CN104699947B - A kind of method of use RANS/LES hybrid technologies simulated flight device rock and roll motion - Google Patents
A kind of method of use RANS/LES hybrid technologies simulated flight device rock and roll motion Download PDFInfo
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Abstract
The invention discloses a kind of method of use RANS/LES hybrid technologies simulated flight device rock and roll motion, it is therefore intended that solve prior art can not the self-excitation rock and roll that separates on a large scale under flox condition of accurate simulation aircraft the problem of move, mainly include：Turbulence model length dimension is suitably corrected on the basis of traditional unsteady RANS methods, DES class methods are constructed；Using Predictor-Correcting Algorithm, realize that the close coupling of flow field control equation and rigid block element is solved in the pseudo-time iterative process of dual-time scale, obtain rudders pneumatic power parameter and kinematic parameter changes with time course.The present invention can be on the premise of certain computational efficiency be ensured, aircraft self-excitation rock and roll is moved under the conditions of accurately simulating Complex Flows, and effective means is provided for the Non-linear coupling characteristic evaluation of flight vehicle aerodynamic/motion.
Description
Technical field
It is especially a kind of to be flown using the simulation of RANS/LES hybrid technologies the present invention relates to flight vehicle aerodynamic analogy method
The method of row device rock and roll motion.
Background technology
Rock and roll (Rock) is pneumatic/motion coupling phenomenon that modern combat aircraft and missile armament are frequently encountered, and it is winged
Oscillating movement of the row device in rolling direction.Vibrated in some cases with rolling, yaw direction can also vibrate, be referred to as Holland
Roll (Dutch-roll).As the angle of attack increases, Dutch roll is gradually evolved into the rock and roll motion based on rolling.Rock and roll motion is usual
It is to occur in limit cycles oscillations (Limit Cycle Oscillation, LCO) form.Limit cycles oscillations meaned in a week
The energy variation of motion is zero in phase, that is, the energy absorbed is equal with the energy dissipated, and vibration neither dissipates nor restrained, and is formed
Constant amplitude constant periodic oscillation.In theory, it can all enter rock and roll from arbitrary initial state under perturbation action, finally stablize in the limit
Ring status, but some limit cycles oscillations are unstable, now phase plane there may be other limit cycles, and system is made in disturbance
Can be in limit interannular saltus step, into chaotic motion under.Rock and roll motion is breakneck state, if not knowing about what is occurred
The characteristic and flow mechanism of rock and roll motion, control system do not have suitable control method to go amendment, then theoretically just
Through entering flight out of control.
At present, the predictions and simulations moved for aircraft rock and roll, mainly pass through two kinds of sides of wind tunnel test and numerical computations
Method is carried out.
The rounded flowing pattern of more truly simulated flight device is capable of in wind tunnel test, has certain standard in simulation rock and roll motion
True property.But wind tunnel test exist it is uneven to flow, wind tunnel wall interference, support interference, many-sided interference such as bearing friction, and aircraft
The motion of self-excitation rock and roll it is more sensitive to inlet flow conditions, wind tunnel simulation result and live flying condition is there is certain difference.
Numerical computations are mainly the spatial spreading grid for dividing aircraft Flow Field outside, and couple flow field control equation and rigid body
The equation of motion, carries out unsteady time stepping method solution.This method is disturbed in the absence of flow field, close to live flying condition.
Unsteady RANS methods are generally used in being iterated to calculate at present in flow field.Its thought is to be based on Reynolds average, will be flowed
Field information (speed, pressure etc.) resolves into two parts, and Part I is the permanent part unrelated with the time, and another part is pulsation
Part.Therefore the eddy stress produced, is generally used based on Boussinesq eddy viscositys it is assumed that being converted into eddy viscosity
Solve problems, so as to be solved by turbulence model.In engineering commonly use turbulence model have an equation S-A models, Shuan Fangcheng,
Model etc..
RANS methods can obtain more accurate result in prediction of the attachment flowing in attachment flowing or small separation flowing,
But when flowing has large area separation, RANS methods are due to introducing larger dissipation, it is suppressed that the solution of microvortex motion
Analysis, therefore with the increase of the angle of attack, simulation precision drastically declines, and certain challenge is proposed to the motion of accurate simulation rock and roll.
Moved for the aircraft rock and roll under the conditions of accurate simulation High Angle of Attack, complex flowfield, it is necessary to the flow field at each moment
Vortex structure is accurately simulated.And RANS/LES hybrid technologies, the advantage of RANS methods and LES methods is combined,
Have been obtained for being widely applied in high reynolds number, the calculating of large separated flow.The basic thought of RANS/LES hybrid technologies is
Stream field uses multidomain treat-ment, using RANS methods amount of calculation is born near wall flowing, is adopted in separation stream
Make it that flow field vortex structure is finer with LES methods.
Current RANS/LES hybrid technologies are mainly used in that model is static or unsteady separated flow of designated movement mode
In dynamic calculating, do not found application in pneumatic/motion coupling is calculated also, after the result of calculation of previous moment only influences in the former
The flow field at face moment develops, and in the latter while can also be impacted to the model sport of later point.And RANS/LES is mixed
Conjunction method is introduced into more gas information, and compared with traditional unsteady RANS methods, convergence rate is slack-off, calculates and misses
Difference increase, and calculation error is easy to time integral to the evolution of follow-up flow field structure and the influence of the attitude motion of aircraft
Cause to simulate the result made mistake.Therefore, on the one hand need accurately to solve using the smaller time step progress time, and carry out
The comparison checking of different time step-length, on the other hand needs to carry out pneumatic/motion using the higher close coupling method of time precision
Coupling calculate.
The content of the invention
The purpose of the present invention, aiming at the deficiency present in prior art, and provides a kind of using RANS/LES mixing
The technical scheme of the method for technical modelling aircraft rock and roll motion, the program is shaken using RANS/LES hybrid technology simulated flight devices
Rolling motion, on the premise of solution efficiency is ensured, more subtly parses the vortex structure in complex separations flowing, so as to be moved to whirlpool
Accurate predictions and simulations are made in leading aircraft rock and roll motion.
This programme is achieved by the following technical measures：One kind is shaken using RANS/LES hybrid technology simulated flight devices
The method for rolling motion, it is characterised in that：Comprise the following steps：
Step 1: on the basis of traditional unsteady RANS methods, length dimension in turbulence model is replaced with into DES class sides
The length dimension of method, makes flow field simulate the turbulent flow of small yardstick during resolving near wall continuation RANS methods, and is dividing
Vortex structure is simulated using similar Smagorinsky sub-grid scale models from area, so as to obtain the Flow Field Solution of simulated flight device
Calculation method；
Step 2: setting up the rolling single freedom rigid body equation of motion, and with reference to the flow field calculation method that step one is obtained, adopt
With combined interior homotopy, pneumatic/motion close coupling method for solving is constructed；
The rolling single freedom rigid body equation of motion is as follows：
In formula, ωxFor model angular velocity in roll, MxIt is model by rolling moment, IxxFor the rotation in model rolling direction
Inertia, γ is model roll angle, and t is to have the dimension time；
When n-th of actual time step calculates beginning, the moment calculates obtained aerodynamic force to current time before use
Angular velocity in roll and roll angle are predicted, and prediction algorithm is：
In formula, subscript n represents n-th of actual time step；
Then freeze the current true moment, during carrying out pseudo-time iterative flow field, use correcting algorithm pair
Current kinetic parameters are corrected, and correcting algorithm is：
In formula, subscript " new " is represented by value that most further pseudo-time iteration is obtained；
Step 3: for given aircraft profile grid division；
Step 4: using the computational methods in step 2, the space lattice obtained for step 3 is carried out and calculated, obtains
Rudders pneumatic power parameter and kinematic parameter change with time course.
It is used as the preferred of this programme：The scale of the grid divided in step 3 for given aircraft profile is slightly larger than RANS
Calculate required grid scale.
The beneficial effect of this programme can learn according to the narration to such scheme, due in this scenario traditional non-fixed
On the basis of normal RANS methods, length dimension in turbulence model is replaced with to the length dimension of DES class methods, makes flow field solution process
In continue to simulate the turbulent flow of small yardstick with RANS methods near wall, can more accurately simulate the rock and roll of turbulence model
Motion, can more subtly parse the vortex structure in complex separations flowing, so as to be transported to whirlpool on the premise of solution efficiency is ensured
Move leading aircraft rock and roll motion and make accurate predictions and simulations.
As can be seen here, the present invention compared with prior art, with substantive distinguishing features and progress, its beneficial effect implemented
It is obvious.
Brief description of the drawings
Fig. 1 is multi-wall interference mode shape schematic diagram.
Fig. 2 is that the space lattice of multi-wall interference model divides schematic diagram.
Fig. 3 is the model roll angle versus time curve figure obtained using RANS methods.
Fig. 4 is the model roll angle versus time curve figure obtained using DDES methods.
Fig. 5 is the wind-tunnel free rolling experiment provided in the form of angular velocity in roll-roll angle phasor with using DDES side
Method carries out the comparative result figure of free rolling numerical simulation.
Embodiment
All features disclosed in this specification, or disclosed all methods or during the step of, except mutually exclusive
Feature and/or step beyond, can combine in any way.
Any feature disclosed in this specification (including any accessory claim, summary and accompanying drawing), except non-specifically is chatted
State, can alternative features equivalent by other or with similar purpose replaced.I.e., unless specifically stated otherwise, each feature
It is an example in a series of equivalent or similar characteristics.
The present invention comprises the following steps：
Step 1: on the basis of traditional unsteady RANS methods, length dimension in turbulence model is replaced with into DES class sides
The length dimension of method, makes flow field simulate the turbulent flow of small yardstick during resolving near wall continuation RANS methods, and is dividing
Vortex structure is simulated using similar Smagorinsky sub-grid scale models from area, so as to obtain the Flow Field Solution of simulated flight device
Calculation method；
Step 2: setting up the rolling single freedom rigid body equation of motion, and with reference to the flow field calculation method that step one is obtained, adopt
With combined interior homotopy, pneumatic/motion close coupling method for solving is constructed；
The rolling single freedom rigid body equation of motion is as follows：
In formula, ωxFor model angular velocity in roll, MxIt is model by rolling moment, IxxFor the rotation in model rolling direction
Inertia, γ is model roll angle, and t is to have the dimension time；
When n-th of actual time step calculates beginning, the moment calculates obtained aerodynamic force to current time before use
Angular velocity in roll and roll angle are predicted, and prediction algorithm is：
In formula, subscript n represents n-th of actual time step；
Then freeze the current true moment, during carrying out pseudo-time iterative flow field, use correcting algorithm pair
Current kinetic parameters are corrected, and correcting algorithm is：
In formula, subscript " new " is represented by value that most further pseudo-time iteration is obtained；
Step 3: for given aircraft profile grid division；
Step 4: using the computational methods in step 2, the space lattice obtained for step 3 is carried out and calculated, obtains
Rudders pneumatic power parameter and kinematic parameter change with time course.
The scale of the grid divided in step 3 for given aircraft profile calculates required grid rule slightly larger than RANS
Mould.
Apply the present invention to free rolling motion simulation of the multi-wall interference under the conditions of M=0.6, α=35 °.
Calculate and certain multi-wall interference free rolling model in wind tunnel is referred to using profile and rotary inertia, model total length is
504mm, length is 281.4mm, and fuselage diameter is 63mm, and the rotary inertia around model x-axis (fuselage axis) is
0.003675kg·m2。
The present embodiment changes wherein length dimension d based on Spalart-Allmaras Equation Turbulence ModelswFor DDES
Length dimension, construct and obtain DDES methods.
This example divides space lattice, grid cell total amount about 5,920,000 based on multi-wall interference model.Such as Fig. 1,
Shown in Fig. 2.
Design conditions are M=0.6, α=35 °, model reference length LrefTake fuselage maximum gauge 63mm, area of reference Sref
Fuselage maxi mum cross sectional area 3117.245mm2 is taken, the reynolds number Re based on model reference lengthL=1 × 106。
The initial roll angle of model is set as in limit cycle rock and roll motion state, numerical simulation in order that model faster enters
5 °, and the free degree in releasing theory rolling direction.
From different time step-length, and RANS methods and DDES methods is respectively adopted, with reference to rigid block element, carries out tight
Coupling is calculated, and is obtained model roll angle, angular velocity in roll, rolling moment coefficient equivalence and is changed with time course.
According to the numerical simulation result of different calculation methods, model roll angle versus time curve is made respectively, such as
Shown in Fig. 3, Fig. 4.Using RANS methods, model roll angle occurs to vibrate and converge to quickly equilbrium position；Using DDES methods,
Model rapidly enters the motion of limit cycle rock and roll.For two kinds of computational methods, different time step-length is to analog result without essence
Difference.
According to numerical simulation result and results of wind tunnel, model angular velocity in roll-roll angle phase diagram, such as Fig. 5 is made
It is shown.It is coincide using DDES methods acquired results result corresponding with wind tunnel test preferable, because wind tunnel test has more do
The randomness for disturbing different cycles in factor, therefore result is larger, and the randomness of result of calculation is relatively small.
It is as shown in table 1 that wind tunnel test and different calculation methods move analog result to multi-wall interference rock and roll：
The wind tunnel test of table 1 and numerical simulation move analog result to multi-wall interference rock and roll
| Analogy method | Amplitude (°) | Frequency (Hz) |
| Wind-tunnel free rolling is tested | 35.271 | 7.418 |
| Numerical simulation (RANS) | Motion convergence | 7.993 |
| Numerical simulation (DDES) | 35.732 | 7.621 |
As shown in Table 1, the simulation effect moved to wing body rock and roll using traditional RANS methods is poor, and uses DDES side
Method can be obtained and the closer result of wind tunnel test.
Numerical simulation is carried out to the motion of aircraft rock and roll present invention employs DES classes method, large area can be separated and flowed
Fine resolution is made in dynamic complicated whirlpool motion, obtains moving with the more consistent rock and roll of results of wind tunnel so as to simulate.
The invention is not limited in foregoing embodiment.The present invention, which is expanded to, any in this manual to be disclosed
New feature or any new combination, and disclose any new method or process the step of or any new combination.
Claims (2)
1. a kind of method of use RANS/LES hybrid technologies simulated flight device rock and roll motion, it is characterised in that：Including following step
Suddenly：
Step 1: on the basis of traditional unsteady RANS methods, length dimension in turbulence model is replaced with into DES class methods
Length dimension, makes flow field simulate the turbulent flow of small yardstick during resolving near wall continuation RANS methods, and in Disengagement zone
Vortex structure is simulated using Smagorinsky sub-grid scale models, so as to obtain the flow field calculation method of simulated flight device；
Step 2: the rolling single freedom rigid body equation of motion is set up, and the flow field calculation method obtained with reference to step one, using pre-
Estimate-correcting algorithm, construct pneumatic/motion close coupling method for solving；
The rolling single freedom rigid body equation of motion is as follows：
In formula, ωxFor model angular velocity in roll, MxIt is model by rolling moment, IxxFor the rotary inertia in model rolling direction,
γ is model roll angle, and t is to have the dimension time；
When n-th of actual time step calculates beginning, the moment calculates rolling of the obtained aerodynamic force to current time before use
Angular speed and roll angle are predicted, and prediction algorithm is：
In formula, subscript n represents n-th of actual time step；
Then freezing the current true moment, during carrying out pseudo-time iterative flow field, using correcting algorithm to current
Kinematic parameter is corrected, and correcting algorithm is：
In formula, subscript " new " is represented by value that most further pseudo-time iteration is obtained；
Step 3: for given aircraft profile grid division；
Step 4: using the computational methods in step 2, the space lattice obtained for step 3 is carried out and calculated, flown
Device aerodynamic parameter and kinematic parameter change with time course.
2. a kind of method of use RANS/LES hybrid technologies simulated flight device rock and roll motion according to claim 1, its
It is characterized in：The scale of the grid divided in the step 3 for given aircraft profile is more than RANS and calculates required grid rule
Mould.
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| CN106650046B (en) * | 2016-12-02 | 2019-10-18 | 中国船舶工业系统工程研究院 | A kind of unsteady characteristic acquisition methods in Ship Air flow field |
| CN106682398A (en) * | 2016-12-12 | 2017-05-17 | 华南理工大学 | RANS/LES method based on tubulence energy and turbulence length scale truncation |
| CN112131800B (en) * | 2020-07-20 | 2024-04-12 | 中国科学院力学研究所 | Novel large vortex simulation method and device based on energy flow similarity |
| CN112525472B (en) * | 2020-12-07 | 2022-03-22 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel dynamic experiment method for influence of rotational inertia of aircraft model on rock characteristic |
| CN115438601B (en) * | 2022-09-19 | 2023-06-20 | 中国航空发动机研究院 | Hybrid RANS-LES method based on LES adaptive grid filtering scale and related equipment |
| CN116361927B (en) * | 2023-06-02 | 2023-08-29 | 浙江大学 | High-precision turbulence modeling method for complex internal flow numerical simulation of high-speed aircraft |
| CN116910427B (en) * | 2023-09-14 | 2023-12-12 | 清华大学 | Forced resonance calculation method taking wake sweep and wake pulsation into consideration |
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