure 136851DEST_PATH_IMAGE071
The specific expression does not influence the convergence solution of the steady problem, so the implicit solution method in the NS equation can be used for changing the macroscopic conservation quantity
Figure 29721DEST_PATH_IMAGE009
And carrying out iterative solution.
Is provided with
Figure 272483DEST_PATH_IMAGE009
Macroscopic conservation quantities can be estimated:
Figure 872092DEST_PATH_IMAGE039
this step is called a macroscopic quantity estimation method.
GMRES is a Krylov subspace projection method, an orthogonal basis of the Krylov subspace is constructed through an Arnoldi process, an optimal solution is selected on the Krylov subspace by solving a least square method problem, and a residual error mode during each step of iteration is minimized. The method has been extensively studied in iteratively solving the NS equation. The process is described in detail in the following documents:
zhang Yifeng-high precision format (WCNS) application research for accelerated convergence and complex flow numerical simulation-Mianyang-China aerodynamic research and development center-2007-doctor academic thesis.
Swallow-shake country-high-precision hybrid linear compact format implicit time-advanced method research-mianyang-Chinese aerodynamic research and development center-2013-Master academic paper.
Step 10: according to the estimated macroscopic conservation quantity obtained in the step 9 of the embodiment of the invention
Figure 807687DEST_PATH_IMAGE038
Determining the current time by combining the relation between the macroscopic conservation quantity and the equilibrium state distribution function (
Figure 171541DEST_PATH_IMAGE002
) Estimated equilibrium distribution function
Figure 155677DEST_PATH_IMAGE011
。
Figure DEST_PATH_IMAGE074
Wherein, the equilibrium state distribution function is an unknown item in the distribution function control equation, the value of the unknown item needs to be obtained first to solve the distribution function control equation,
Figure 468847DEST_PATH_IMAGE042
，
Figure 513026DEST_PATH_IMAGE043
in order to be the pressure, the pressure is,
Figure 380488DEST_PATH_IMAGE023
respectively the coordinates of a three-dimensional velocity space grid point,
Figure 715786DEST_PATH_IMAGE044
is the component of the macroscopic velocity in the x-direction,
Figure 289987DEST_PATH_IMAGE045
is the component of the macroscopic velocity in the y-direction,
Figure 567384DEST_PATH_IMAGE046
is the component of the macroscopic velocity in the z direction. Note the book
Figure 390984DEST_PATH_IMAGE038
Are respectively five components of
Figure 982502DEST_PATH_IMAGE047
、
Figure 473526DEST_PATH_IMAGE048
、
Figure 642864DEST_PATH_IMAGE049
、
Figure 484918DEST_PATH_IMAGE050
、
Figure 614548DEST_PATH_IMAGE051
Then, there are:
Figure 694499DEST_PATH_IMAGE052
，
Figure 579279DEST_PATH_IMAGE053
，
Figure 580733DEST_PATH_IMAGE054
，
Figure DEST_PATH_IMAGE075
，
Figure DEST_PATH_IMAGE076
，
Figure 592682DEST_PATH_IMAGE057
is the specific heat ratio of the gas.
Further determining the current time (
Figure 792720DEST_PATH_IMAGE002
) One of the collision generators in the predicted distribution function control equation
Figure DEST_PATH_IMAGE077
：
Figure 317242DEST_PATH_IMAGE058
Figure DEST_PATH_IMAGE078
Wherein
Figure 851997DEST_PATH_IMAGE060
Is the number of the prandtl number,
Figure 120167DEST_PATH_IMAGE061
is the molecular thermal motion velocity or specific velocity, also known as random velocity,
Figure 174711DEST_PATH_IMAGE062
is the heat flow vector.
Step 11: based on the result obtained in step 10 of the example of the present invention
Figure 401293DEST_PATH_IMAGE077
And carrying out iterative solution on the distribution function control equation. For details, reference is made to section 4.3 of the following literature.
Jiangdu-gas dynamic algorithm research based on model equation analytic solution-Chinese air power research and development center doctor's paper-2016 month 6.
Obtaining the variation of distribution function
Figure 111760DEST_PATH_IMAGE013
。
Figure 934354DEST_PATH_IMAGE064
The distribution function variance is an unknown in the distribution function control equation.
Due to the distribution function of the last moment
Figure 374562DEST_PATH_IMAGE014
In known amounts. So that the distribution function of the current moment can be obtained
Figure 444150DEST_PATH_IMAGE015
。
Figure 704230DEST_PATH_IMAGE064
With the distribution function of the current time, the macroscopic conservation quantity of the current time can be obtained by the following formula
Figure 579782DEST_PATH_IMAGE016
Figure DEST_PATH_IMAGE079
Step 12: repeat steps 7-11 in the embodiment of the present invention until the residual vector
Figure 595536DEST_PATH_IMAGE008
Less than a set value or until the flow field converges.
Step 13: and collecting aerodynamic force data of all states to obtain a high-altitude aerodynamic force database.
The pressure and the friction of the surface of the aircraft can be obtained through macroscopic conservation quantity, and then the aerodynamic force data can be obtained by summing the pressure and the friction of all points of the surface of the aircraft.
Specific examples of the blunt taper profile are given below.
The radius of the ball head of the blunt cone is 600mm, and the half cone angle is 10 degrees. Table 1 gives the calculation states.
TABLE 1 calculation states
Figure DEST_PATH_IMAGE080
Fig. 2 shows a physical space grid schematic.
Taking a state of (altitude =80km, mach number =10, angle of attack =10, sideslip angle = 0) as an example, the difference in efficiency between the current method of solving aerodynamic characteristics and the conventional method is compared. Fig. 3 shows the convergence course of the pitching moment of the two methods. The implicit method 1 represents a unified gas dynamic implicit method for macroscopic quantity estimation based on a GMRES technology in the invention, and the implicit method 2 represents a traditional unified gas dynamic implicit method for macroscopic quantity estimation based on a LUSGS technology. Implicit method 1 converges at about 1000 steps of the pitching moment. The pitch moment calculated by the implicit method 2 initially oscillates more severely, and the amplitude decreases at about 9000 steps, converging to the same value as in the implicit method 1. The number of calculation steps of the implicit method 1 is only 1/9 of the implicit method 2.
Table 2 gives the results of the calculations for all 24 states in this example. From these calculations a simple high altitude aerodynamic database can be built.
With the method of the present invention, the cost of building an aerodynamic database is nearly an order of magnitude less than conventional methods.
TABLE 2 force coefficient calculation results
Figure DEST_PATH_IMAGE081
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the invention.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.

Claims (10)

1. A method of building a high altitude aerodynamic database for an aircraft, the method comprising:
obtaining the appearance parameters of the aircraft;
setting state parameters, wherein the state parameters comprise: flight altitude range and interval, flight mach number range and interval, aircraft angle of attack range and interval, aircraft sideslip angle range and interval;
generating a number of virtual flight states based on the state parameters, the virtual flight states including: flight altitude, flight mach number, aircraft angle of attack, and aircraft sideslip angle;
performing numerical simulation calculation on each virtual flight state based on the aircraft shape parameters, and correspondingly obtaining corresponding aerodynamic force data for each virtual flight state;
acquiring an aircraft high-altitude aerodynamic database based on aerodynamic data corresponding to all the virtual flight states;
wherein, the process of performing numerical simulation calculation on the single virtual flight state comprises the following steps:
step 1: generating an aircraft physical space grid based on the aircraft shape parameters;
step 2: setting the inflow condition, initial iteration condition and iteration time step length of numerical simulation calculation
Figure DEST_PATH_IMAGE001
；
And step 3: the current time is
Figure DEST_PATH_IMAGE002
The last moment is
Figure DEST_PATH_IMAGE003
At the current time, for each physical space grid cell in the aircraft physical space grid, a distribution function on each interface surrounding the physical space grid cell is obtained
Figure DEST_PATH_IMAGE004
；
And 4, step 4: based on
Figure 390499DEST_PATH_IMAGE004
Calculating the flux of the distribution function
Figure DEST_PATH_IMAGE005
And macroscopic constant flux
Figure DEST_PATH_IMAGE006
；
And 5: based on
Figure 120689DEST_PATH_IMAGE006
、
Figure 634847DEST_PATH_IMAGE001
And calculating the corresponding interface area to obtain the residual vector of each physical space grid unit
Figure DEST_PATH_IMAGE007
；
Step 6: based on
Figure 357952DEST_PATH_IMAGE001
、
Figure 703483DEST_PATH_IMAGE007
Volume of physical space grid cells and
Figure 260366DEST_PATH_IMAGE007
the Jacobian matrix calculates to obtain the variation of the macroscopic conservation quantity from the last moment to the current moment
Figure DEST_PATH_IMAGE008
；
And 7: based on
Figure 104563DEST_PATH_IMAGE008
And macro conservation of previous time
Figure DEST_PATH_IMAGE009
Estimating to obtain the macroscopic conservation quantity estimated quantity of the current moment;
and 8: macroscopic conservation quantity pre-estimate based on current momentCalculating to obtain the equilibrium state distribution function of the current moment
Figure DEST_PATH_IMAGE010
；
And step 9: based on
Figure 100201DEST_PATH_IMAGE010
Obtaining a collision generator in a distributed function control equation for a current time
Figure DEST_PATH_IMAGE011
；
Step 10: based on
Figure 50971DEST_PATH_IMAGE011
The distribution function control equation is iteratively solved to obtain the distribution function variation in the distribution function control equation
Figure DEST_PATH_IMAGE012
Based on the distribution function at the previous moment
Figure DEST_PATH_IMAGE013
And
Figure 106651DEST_PATH_IMAGE012
calculating to obtain the distribution function of the current moment
Figure DEST_PATH_IMAGE014
；
Step 11: based on
Figure 452793DEST_PATH_IMAGE014
Calculating to obtain the macroscopic conservation quantity of the current moment
Figure DEST_PATH_IMAGE015
；
Step 12: judging whether the current time corresponds to
Figure DEST_PATH_IMAGE016
If the current time is less than the set value, executing a step 13, otherwise, adding 1 at the moment and returning to execute a step 3;
step 13: corresponding aerodynamic force data are obtained based on all macroscopic conservation quantities obtained by calculation.
2. The method for building the high-altitude aerodynamic database of the aircraft according to claim 1, wherein the corresponding aerodynamic data are obtained based on macroscopic conservation quantities in the method by the following steps:
obtaining the pressure and friction force of the surface of the aircraft based on the macroscopic conservation quantity;
the pressure and friction of all physical space grid cells on the aircraft surface are summed to obtain aerodynamic data.
3. Method for building an aircraft high aerodynamic database according to claim 1, characterized in that the distribution function flux is distributed
Figure 986542DEST_PATH_IMAGE005
The calculation method is as follows:
Figure DEST_PATH_IMAGE017
wherein the content of the first and second substances,
Figure DEST_PATH_IMAGE018
is the normal velocity at the interface.
4. Method for building an aircraft high aerodynamic database according to claim 3, characterized in that the macroscopic constant flux
Figure 322977DEST_PATH_IMAGE006
The calculation method is as follows:
Figure DEST_PATH_IMAGE019
wherein the content of the first and second substances,
Figure DEST_PATH_IMAGE020
representing the traversal summation of all velocity space grid points,
Figure DEST_PATH_IMAGE021
is a vector of the moment of the force,
Figure DEST_PATH_IMAGE022
respectively the coordinates of a three-dimensional velocity space grid point,
Figure DEST_PATH_IMAGE023
is a transposed matrix.
5. Method for building an aircraft high aerodynamic database according to claim 1, characterized in that the physical space grid cells are represented as (i, j, k), residual vectors
Figure 657881DEST_PATH_IMAGE016
The calculation method is as follows:
Figure DEST_PATH_IMAGE024
wherein i is the number of the physical space grid cell in the first direction, j is the number of the physical space grid cell in the second direction, k is the number of the physical space grid cell in the third direction, (i-1/2, j, k), (i +1/2, j, k), (i, j-1/2, k), (i, j +1/2, k), (i, j, k-1/2), (i, j, k + 1/2) respectively represent the left interface, the right interface, the lower interface, the upper interface, the rear interface and the front interface surrounding the physical space grid cell,
Figure DEST_PATH_IMAGE025
is a boundaryThe area of the surface is as follows,
Figure DEST_PATH_IMAGE026
is an integral variable.
6. Method for building an aircraft high aerodynamic database according to claim 1, characterized in that the variation of the macroscopic conservation quantity from the last moment to the current moment
Figure 243714DEST_PATH_IMAGE008
The calculation method is as follows:
Figure DEST_PATH_IMAGE027
wherein the content of the first and second substances,
Figure DEST_PATH_IMAGE028
is the volume of the physical space grid cell,
Figure DEST_PATH_IMAGE029
is a matrix of the units,
Figure DEST_PATH_IMAGE030
is formed by density
Figure DEST_PATH_IMAGE031
Momentum in x direction
Figure DEST_PATH_IMAGE032
Momentum in y direction
Figure DEST_PATH_IMAGE033
Z direction momentum
Figure DEST_PATH_IMAGE034
And energy
Figure DEST_PATH_IMAGE035
The conservation variable of the composition is changed,
Figure DEST_PATH_IMAGE036
is composed of
Figure 771035DEST_PATH_IMAGE016
The jacobian matrix of.
7. Method for building an aircraft aerodynamic database according to claim 6, characterized in that a macroscopic conservative estimate of the current time is made
Figure DEST_PATH_IMAGE037
The calculation method is as follows:
Figure DEST_PATH_IMAGE038
。
8. method for building an aircraft high aerodynamic database according to claim 7, characterized in that the distribution function of the equilibrium state at the current moment
Figure DEST_PATH_IMAGE039
The calculation method is as follows:
Figure DEST_PATH_IMAGE040
wherein the content of the first and second substances,
Figure DEST_PATH_IMAGE041
，
Figure DEST_PATH_IMAGE042
in order to be the pressure, the pressure is,
Figure 319566DEST_PATH_IMAGE022
respectively the coordinates of a three-dimensional velocity space grid point,
Figure DEST_PATH_IMAGE043
is the component of the macroscopic velocity in the x-direction,
Figure DEST_PATH_IMAGE044
is the component of the macroscopic velocity in the y-direction,
Figure DEST_PATH_IMAGE045
is the component of the macroscopic velocity in the z direction.
9. Method for building an aircraft high aerodynamic database according to claim 8, characterized in that the collision generating term
Figure DEST_PATH_IMAGE046
The calculation method is as follows:
Figure DEST_PATH_IMAGE047
Figure DEST_PATH_IMAGE048
wherein the content of the first and second substances,
Figure DEST_PATH_IMAGE049
is the number of the prandtl number,
Figure DEST_PATH_IMAGE050
is the speed of the thermal movement of the molecules,
Figure DEST_PATH_IMAGE051
as a vector of the heat flow,
Figure 375771DEST_PATH_IMAGE023
is a transposed matrix.
10. Method for building an aircraft high aerodynamic database according to claim 6, characterized in that the macroscopic conservation quantity at the current moment
Figure 635851DEST_PATH_IMAGE015
The calculation method is as follows:
Figure DEST_PATH_IMAGE052
Figure DEST_PATH_IMAGE053
wherein the content of the first and second substances,
Figure DEST_PATH_IMAGE054
is a moment vector.
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Publication number Priority date Publication date Assignee Title
CN114444214B (en) * 2022-04-07 2022-06-07 中国空气动力研究与发展中心计算空气动力研究所 Aircraft control method based on control surface efficiency
CN114444216B (en) * 2022-04-11 2022-06-03 中国空气动力研究与发展中心计算空气动力研究所 Aircraft attitude control method and system under high-altitude condition based on numerical simulation
CN115618498B (en) * 2022-11-08 2023-03-10 中国空气动力研究与发展中心计算空气动力研究所 Prediction method, device, equipment and medium for cross-basin flow field of aircraft
CN116384290B (en) * 2023-06-06 2023-08-22 中国空气动力研究与发展中心计算空气动力研究所 Hypersonic aircraft dynamic derivative prediction method considering real gas effect

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102270252A (en) * 2010-06-04 2011-12-07 利弗莫尔软件技术公司 Systems and methods of performing vibro-acoustic analysis of a structure
CN108920811A (en) * 2018-06-28 2018-11-30 南京航空航天大学 A kind of analogy method and system for helicopter flight simulation
CN111441306A (en) * 2020-04-20 2020-07-24 水利部交通运输部国家能源局南京水利科学研究院 Hydrodynamic force improving method and performance testing method thereof
CN112347561A (en) * 2020-11-10 2021-02-09 中国商用飞机有限责任公司北京民用飞机技术研究中心 Static aeroelasticity analysis method, device, equipment and storage medium of aircraft
CN113694528A (en) * 2021-04-07 2021-11-26 腾讯科技（深圳）有限公司 Data processing method and device, electronic equipment and storage medium

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6956917B2 (en) * 2003-04-17 2005-10-18 Finisar Corporation Method and apparatus for reducing interference in an optical data stream using data-independent equalization
US8495120B2 (en) * 2009-06-15 2013-07-23 Em Photonics, Inc. Method for using a graphics processing unit for accelerated iterative and direct solutions to systems of linear equations

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102270252A (en) * 2010-06-04 2011-12-07 利弗莫尔软件技术公司 Systems and methods of performing vibro-acoustic analysis of a structure
CN108920811A (en) * 2018-06-28 2018-11-30 南京航空航天大学 A kind of analogy method and system for helicopter flight simulation
CN111441306A (en) * 2020-04-20 2020-07-24 水利部交通运输部国家能源局南京水利科学研究院 Hydrodynamic force improving method and performance testing method thereof
CN112347561A (en) * 2020-11-10 2021-02-09 中国商用飞机有限责任公司北京民用飞机技术研究中心 Static aeroelasticity analysis method, device, equipment and storage medium of aircraft
CN113694528A (en) * 2021-04-07 2021-11-26 腾讯科技（深圳）有限公司 Data processing method and device, electronic equipment and storage medium

Non-Patent Citations (6)

* Cited by examiner, † Cited by third party
Title
GMRES convergence bounds that depend on the right-hand-side vector;David Titley-Peloquin 等;《IMA Journal of Numerical Analysis》;20140430;第34卷(第2期);第462-479页 *
使用深度残差网络的乘波体气动性能预测;陈冰雁 等;《空气动力学学报》;20190615;第37卷(第3期);第505-509页 *
基于GM（1,1）残差修正模型的飞行训练量预测;姚裕盛 等;《西安航空学院学报》;20180202;第36卷(第1期);第78-82页 *
气体动理学统一算法的隐式方法研究;毛枚良 等;《力学学报》;20150624;第47卷(第5期);第822-829页 *
虚拟飞行中气动、运动和控制耦合的数值模拟技术;张来平 等;《力学进展》;20141117;第376-417页 *
高阶精度格式（WCNS）加速收敛和复杂流动数值模拟的应用研究;张毅锋;《中国优秀博硕士学位论文全文数据库(博士)基础科学辑》;20100615;A004-2 *

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