CN117421825A - CFD simulation method and system for large aircraft under influence of near-stratum wind environment - Google Patents
CFD simulation method and system for large aircraft under influence of near-stratum wind environment Download PDFInfo
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Abstract
The invention relates to the field of numerical simulation, in particular to a CFD simulation method and system for a large aircraft under the influence of near-stratum wind environment, wherein the method comprises the following steps: constructing a wind field grid model of typical terrain; adopting a first wind profile model as an inlet input condition, and simulating a wind field grid model to obtain wind field data; the first wind profile model is a wind profile function used for representing the change of wind speed along with the height direction; selecting a data selection surface according to the flight state and the height direction change of the aircraft, and fitting according to the wind speed vector of each data point in the data selection surface to obtain a second wind profile model, wherein the second wind profile model is a wind profile function for representing the change of wind speed along with the direction of the corresponding data selection surface; and inputting the second wind profile model into the initial six-degree-of-freedom motion equation to solve a modified six-degree-of-freedom motion equation. The invention introduces typical topography factors and real flying environment characteristics into the pneumatic simulation process, and improves the authenticity of the simulation result.
Description
Priority application
The present application claims priority to a large aircraft CFD simulation method and system under the influence of near-stratum wind conditions from chinese patent application CN2023113007559 filed in month 10 of 2023, 9, which is incorporated by reference in its entirety.
Technical Field
The invention relates to the field of numerical simulation, in particular to a CFD simulation method and system for a large aircraft under the influence of near-stratum wind environment.
Background
The pneumatic simulation of the aircraft is crucial to the flight attitude control of the aircraft, and the existing pneumatic simulation and flight control of the aircraft mainly comprise the following two routes:
1. controlling aircraft flight attitude using monitored wind data
For example, CN105182989a discloses a flight control method that uses wind data collected at monitoring points to achieve flight control adjustments for an aircraft. However, the investment cost for arranging the wind measuring tower and the laser radar at the planned point location is very high, the wind measuring point location and the height are difficult to meet the requirements, and only wind measuring data below 300m of the planned point location can be measured.
2. Aircraft flight attitude control using simulation models
For example, CN108008645A discloses a six-degree-of-freedom simulation modeling method,
The unmanned aerial vehicle flight control system can be used for flight control and flight path planning and display tasks in the unmanned aerial vehicle simulation flight process. However, the simulation mode does not consider the influence of real meteorological factors on the flight attitude, and is difficult to apply to the pneumatic simulation of a large-scale aircraft.
In the existing simulation route, wind field characteristics of a flight environment can be simulated by using an air disturbance model, and then motion simulation data of an airplane are calculated by combining wind field data obtained by simulation with a power model. Among them, the common air disturbance models generally include constant wind, gust and gust models, but the air disturbance models are generally different from the actual wind field state, and the accuracy of the data is also low.
For example, CN105182989a discloses a method of controlling the attitude of an aircraft under the influence of a wind field. The method adopts the technical route that: and assuming the aircraft to fly straight, arranging a symmetrical vortex ring on the flight path to simulate a micro undershoot airflow wind field. However, the actual course of an aircraft is very complex, and this mode of micro-undershoot airflow wind park is difficult to solve with real flight control issues.
Furthermore, CN116167249a discloses a method, a device and a storage medium for calculating the dynamic load of an asymmetric landing of an aircraft, where the method regards the aircraft as a separate structure (e.g. distinguishes a landing gear system), and further introduces the aircraft structural parameter, the landing gear system performance parameter, the landing state parameter and the environmental parameter into a kinematic model, and further obtains the flight power data of the aircraft by solving. However, the split simulation mode is often suitable for an asymmetric landing stage, and is difficult to apply to an aerial navigation stage of an aircraft.
Therefore, a simulation method capable of improving the accuracy of the aerodynamics simulation of the flight is needed.
Disclosure of Invention
The invention aims to provide a CFD simulation method and system for a large-scale aircraft under the influence of near-stratum wind environment, which partially solve or relieve the defects in the prior art and can improve the accuracy and reliability of numerical simulation of the large-scale transportation aircraft.
In order to solve the technical problems, the invention adopts the following technical scheme:
according to the method, a real wind field in an atmosphere boundary layer affected by typical terrain can be well simulated, and a new six-degree-of-freedom response equation affected by the wind field can be obtained by calculation as an input condition of simulation of flight dynamics and flight mechanics models of the large transport aircraft, so that the problems in the background art are solved.
The CFD simulation method of the large aircraft under the influence of the near-stratum wind environment comprises the following steps:
s101, constructing a wind field grid model of typical terrain;
s102, adopting a first wind profile model as an inlet input condition, and carrying out numerical simulation on the wind field grid model to obtain first wind field data; wherein the first wind profile model is a wind profile function for representing a change of wind speed along the height direction of the typical terrain, and correspondingly the first wind field data is a wind speed vector distributed along the height direction of the typical terrain;
S103, selecting at least one corresponding data selection surface according to the flight state of the airplane and the change of the altitude direction, and fitting according to the wind speed vector of each data point in the data selection surface to obtain a second wind profile model, wherein the second wind profile model is a wind profile function used for representing the change of wind speed along with the direction of the corresponding data selection surface;
s104, inputting the second wind profile model into an initial six-degree-of-freedom motion equation of the aircraft, and calculating a corrected six-degree-of-freedom motion equation corresponding to the current typical terrain through iterative solution.
In some embodiments, the step of selecting at least one data selection surface corresponding to the change in altitude direction according to the flight status of the aircraft comprises:
judging the flight phase of the aircraft according to the flight state of the aircraft, wherein the flight phase comprises the following steps: a high-altitude flight stage, a low-altitude flight stage and a lifting stage;
selecting at least one corresponding data selection surface according to the flight phase, wherein,
when the aircraft is in a high-altitude flight stage, selecting a horizontal plane data selection surface corresponding to the current position, wherein the heights of all points in the horizontal plane data selection surface are the same or similar; when the aircraft is in a low-altitude flight stage and/or a lifting stage, a curved surface data selection surface corresponding to the current position is selected, and the height distribution of each point in the curved surface data selection surface is the same as or similar to the height direction change of the typical terrain.
In some embodiments, prior to S101, further comprising the steps of:
providing an offline database, wherein the offline database comprises: at least one second wind field data of a set wind field area, wherein the second wind field data is a wind speed vector which is obtained by simulation according to historical meteorological data and changes along the height direction of a typical terrain;
judging whether second wind field data corresponding to the typical topography exists in the offline database; if not, executing S101; if yes, the second wind field data is used as the first wind field data, and step S103 is executed.
In some embodiments, before the second wind profile model is obtained by fitting the wind speed vector in the data selection surface, the method further comprises the steps of:
s105, calculating standard point variances of all data points in the first wind field data;
s106, screening and filtering data points, in the first wind field data, of which the standard point variance belongs to a preset variance threshold range;
and S107, improving the resolution of the filtered first wind field data by adopting an interpolation method.
In some embodiments, before S107, the method further comprises the step of:
judging whether the resolution of the filtered first wind field data belongs to a preset resolution threshold range or not; if yes, executing S107; if not, prompting the user to adjust the preset variance threshold range.
In some embodiments, S101 comprises:
acquiring terrain data for the representative terrain, the terrain data comprising: longitude and latitude coordinates, and terrain height distribution;
constructing a wind field grid model corresponding to the typical terrain by using the terrain data by adopting a three-dimensional modeling method;
and determining a near stratum area according to the typical topography, and encrypting the grid of the near stratum area of the wind field grid model.
In some embodiments, prior to S101, further comprising the steps of:
determining a typical characterization index for the typical terrain from a terrain class of the typical terrain, the terrain class including one or more of: canyon terrain, hilly terrain;
and judging whether the typical characterization index accords with a preset simulation condition range, if so, executing S101, and if not, prompting the user that the current typical topography does not accord with the simulation condition range.
In some embodiments, a large aircraft comprises: fixed wing aircraft, rotorcraft.
The second aspect of the present invention also provides a CFD simulation system for a large aircraft under the influence of a near-stratum wind environment, comprising:
a grid construction module configured to construct a wind field grid model of a typical terrain;
The first wind profile calculation module is configured to adopt a first wind profile model as an inlet input condition, perform numerical simulation on the wind field grid model, and further obtain first wind field data; wherein the first wind profile model is a wind profile function for representing a change of wind speed along the height direction of the typical terrain, and correspondingly the first wind field data is a wind speed vector distributed along the height direction of the typical terrain;
the second wind profile calculation module is configured to select at least one corresponding data selection surface according to the flight state of the airplane and the change of the altitude direction, and fit a wind speed vector of each data point in the data selection surface to obtain a second wind profile model, wherein the second wind profile model is a wind profile function used for representing the change of wind speed along with the direction of the corresponding data selection surface;
a motion equation solving module configured to input the second wind profile model into an initial six-degree-of-freedom motion equation of the aircraft, and calculate a modified six-degree-of-freedom motion equation corresponding to the current typical terrain through iterative solution
In some embodiments, the second wind profile calculation module includes:
A flight phase determination unit configured to determine a flight phase of the aircraft according to a flight state of the aircraft, the flight phase comprising: a high-altitude flight stage, a low-altitude flight stage and a lifting stage;
the plane selection unit is configured to select at least one corresponding data selection plane according to the flight phase, wherein when the aircraft is in the high-altitude flight phase, a horizontal plane data selection plane corresponding to the current position is selected, and the heights of all points in the horizontal plane data selection plane are the same or similar; when the aircraft is in a low-altitude flight stage and/or a lifting stage, a curved surface data selection surface corresponding to the current position is selected, and the height distribution of each point in the curved surface data selection surface is the same as or similar to the height direction change of the typical terrain.
The beneficial technical effects are as follows:
according to the invention, a bidirectional drawing mode for inserting typical data screening (namely data surface selection) is introduced for aerodynamic characteristic simulation of a large-scale aircraft, on one hand, the bidirectional drawing mode introduces environmental factors such as climate factors, typical topography factors and the like into an aerodynamic simulation process, and on the other hand, the relevance between the wind environment influence characteristics of the aircraft and a real flight state (namely the corresponding data selection surface is selected through the flight state) is considered, so that the rapid fusion of limited factors such as climate, typical topography and flight state and the like is realized through the bidirectional drawing mode.
In addition, the invention introduces a bidirectional drawing mode into the pneumatic simulation process of the aircraft,
the method is also beneficial to decoupling the pneumatic simulation process of the large aircraft into two large processes of offline storage and online calculation. The offline storage and online calculation processes are cooperated, so that the processing efficiency in the real-time simulation process can be effectively improved.
Furthermore, the invention also provides a rapid judging (or selecting) mechanism aiming at key stages such as typical terrain recognition, data screening, data processing after data screening and the like, so that the applicability and reliability of the current simulation mode to large-scale flight aerodynamic simulation in a real environment can be rapidly judged through a multi-stage evaluation mode.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art,
the drawings that accompany the embodiments or the prior art description can be briefly described as follows. Like elements or portions are generally identified by like reference numerals throughout the several figures. In the drawings, elements or portions thereof are not necessarily drawn to scale. It will be apparent to those of ordinary skill in the art that the drawings in the following description are of some embodiments of the invention and that other drawings may be derived from these drawings without inventive faculty.
FIG. 1 is a schematic flow chart of a method according to an exemplary embodiment of the invention;
FIG. 2 is a schematic diagram of wind speed as a function of horizontal lateral length at 300m altitude for a typical terrain wind field;
fig. 3 is a schematic block diagram of a system according to an exemplary embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are some, but not all, embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Herein, use is made of a component such as a "module", "part" or "component" for example
The suffix of "unit" is only for facilitating the description of the invention, and is of no particular significance per se. Thus, "module," "component," or "unit" may be used in combination.
As used herein, the terms "upper", "lower", "inner", "outer", "front", and "back" are used interchangeably,
The orientation or positional relationship indicated by "rear", "one end", "the other end", etc. is based on the orientation or positional relationship shown in the drawings, is merely for convenience of description and to simplify the description, and is not indicative or implying that the apparatus or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as limiting the invention. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
The terms "mounted," "configured to," "connected," and the like, herein, are to be construed broadly as, for example, "connected," whether fixedly, detachably, or integrally connected, unless otherwise specifically defined and limited; the two components can be mechanically connected, can be directly connected or can be indirectly connected through an intermediate medium, and can be communicated with each other. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
Herein, "and/or" includes any and all combinations of one or more of the associated listed items.
Herein, "plurality" means two or more, i.e., it includes two, three, four, five, etc.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further restrictions, by statements
The inclusion of an element defined by "… …" does not preclude the presence of additional identical elements in a process, method, article, or apparatus that comprises the element.
As used in this specification, the term "about" is typically expressed as +/-5% of the value, more typically +/-4% of the value, more typically +/-3% of the value, more typically +/-2% of the value, even more typically +/-1% of the value, and even more typically +/-0.5% of the value.
In this specification, certain embodiments may be disclosed in a format that is within a certain range. It should be appreciated that such a description of "within a certain range" is merely for convenience and brevity and should not be construed as a inflexible limitation on the disclosed ranges. Accordingly, the description of a range should be considered to have specifically disclosed all possible sub-ranges and individual numerical values within that range. For example, a range The description of (c) should be taken as having specifically disclosed sub-ranges such as from 1 to 3, from 1 to 4, from 1 to 5, from 2 to 4, from 2 to 6, from 3 to 6, etc., as well as individual numbers within such ranges, e.g. 1,
2,3,4,5 and 6. The above rule applies regardless of the breadth of the range.
The near-ground layer (near surface layer), also referred to herein as the ground boundary layer (surface boundary layer), or near-ground layer, or constant flux layer (constant fluxlayer), is the portion of the atmospheric boundary layer that is stably present, closest to the underlying surface.
In the existing large-scale aircraft pneumatic simulation process, wind interference models such as constant wind, gust and gust models are generally sampled to draw wind field data, and then the aircraft pneumatic characteristic simulation is carried out based on the corresponding wind field data. However, the real flight characteristics of an aircraft may be related to multiple factors, such as real weather, geographical location, airframe design of the aircraft, etc., so that it is difficult for existing simulation methods to reliably reflect the real attitude changes of the aircraft.
In order to improve the pneumatic simulation accuracy of a large-scale aircraft, new wind field drawing data are introduced in the process of constructing the motion equation of the aircraft, and the drawing data are subjected to bidirectional drawing by interpenetration of flight state data screening, so that the influence of key factors such as typical terrain, atmospheric stability, actual flight state of the aircraft and the like on the pneumatic simulation process is introduced.
The construction mode of the six-degree-of-freedom motion equation based on the new wind field drawing data can more accurately simulate the six-degree-of-freedom response equation (or motion equation) of the large-scale transportation aircraft under the influence of the near-stratum wind environment.
Example 1
As shown in FIG. 1, the invention provides a CFD simulation method of a large aircraft under the influence of near-stratum wind environment, which comprises the following steps:
s101, constructing a wind field grid model of typical terrain;
s102, adopting a first wind profile model as an inlet input condition, and carrying out numerical simulation on the wind field grid model to obtain first wind field data; wherein the first wind profile model is a wind profile function for representing a change of wind speed along the height direction of the typical terrain, and correspondingly the first wind field data is a wind speed vector distributed along the height direction of the typical terrain;
s103, selecting at least one corresponding data selection surface according to the flight state of the airplane and the change of the altitude direction, and fitting according to the wind speed vector of each data point in the data selection surface to obtain a second wind profile model, wherein the second wind profile model is a wind profile function (for example, a wind profile piecewise function representing the change of the wind speed along with the plane direction or along with the curved surface direction) for representing the change of the wind speed along with the corresponding data selection surface direction;
S104, inputting the second wind profile model into an initial six-degree-of-freedom motion equation of the aircraft, and calculating a corrected six-degree-of-freedom motion equation corresponding to the current typical terrain through iterative solution.
In some embodiments, the step of selecting at least one data selection surface corresponding to the change in altitude direction according to the flight status of the aircraft comprises:
judging the flight phase of the aircraft according to the flight state of the aircraft, wherein the flight phase comprises the following steps: a high-altitude flight stage, a low-altitude flight stage and a lifting stage;
selecting at least one corresponding data selection surface according to the flight phase, wherein,
when the aircraft is in a high-altitude flight stage, selecting a horizontal plane data selection surface corresponding to the current position, wherein the heights of all points in the horizontal plane data selection surface are the same or similar; when the aircraft is in a low-altitude flight stage and/or a lifting stage, a curved surface data selection surface corresponding to the current position is selected, and the height distribution of each point in the curved surface data selection surface is the same as or similar to the height direction change of the typical terrain.
For example, in some embodiments, when the aircraft is flying at high altitude, a horizontal plane is drawn along the current flight trajectory of the aircraft, and the horizontal plane may be used as the corresponding data selection surface.
When the aircraft flies at low altitude, at least one curved surface is drawn along the flight track according to the height distribution (or fluctuation trend) of the typical terrain, and the corresponding curved surface can be used as the corresponding data selection surface.
When the aircraft ascends or descends, at least one curved surface is drawn along the flight track of the aircraft according to the height distribution (or fluctuation trend) of the typical terrain, and the corresponding curved surface can be used as the corresponding data selection surface. Wherein the curved surface drawn can encompass the area of approach of the aircraft.
For example, in some embodiments, the flight status includes: the flying height of the aircraft is determined by the aircraft,
and (3) a flight path. Wherein the aircraft is considered to be in a high altitude flight phase when the altitude belongs to a first preset altitude threshold (e.g., above about 1-2 km).
And when the flying height belongs to a second preset height threshold value, the aircraft is considered to be in a low-altitude flying stage.
For another example, when the change of the flying height in the first time exceeds the preset difference (or when the change speed of the flying height is greater than the first preset speed), the aircraft is considered to be in a lifting stage, and the curved surface data selection surface is selected.
For another example, in other embodiments, the flight status includes: the characteristics of the airflow layer in which the aircraft is currently located, such as selecting a horizontal plane data selection surface when the aircraft is at the stratosphere, and selecting a curved plane data selection surface when the aircraft is at the stratosphere (e.g., typically less than about 2km from ground).
In some embodiments, prior to S101, further comprising the steps of:
providing an offline database, wherein the offline database comprises: at least one second wind field data of a set wind field area, wherein the second wind field data is a wind speed vector which is obtained by simulation according to historical meteorological data and changes along the height direction of a typical terrain;
judging whether second wind field data corresponding to the typical topography exists in the offline database; if not, executing S101; if yes, the second wind field data is used as the first wind field data, and step S103 is executed.
In some embodiments, the step of obtaining the second wind farm data in the offline database comprises:
step 1: the dominant wind direction is determined based on typical terrain local historical meteorological data (e.g., twenty year meteorological measurements) or what season wind zones the geographic location is in.
Step 2: partitioning the typical terrain results in a plurality of wind park partitions (corresponding to set wind park areas), wherein wind parks may have different wind directions.
For example, 72 wind field divisions are obtained by dividing the typical topography by 5 ° in the latitudinal direction.
Step 3: performing numerical simulation on each wind field partition to obtain corresponding wind field data; wherein, the numerical simulation step includes: taking the first wind profile model as an inlet input condition of the typical topography, and carrying out numerical simulation on a wind field grid model of the typical topography according to the corresponding wind direction; the rest boundary simulation conditions can be set by a user in a self-defined way in combination with the actual solving condition.
Wherein the first wind profile model is the wind speed v under different thermal stabilities w An inlet wind profile model as a function of height z.
Step 4: and storing the wind field data of each wind field partition to the cloud for the subsequent call of the pneumatic simulation process of various large aircrafts.
In this embodiment, factors such as thermal stability and altitude change influence are introduced through the first wind profile model, so that the corresponding wind speed vector is used as offline data. In the actual simulation process, the wind profile model is secondarily drawn according to typical terrain characteristics, aircraft flight states and the like through data screening, data fitting and other modes, so that the online simulation efficiency can be improved (the calculation force requirement on a computer is reduced) through cooperation of an offline process and an online process, and the simulation time is saved.
In some embodiments, before the second wind profile model is obtained by fitting the wind speed vector in the data selection surface, the method further comprises the steps of:
s105, calculating standard point variances of all data points in the first wind field data;
s106, screening and filtering data points, in the first wind field data, of which the standard point variance belongs to a preset variance threshold range;
and S107, improving the resolution of the filtered first wind field data by adopting an interpolation method.
Further, to improve the accuracy of the aerodynamic simulation of the large aircraft, in some embodiments, before S107, the method further includes the steps of:
judging whether the resolution of the filtered first wind field data belongs to a preset resolution threshold range or not; if yes, executing S107; if not, prompting the user to adjust the preset variance threshold range.
In this embodiment, before the secondary drawing of the wind profile model, the standard point variance is used to perform data screening again and increase the resolution synchronously, so as to improve the applicability and accuracy of the secondary drawing wind profile model in the pneumatic simulation applied to the large aircraft.
In some embodiments, S101 comprises:
acquiring terrain data for the representative terrain, the terrain data comprising: longitude and latitude coordinates, and terrain height distribution;
Constructing a wind field grid model corresponding to the typical terrain by using the terrain data by adopting a three-dimensional modeling method;
and determining a near stratum area according to the typical topography, and encrypting the grid of the near stratum area of the wind field grid model.
In this embodiment, in order to ensure the applicability of the simulation method used to the current typical terrain, in some embodiments, before S101, the method further includes the steps of:
determining a typical characterization index for the typical terrain from a terrain class of the typical terrain, the terrain class including one or more of: canyon terrain, hilly terrain;
and judging whether the typical characterization index accords with the simulation condition range corresponding to the preset simulation condition, if so, executing S101, and if not, prompting the user that the current typical topography does not accord with the simulation condition range.
Among these, the typical terrain categories are generally plain and continuous hills, deep canyons.
For example, when the terrain class of a typical terrain is a canyon, the typical characterization index is a height difference between a peak and a valley, and when the height difference falls within a preset simulation condition range, the typical terrain is considered to be suitable for the current simulation mode. For example, the simulation conditions range from (800 m, ++ infinity A kind of electronic device.
For another example, when the terrain class of the typical terrain is hilly terrain, the typical characterization index includes: the terrain continuously undulates relative to altitude, absolute altitude, wherein the typical terrain is considered suitable for the current simulation mode when the relative altitude falls within the first range of simulation conditions and the absolute altitude falls within the first range of simulation conditions. For example, the first simulation condition range is (0,200 m), and the second simulation condition range is (0,500 m).
In this example, a typical characterization index of a typical terrain is rapidly evaluated,
the three-level evaluation mode formed by combining the selection of the data selection surface and the data processing (such as data filtering, data distribution point increasing and other processing modes) can further improve the accuracy and reliability of the pneumatic simulation of the preset offline database in the real flight environment.
Therefore, the three-level evaluation mode can reduce the necessity of real-time online unsteady simulation of wind field data to a certain extent, and further improve the efficiency of pneumatic simulation of a large-scale aircraft.
In some embodiments, a large aircraft comprises: fixed wing aircraft, rotorcraft.
The technical scheme of the invention is described in detail in the following by a specific embodiment:
And obtaining a second wind profile model (or a second wind profile piecewise function) according to the secondary drawing method. Wherein, post-processing software (such as ansys) can be adopted to fit the wind field data (i.e. sampling data) selected by the data selection surface to obtain a second wind profile model, and the result of the fitting function is shown in fig. 2. Then, wind speed vectors of wind field data represented by the second wind profile model in xyz three directions are input into an initial six-degree-of-freedom equation of the large transport aircraft.
Preferably, the first wind profile model is a wind profile model adapted below the atmospheric boundary layer height to which coriolis forces are added. The first wind profile model comprises a corrected wind profile model, and mainly gives the wind speed v under different thermal stabilities w Varying with height zA model of the mouth wind profile.
When the thermal stability is 3 or less:
when the thermal stability is 4 or 5:
in the middle of
z h ＝cu * /f；
z s ＝c′z h ；
x'＝(1-12z/L) 1/3 ；
Wherein v is w For wind speed, z is height, z s And z h For two heights affected differently by ground deflection forces, ψ represents the correction term equation, u zs As z=z s Time wind speed v w Alpha is 0.2 and 0.25 at a stability of 4 or 5, u * 、u 4 、z 0 And L is the surface friction velocity obtained by actual measurement, the wind speed at a preset height of the surface (e.g. 4 m), the surface friction and the morning-obhuff length, respectively, κ is von-karman constant (recommended value is 0.41), f=2Ω E sin lambda is the Coriolis parameter, Ω E Is the earth rotation rate, lambda is the latitude, u g The wind speed is changed to:
calculation terms related to stability for A, B:
wherein μ=z h Each of/L, c and c' is a constant related to the thermal stability.
Large scale movements inside the atmospheric boundary layer are affected by thermal stratification and coriolis effects, caused by earth rotation and inertial mass, respectively. In some embodiments, these effects may also be introduced into the RANS equation set in the wind farm simulation calculation through additional source terms when modeling the entire wind farm.
In some embodiments, the initial six degree of freedom equation of motion includes:
decomposing the motion of the large transport aircraft into translation along three coordinate axes of a ground coordinate system; the three angular movements roll around the centroid, the rolling movement takes the X axis as the axis, the pitching movement takes the Y axis as the axis and the yawing movement takes the Z axis as the axis.
After solving a typical terrain wind field by a CFD method, establishing an expression of a wind speed vector in a ground coordinate system:
v w representing wind velocity vector, v w The subscript xyz denotes xyz three directional components;
the speed of the large transport aircraft is further decomposed into relative speeds in three directions relative to the wind speed in the flight state:
u, v, w represent the relative speeds of the aircraft in three directions, respectively, u x ，u y And u z The speeds of the large transport aircraft in the directions of x, y and z are respectively calculated byv r Indicating the resultant speed of the large transport aircraft at this time:
wherein aerodynamic forces of the large aircraft in three directions are expressed as:
F x ,F y ,F z respectively representing the resistance, lift and lateral force of the aircraft; correspondingly, C x ，C y ，C z Represents the drag coefficient, the lift coefficient and the lateral force coefficient, ρ represents the air density, and S represents the fuselage reference area.
The six-degree-of-freedom motion equation of a large transport aircraft subjected to a typical terrain wind field under an atmospheric boundary layer can be expressed as:
wherein m represents the mass of the large transport aircraft, theta,Gamma represents the pitch angle, yaw angle and roll angle of the body of the large transport aircraft respectively. I x 、I y 、I z Respectively represent the moment of inertia in all directions around the axis of the aircraft body, I xy Is the product of inertia to the body; omega x 、ω y 、ω z Angular velocities in three directions, M x 、M y 、M z Is three direction moment; /> Acceleration of the plane translational motion equation in the triaxial direction is represented, g is gravity acceleration, and +.>Angular acceleration in three directions of body coordinate axes x, y and z is expressed, and the terms +.>The three directions of the machine body coordinate axes x, y and z are respectively indicated as pitch angles, yaw angles and rolling angles.
The aircraft in this embodiment is preferably a large transportation type aircraft including, but not limited to, various stationary wings, rotor wing personnel, unmanned aerial vehicles, and the like.
Example two
Correspondingly, as shown in fig. 3, the invention also provides an aircraft numerical simulation system considering a typical terrain wind field, the system comprises:
a grid construction module 10 configured for constructing a wind field grid model of a typical terrain;
the first wind profile calculation module 20 is configured to perform numerical simulation on the wind field grid model by using the first wind profile model as an inlet input condition, so as to obtain first wind field data; wherein the first wind profile model is a wind profile function for representing a change of wind speed along the height direction of the typical terrain, and correspondingly the first wind field data is a wind speed vector distributed along the height direction of the typical terrain;
a second wind profile calculation module 30, configured to select at least one data selection surface corresponding to the flight status and the altitude direction change of the aircraft, and fit a second wind profile model according to a wind speed vector of each data point in the data selection surface, where the second wind profile model is a wind profile function for representing a change of a wind speed along with the corresponding data selection surface direction;
The motion equation solving module 40 is configured to input the second wind profile model into an initial six-degree-of-freedom motion equation of the aircraft, and calculate a modified six-degree-of-freedom motion equation corresponding to the current typical terrain through iterative solution.
In some embodiments, the second wind profile calculation module 30 includes:
a flight phase determination unit 31 configured to determine a flight phase of the aircraft according to a flight state of the aircraft, the flight phase including: a high-altitude flight stage, a low-altitude flight stage and a lifting stage;
a plane selection unit 32 configured to select a corresponding at least one data selection plane according to the flight phase, wherein when the aircraft is in a high-altitude flight phase, a horizontal plane data selection plane corresponding to a current position is selected, and heights of various points in the horizontal plane data selection plane are the same or similar; when the aircraft is in a low-altitude flight stage and/or a lifting stage, a curved surface data selection surface corresponding to the current position is selected, and the height distribution of each point in the curved surface data selection surface is the same as or similar to the height direction change of the typical terrain.
In some embodiments, the system further comprises:
An offline module 50 configured to provide an offline database, wherein the offline database comprises: at least one second wind field data of a set wind field area, wherein the second wind field data is a wind speed vector which is obtained by simulation according to historical meteorological data and changes along the height direction of a typical terrain;
a data selection module 60 configured to determine whether second wind farm data corresponding to the typical terrain exists in the offline database; if not, inputting the topographic data into the grid construction module 10; if so, the second wind farm data is used as the first wind farm data, and the second wind profile calculation module 30 is started.
In some embodiments, the system further comprises: a data processing module 70, comprising:
a variance calculating unit 71 configured to calculate standard point variances of respective data points in the first wind field data;
a screening filtering unit 72 configured to screen data points in the first wind farm data for which the standard point variance belongs to a preset variance threshold range;
a resolution unit 73 configured to increase the resolution of the filtered first wind field data using an interpolation method.
In some embodiments, the data processing module 70 further comprises the steps of:
a resolution evaluation unit 74 configured to determine whether the resolution of the screened out first wind field data belongs to a preset resolution threshold range; if yes, inputting the corresponding first wind field data into the resolution unit 73; if not, prompting the user to adjust the preset variance threshold range.
In some embodiments, grid construction module 10 includes:
a terrain data acquisition unit 11 configured to acquire terrain data of the typical terrain, the terrain data including: longitude and latitude coordinates, and terrain height distribution;
a wind field grid construction unit 12 configured to construct a wind field grid model corresponding to the typical terrain using the terrain data using a three-dimensional modeling method;
a wind farm grid encryption unit 12 configured to determine a near-horizon area from the typical terrain and encrypt a grid of the near-horizon area of the wind farm grid model.
In some embodiments, the system further comprises: the terrain determination module 80, the terrain determination module 80 further comprising:
a standard index selection unit 81 configured for determining a typical characterization index of the typical terrain from a terrain class of the typical terrain, the terrain class comprising one or more of: canyon terrain, hilly terrain;
The terrain determination unit 82 is configured to determine whether the typical characterization index meets a preset simulation condition range, if yes, send the terrain data of the typical terrain to the grid construction module 10, and if not, prompt the user that the current typical terrain does not meet the simulation condition range.
It will be appreciated that the system of the present invention may also implement the method or the steps in any of the foregoing embodiments, which are not described herein.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further restrictions, by statements
The inclusion of an element defined by "… …" does not preclude the presence of additional identical elements in a process, method, article, or apparatus that comprises the element.
From the above description of the embodiments, it will be clear to those skilled in the art that the above-described embodiment method may be implemented by means of software plus a necessary general hardware platform, but of course may also be implemented by means of hardware, but in many cases the former is a preferred embodiment. Based on such understanding, the technical solution of the present invention may be embodied essentially or in a part contributing to the prior art in the form of a software product stored in a storage medium (e.g. ROM/RAM, magnetic disk, optical disk) comprising several instructions for causing a computer terminal (which may be a mobile phone, a computer, a server, or a network device, etc.) to perform the method according to the embodiments of the present invention.
The embodiments of the present invention have been described above with reference to the accompanying drawings, but the present invention is not limited to the above-described embodiments, which are merely illustrative and not restrictive, and many forms may be made by those having ordinary skill in the art without departing from the spirit of the present invention and the scope of the claims, which are to be protected by the present invention.
Claims (10)
1. The large aircraft CFD simulation method under the influence of the near-stratum wind environment is characterized by comprising the following steps:
s101, constructing a wind field grid model of typical terrain;
s102, adopting a first wind profile model as an inlet input condition, and carrying out numerical simulation on the wind field grid model to obtain first wind field data; wherein the first wind profile model is a wind profile function for representing a change of wind speed along the height direction of the typical terrain, and correspondingly the first wind field data is a wind speed vector distributed along the height direction of the typical terrain;
s103, selecting at least one corresponding data selection surface according to the flight state of the airplane and the change of the altitude direction, and fitting according to the wind speed vector of each data point in the data selection surface to obtain a second wind profile model, wherein the second wind profile model is a wind profile function used for representing the change of wind speed along with the direction of the corresponding data selection surface;
S104, inputting the second wind profile model into an initial six-degree-of-freedom motion equation of the aircraft, and calculating a corrected six-degree-of-freedom motion equation corresponding to the current typical terrain through iterative solution.
2. The method of claim 1, wherein selecting at least one data selection surface corresponding to the altitude direction change according to the flight status of the aircraft comprises:
judging the flight phase of the aircraft according to the flight state of the aircraft, wherein the flight phase comprises the following steps: a high-altitude flight stage, a low-altitude flight stage and a lifting stage;
selecting at least one corresponding data selection surface according to the flight phase, wherein when the aircraft is in a high-altitude flight phase, a horizontal plane data selection surface corresponding to the current position is selected, and the heights of all points in the horizontal plane data selection surface are the same or similar; when the aircraft is in a low-altitude flight stage and/or a lifting stage, a curved surface data selection surface corresponding to the current position is selected, and the height distribution of each point in the curved surface data selection surface is the same as or similar to the height direction change of the typical terrain.
3. The method for CFD simulation of a large aircraft under the influence of near-stratum wind environment according to claim 1, further comprising the steps of, before S101:
providing an offline database, wherein the offline database comprises: at least one second wind field data of a set wind field area, wherein the second wind field data is a wind speed vector which is obtained by simulation according to historical meteorological data and changes along the height direction of a typical terrain;
judging whether second wind field data corresponding to the typical topography exists in the offline database; if not, executing S101; if yes, the second wind field data is used as the first wind field data, and step S103 is executed.
4. The method for CFD simulation of a large aircraft under the influence of near-stratum wind environment according to claim 1, further comprising the steps of, before S101:
determining a typical characterization index for the typical terrain from a terrain class of the typical terrain, the terrain class including one or more of: canyon terrain, hilly terrain;
and judging whether the typical characterization index accords with a preset simulation condition range, if so, executing S101, and if not, prompting the user that the current typical topography does not accord with the simulation condition range.
5. The method for simulating CFD of a large aircraft under the influence of near-stratum wind environment according to claim 1, wherein before the second wind profile model is obtained by fitting the wind velocity vectors in the data selection plane, the method further comprises the steps of:
s105, calculating standard point variances of all data points in the first wind field data;
s106, screening and filtering data points, in the first wind field data, of which the standard point variance belongs to a preset variance threshold range;
and S107, improving the resolution of the filtered first wind field data by adopting an interpolation method.
6. The method for CFD simulation of a large aircraft under the influence of near-stratum wind environment according to claim 5, further comprising the step of, before S107:
judging whether the resolution of the filtered first wind field data belongs to a preset resolution threshold range or not; if yes, executing S107; if not, prompting the user to adjust the preset variance threshold range.
7. The method for CFD simulation of a large aircraft under the influence of near-stratum wind environment according to claim 1, wherein S101 comprises:
acquiring terrain data for the representative terrain, the terrain data comprising: longitude and latitude coordinates, and terrain height distribution;
Constructing a wind field grid model corresponding to the typical terrain by using the terrain data by adopting a three-dimensional modeling method;
and determining a near stratum area according to the typical topography, and encrypting the grid of the near stratum area of the wind field grid model.
8. The method for simulating CFD of a large aircraft under the influence of near-stratum wind environment according to claim 1, wherein the large aircraft comprises: fixed wing aircraft, rotorcraft.
9. A large aircraft CFD simulation system under the influence of near-formation wind environment, comprising:
a grid construction module configured to construct a wind field grid model of a typical terrain;
the first wind profile calculation module is configured to adopt a first wind profile model as an inlet input condition, perform numerical simulation on the wind field grid model, and further obtain first wind field data; wherein the first wind profile model is a wind profile function for representing a change of wind speed along the height direction of the typical terrain, and correspondingly the first wind field data is a wind speed vector distributed along the height direction of the typical terrain;
the second wind profile calculation module is configured to select at least one corresponding data selection surface according to the flight state of the airplane and the change of the altitude direction, and fit a wind speed vector of each data point in the data selection surface to obtain a second wind profile model, wherein the second wind profile model is a wind profile function used for representing the change of wind speed along with the direction of the corresponding data selection surface;
And the motion equation solving module is configured to input the second wind profile model into an initial six-degree-of-freedom motion equation of the aircraft, and calculate a modified six-degree-of-freedom motion equation corresponding to the current typical terrain through iterative solving.
10. The large aircraft CFD simulation system in the near-formation wind environment according to claim 9, wherein the second wind profile calculation module comprises:
a flight phase determination unit configured to determine a flight phase of the aircraft according to a flight state of the aircraft, the flight phase comprising: a high-altitude flight stage, a low-altitude flight stage and a lifting stage;
the plane selection unit is configured to select at least one corresponding data selection plane according to the flight phase, wherein when the aircraft is in the high-altitude flight phase, a horizontal plane data selection plane corresponding to the current position is selected, and the heights of all points in the horizontal plane data selection plane are the same or similar; when the aircraft is in a low-altitude flight stage and/or a lifting stage, a curved surface data selection surface corresponding to the current position is selected, and the height distribution of each point in the curved surface data selection surface is the same as or similar to the height direction change of the typical terrain.
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