CN108304684A - A kind of rocket motor tail injection stream emulation mode and system - Google Patents
A kind of rocket motor tail injection stream emulation mode and system Download PDFInfo
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Abstract
A kind of rocket motor tail injection stream emulation mode of the present invention and system.(1) 3-D geometric model of size identical as rocket tube is established；(2) mesh generation is carried out to 3-D geometric model and encrypted, determine boundary condition；(3) computation model is established, it is ensured that tail injection stream process meets sticky navier stokes equations；(4) it uses computation model to be iterated solution to rocket motor tail injection stream model, completes the simulation process of rocket motor tail injection stream.The present invention calculates rocket motor tail injection stream using the SST k ω turbulence models of temperature adjustmemt, compensate for existing turbulence model can not under the big temperature gradient of Accurate Prediction supersonic speed compressible jet defect, the accuracy of simulation result significantly improves, and simulation result is contracted to 1% with experimental results error.
Description
Technical field
The invention belongs to rocket motor tail injection streams to emulate field, be related to a kind of building for simulation model of tail injection stream
It is vertical.
Background technology
Rocket engine makes the chemical energy of medium be converted into interior energy by combustion reaction, and the high temperature and high pressure gas of generation passes through
Nozzle expansion acting generates thrust, therefore tail injection properties of flow can directly affect the key technical indexes such as the thrust of engine, specific impulse.
The research method of rocket motor tail injection stream includes mainly at present：Experimental test method and simulation analysis method；Wherein due to experiment
The limitation of condition and measuring technique it is immature, be only difficult comprehensively intuitive to understand rocket motor nozzle by experimental test
Jet stream feature.In recent years, with the development of Fluid Mechanics Computation, fluid emulation has become the important of analysis rocket engine flow field
Means.This method is not put to the test the limitations such as condition and test equipment, can obtain in computational domain comprehensive flow field data in real time,
Tail injection stream simulation analysis contributes to the promotion of the optimization and engine performance in rocket tube type face.
Rocket motor tail injection stream belongs to the compressible turbulent flow of high speed, and rocket motor tail injection stream emulation at present is mainly adopted
With two-equation turbulence model, as standard k-ε turbulence model, realizable k- ε turbulence models, standard k- ω turbulence models and
SST k- ω turbulence models.The characteristics of above-mentioned model and the scope of application are different, and wherein SST k- ω turbulence models combine
The characteristics of standard k-ε turbulence model and standard k- ω turbulence models, has more wide applicability and reliability, therefore the mould
Type has apparent superiority in calculating rocket motor tail injection stream.However, existing turbulence model presently, there are the problem of
It is：Influence of the big graded of temperature to turbulent dissipation is had ignored, it is both sides' journey turbulent flow mould of representative to lead to SST k- ω models
Type can not accurately calculate the turbulent mixing process under big gradient temperature variation.In consideration of it, improving existing tail injection stream emulation mould
Type and accurate rocket motor tail injection stream emulation mode is established, properties of flow and promotion are sprayed for exploration rocket engines tail
Nozzle performance is most important.
Invention content
Present invention solves the technical problem that being：Overcome the deficiencies of the prior art and provide a kind of rocket motor tail injection stream
Emulation mode and system solve the problems, such as that existing turbulence model can not accurate simulation supersonic speed compressible jet shear-mixed.
The technical scheme is that：A kind of rocket motor tail injection stream emulation mode, steps are as follows：
(1) 3-D geometric model of size identical as rocket tube is established；
(2) mesh generation is carried out to 3-D geometric model and encrypted, determine boundary condition；
(3) computation model is established, it is ensured that tail injection stream process meets sticky Navier Stokes equation；
(4) it uses computation model to be iterated solution to rocket motor tail injection stream model, completes rocket motor tail
The simulation process of injection stream.
Boundary condition is described in step (2)：Nozzle entry and outlet are set as pressure boundary condition, the setting of jet pipe wall surface
For wall boundary condition, axially symmetric face is set as claiming boundary condition；Wherein nozzle entry pressure is the pressure of engine chamber
Power, nozzle exit pressure are environmental pressure.
Nozzle wall is set as wall boundary condition in step (2), and wall surface is characterized as smooth, adiabatic and without sliding.
Turbulence model in step (3) viscosity Navier Stokes equation selects SST k- ω turbulence models, and to SST
K- ω turbulence models carry out temperature adjustmemt.
The modified concrete mode of temperature is to establish temperature using turbulent shear layer gas total temperature gradient as variable in step (3)
Correction function changes tubulence energy distribution by correcting the turbulent viscosity of SST k- ω turbulence models；
It is to the detailed process of SST k- ω turbulence models progress temperature adjustmemt in step (3)：
Build the SST k- ω turbulence model viscosity formulas of temperature adjustmemt：
μ in formulat SST k-ωFor the turbulent viscosity of SST k- ω turbulence models；μt correctedFor the SST k- after temperature adjustmemt
The turbulent viscosity of ω turbulence models；CTFor correction function, expression formula is：
In above formulaH (x) is He Wei Saden jump functions, Mτ0=
0.1, f (Mτ)=0 is indicated without compressible amendment；
MτFor turbulent Mach number, expression formula is：
Wherein a is local velocity of sound, and k is tubulence energy；
TgTo correct variable, expression formula is：
Wherein TtFor gas total temperature,For total temperature gradient absolute value,For turbulent flow length dimension, ω is specific consumption
The rate of dissipating.
It is changed to rocket motor tail injection stream model using the SST k- ω turbulence models of temperature adjustmemt in step (4)
It is for the specific method solved：The SST k- ω turbulent flows modified turbulent viscosity expression formula of temperature gradient being imported into solver
In model, it to be used for the numerical computations of tail injection stream.
A kind of rocket motor tail injection stream analogue system, including 3-D geometric model establishes module, boundary condition determines
Module, computation model establish module and emulation module；It is identical as rocket tube that 3-D geometric model establishes module foundation
The 3-D geometric model of size；Boundary condition determining module carries out mesh generation, encryption to the 3-D geometric model of foundation, and really
Determine boundary condition；Computation model establishes module and establishes computation model, it is ensured that tail injection stream process meets sticky Na Wei-Stokes
Equation；Emulation module establishes module using computation model and is iterated solution to rocket motor tail injection stream model, completes fire
The simulation process of arrow engines tail injection stream.
A kind of rocket motor tail injection stream emulation terminal equipment, including memory, processor and it is stored in described deposit
In reservoir and the computer program that can run on the processor, the processor are realized such as when executing the computer program
The step of above method.
A kind of computer readable storage medium, the computer-readable recording medium storage have computer program, the meter
Calculation machine program is performed the step of realizing method as described above.
The advantageous effect of the present invention compared with prior art is：
The present invention calculates rocket motor tail injection stream using the SST k- ω turbulence models of temperature adjustmemt, compensates for existing
Turbulence model can not under the big temperature gradient of Accurate Prediction supersonic speed compressible jet defect, the accuracy of simulation result significantly carries
Height, simulation result are contracted to 1% with experimental results error.
Description of the drawings
Fig. 1 is rocket motor tail injection stream simulation contact surface；
Fig. 2 is jet pipe grid chart；
Fig. 3 is computational domain grid chart；
Fig. 4 is axial velocity profile figure；
Fig. 5 is axial pressure distribution figure；
Fig. 6 is Axial Temperature Distribution figure；
Fig. 7 is axial velocity checkout result and comparison of test results figure；
Fig. 8 differences the model calculation and comparison of test results figure.
Specific implementation mode
The specific implementation mode of the present invention is as follows：
The overall flow field of rocket motor tail injection stream emulation is as shown in Figure 1, mainly comprise the following steps：
1. establishing Geometric Modeling and mesh generation
According to jet pipe geometric parameter, using Solidwork softwares engine jet pipe shrinkage expansion section and external jet area
Carry out three-dimensional modeling.
2, it divides and calculates grid and determine boundary condition
Mesh generation is carried out to the geometrical model of foundation using Ansys ICEM softwares, the grid of generation is as shown in Figure 2.Hair
Motivation is burnt indoor pressure, temperature, the initial boundary conditions that group gradation parameter is nozzle exit pressure entrance, environmental pressure and environment
Temperature is the initial boundary conditions of nozzle exit, and jet pipe wall surface is smooth adiabatic and without sliding.Gas in jet pipe is compressible, meets
The Ideal-Gas Equation, molecular viscosity meet Su Salan formula.
3, computation model is established
(1) governing equation
Tail injection stream simulation calculation process follows sticky Navier Stokes equation, that is, meets the conservation of mass, the conservation of momentum
And energy conservation equation, associated expression are as follows：
μ is aerodynamic force viscosity in above formula；qiFor heat flow；σijFor viscous stress tensor；cpFor specific heat at constant pressure.
(2) SST k- ω turbulence models and temperature adjustmemt
The transmission equation of SST k- ω turbulence models is：
The turbulent viscosity expression formula of SST k- ω models：
In formula, τijFor Renolds stress tensor, Ω is curl, and ω is than dissipative shock wave, and ν is laminar flow viscosity, y be to wall surface away from
From model constants a1=0.31, β*=0.09, σk1=0.85, σω1=0.5, σk2=1.0, σω2=0.856.
Influence of the temperature gradient to turbulent mixing process is fully considered on the basis of SST k- ω models.With in the scale of turbulence
Total temperature gradient obtains the turbulent viscosity of temperature adjustmemt as variable.Temperature gradient wherein in the scale of turbulence is represented by：
C in revised SST k- ω modelsTExpression formula be：
In above formulaH (x) is He Wei Saden jump functions, Mτ0=0.1, f
(Mт)=0 is indicated without compressible amendment.
The turbulent viscosity expression formula of revised SST k- ω models is：
It is that foundation is complete with experimental condition that the reliability of revised model, which uses hot test data verification, specific method,
Identical computation model, wherein computational domain mesh generation is as shown in figure 3, result of calculation is compared with test data.
4, it calculates and solves and post-process
Calculating solution is carried out using Ansys Fluent business softwares.Choose the density base suitable for high speed compressible jet
Revised turbulent viscosity expression formula is written as C language code and is applied to by User-Defined Functions (UDF) by solver
The calculating solution procedure of fluid.Calculate the speed of the tail injection stream obtained, pressure and temperature is distributed as shown in Fig. 4~Fig. 6, emulation
As a result it tallies with the actual situation.The result of calculation of SST k- ω turbulence models and existing model after temperature adjustmemt and test data
Comparing as shown in Figure 7 and Figure 8, under different temperatures graded, revised the model calculation is coincide very much with test data,
The minimal error that existing model can be realized is 5%, and the calculating error of temperature adjustmemt SST k- ω turbulence models is used to keep
Within 1%.It can be seen that simulation result is greatly improved in rocket motor tail injection stream emulation mode proposed by the present invention
Accuracy.
Note that above are only presently preferred embodiments of the present invention and institute's application technology principle.It will be appreciated by those skilled in the art that
The present invention is not limited to specific embodiments described here, can carry out for a person skilled in the art it is various it is apparent variation,
It readjusts and substitutes without departing from protection scope of the present invention.Therefore, although being carried out to the present invention by above example
It is described in further detail, but the present invention is not limited only to above example, without departing from the inventive concept, also
May include other more equivalent embodiments, and the scope of the present invention is determined by scope of the appended claims.
Unspecified part of the present invention belongs to common sense well known to those skilled in the art.
Claims (10)
1. a kind of rocket motor tail injection stream emulation mode, it is characterised in that steps are as follows：
(1) 3-D geometric model of size identical as rocket tube is established；
(2) mesh generation is carried out to 3-D geometric model and encrypted, determine boundary condition；
(3) computation model is established, it is ensured that tail injection stream process meets sticky Navier Stokes equation；
(4) it uses computation model to be iterated solution to rocket motor tail injection stream model, completes the injection of rocket motor tail
The simulation process of stream.
2. a kind of rocket motor tail injection stream emulation mode according to claim 1, it is characterised in that：In step (2)
The boundary condition is：Nozzle entry and outlet are set as pressure boundary condition, and jet pipe wall surface is set as wall boundary condition, axis
It is set as claiming boundary condition to the plane of symmetry；Wherein nozzle entry pressure is the pressure of engine chamber, and nozzle exit pressure is
Environmental pressure.
3. a kind of rocket motor tail injection stream emulation mode according to claim 1, it is characterised in that：In step (2)
Nozzle wall is set as wall boundary condition, and wall surface is characterized as smooth, adiabatic and without sliding.
4. a kind of rocket motor tail injection stream emulation mode according to claim 1, it is characterised in that：Step (3) is viscous
Property Navier Stokes equation in turbulence model select SST k- ω turbulence models, and to SST k- ω turbulence models carry out
Temperature adjustmemt.
5. a kind of rocket motor tail injection stream emulation mode according to claim 4, it is characterised in that：In step (3)
The concrete mode of temperature adjustmemt is to establish temperature adjustmemt function using turbulent shear layer gas total temperature gradient as variable, pass through amendment
The turbulent viscosity of SST k- ω turbulence models changes tubulence energy distribution.
6. a kind of rocket motor tail injection stream emulation mode according to claim 5, it is characterised in that：In step (3)
To SST k- ω turbulence models carry out temperature adjustmemt detailed process be：
Build the SST k- ω turbulence model viscosity formulas of temperature adjustmemt：
μ in formulat SST k-ωFor the turbulent viscosity of SST k- ω turbulence models；μt correctedFor the SSTk- ω turbulent flows after temperature adjustmemt
The turbulent viscosity of model；CTFor correction function, expression formula is：
In above formulaH (x) is He Wei Saden jump functions, Mτ0=0.1, f
(Mτ)=0 is indicated without compressible amendment；
MτFor turbulent Mach number, expression formula is：
Wherein a is local velocity of sound, and k is tubulence energy；
TgTo correct variable, expression formula is：
Wherein TtFor gas total temperature,For total temperature gradient absolute value,For turbulent flow length dimension, ω is than dissipative shock wave.
7. a kind of rocket motor tail injection stream emulation mode according to claim 6, it is characterised in that：In step (4)
The specific method of solution is iterated to rocket motor tail injection stream model using the SST k- ω turbulence models of temperature adjustmemt
For：The modified turbulent viscosity expression formula of temperature gradient is imported into the SST k- ω turbulence models in solver, is sprayed for tail
The numerical computations of jet stream.
8. a kind of rocket motor tail injection stream analogue system, it is characterised in that：Module, boundary are established including 3-D geometric model
Condition determining module, computation model establish module and emulation module；3-D geometric model establishes module foundation and rocket engine
The 3-D geometric model of the identical size of jet pipe；Boundary condition determining module to the 3-D geometric model of foundation carry out mesh generation,
Encryption, and determine boundary condition；Computation model establishes module and establishes computation model, it is ensured that tail injection stream process meets viscosity and receives
Dimension-stokes equation；Emulation module is established module using computation model and is iterated to rocket motor tail injection stream model
It solves, completes the simulation process of rocket motor tail injection stream.
9. a kind of rocket motor tail injection stream emulation terminal equipment, including memory, processor and it is stored in the storage
In device and the computer program that can run on the processor, it is characterised in that：The processor executes the computer journey
The step of the method as arbitrary such as claim 1-6 is realized when sequence.
10. a kind of computer readable storage medium, the computer-readable recording medium storage has computer program, feature to exist
In：The computer program is performed the step of realizing the method as arbitrary such as claim 1-6.
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| CN109840378A (en) * | 2019-01-31 | 2019-06-04 | 北京航天发射技术研究所 | Complicated launching condition rocket dynamic is taken off gas flow field grid model generation method |
| CN109858150A (en) * | 2019-01-31 | 2019-06-07 | 北京航天发射技术研究所 | The gas flow field grid model generation method of complicated lift-off technology condition |
| CN109858153A (en) * | 2019-01-31 | 2019-06-07 | 北京航天发射技术研究所 | The dirty solid coupled boundary condition of rocket launching combustion gas stream impact condition determines method |
| CN109871603A (en) * | 2019-01-31 | 2019-06-11 | 北京航天发射技术研究所 | The gas flow field predicting method of complicated lift-off technology condition |
| CN110427693A (en) * | 2019-07-30 | 2019-11-08 | 中国恩菲工程技术有限公司 | Fluid emulation calculation method in industrial reactor with spray gun |
| CN111553028A (en) * | 2020-04-02 | 2020-08-18 | 北京中科宇航技术有限公司 | Rocket engine nozzle swing simulation analysis method and system |
| CN112036018A (en) * | 2020-08-21 | 2020-12-04 | 西北工业大学 | Solid rocket engine tail flame flow field calculation method based on secondary development technology |
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| CN112597583A (en) * | 2020-12-11 | 2021-04-02 | 五邑大学 | Jet flow pneumatic drag reduction numerical simulation analysis method and device for high-speed train tail part |
| CN113656889A (en) * | 2021-08-02 | 2021-11-16 | 西安航天动力研究所 | Rocket engine system architecture model and static calculation model mapping system and method |
| CN114021404A (en) * | 2021-10-29 | 2022-02-08 | 大连海事大学 | Hydrogen turbulent flow deflagration simulation dynamic modeling method |
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| CN109858153A (en) * | 2019-01-31 | 2019-06-07 | 北京航天发射技术研究所 | The dirty solid coupled boundary condition of rocket launching combustion gas stream impact condition determines method |
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| CN112036018A (en) * | 2020-08-21 | 2020-12-04 | 西北工业大学 | Solid rocket engine tail flame flow field calculation method based on secondary development technology |
| CN112597583A (en) * | 2020-12-11 | 2021-04-02 | 五邑大学 | Jet flow pneumatic drag reduction numerical simulation analysis method and device for high-speed train tail part |
| CN112580222B (en) * | 2020-12-28 | 2024-02-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Spray pipe improvement method and system for solving tail cone ablation problem |
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| CN114021404A (en) * | 2021-10-29 | 2022-02-08 | 大连海事大学 | Hydrogen turbulent flow deflagration simulation dynamic modeling method |
| CN114021404B (en) * | 2021-10-29 | 2024-05-17 | 大连海事大学 | Method for simulating dynamic modeling of hydrogen turbulence deflagration |
| CN115034157A (en) * | 2022-06-15 | 2022-09-09 | 北京航空航天大学 | Method for predicting working characteristics of thixotropic propellant rocket engine |
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|---|---|
| CN108304684B (en) | 2021-06-11 |
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