CN112651083A - Detonation laser thruster analysis method based on FLUENT simulation - Google Patents
Detonation laser thruster analysis method based on FLUENT simulation Download PDFInfo
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Abstract
The invention discloses a detonation laser thruster analysis method based on FLUENT simulation, which comprises the following steps of: s1, determining a control equation according to the working process of the knock mode; s2, constructing a user-defined function UDF; s3, establishing a parabolic model, modeling by using Gambit software, selecting a grid type to divide a grid, setting boundary conditions, and outputting a case file; s4, opening FLUENT software, and importing the case file into the FLUENT software; s5, detecting grids and setting grid units; s6, importing a custom function UDF by FLUENT software; s7, selecting a correct radiation model, an energy model and a turbulence model, and setting material properties and flow field pressure; s8, setting a moving grid; s9, selecting a solving method, and determining solving precision; s10, initializing a boundary, setting iteration parameters and calculating; s11, look at residual map, velocity, pressure and temperature map. The invention discusses the change reason of the thrust in the laser propelling process by using FLUENT simulation software, and can ensure the stable speed in the rocket flying process.
Description
Technical Field
The invention relates to the technical field of laser propulsion, in particular to a detonation laser thruster analysis method based on FLUENT simulation.
Background
The propulsion technology is the core technology of a space carrier, most of the existing space propulsion devices are liquid or solid rocket engines, and the existing space propulsion devices have the common point that heat energy generated by chemical reaction is converted into jet kinetic energy through a jet pipe, and thrust is generated by utilizing the recoil action. Research and practice have shown that for conventional chemical rocket engines, the specific impulse of the engine does not exceed 5000m/s due to the limitations of combustion chamber temperature and combustion product molecular weight. In order to improve the specific impulse, various non-chemical propulsion modes are researched, such as electric propulsion, nuclear energy propulsion, laser propulsion and the like, and an electric propulsion system can obtain high specific impulse but has low thrust; the nuclear propulsion can obtain great thrust and high specific impulse, but the propellant is toxic and has pollution, and large energy equipment needs to be carried; the laser propulsion system forms high-temperature and high-pressure plasma by focusing laser breakdown working media, the plasma is ejected out from the spray pipe to generate recoil force on the engine, the working media of the laser propulsion system are separated from energy, high-energy laser transmitted from a long distance provides energy required by propulsion, and high specific impulse and thrust can be obtained. Aiming at the wide application prospect of the laser propulsion system, an analysis platform aiming at the laser propulsion process needs to be provided urgently, and convenience is provided for the process research of laser propulsion.
Disclosure of Invention
The invention aims to provide a detonation laser thruster analysis method based on FLUENT simulation, which is characterized in that dynamic mesh modeling is applied, a user-defined function UDF is constructed, and the variation of thrust in the detonation laser propulsion process is researched by simulating by utilizing FLUENT software.
In order to achieve the purpose, the invention provides the following scheme:
a detonation laser thruster analysis method based on FLUENT simulation comprises the following steps:
s1, determining a control equation according to a laser wave absorption stage and a subsequent shock wave attenuation stage in the working process of the detonation mode;
s2, constructing a user-defined function UDF for laser energy setting, dynamic boundary setting and plasma parameter adjustment in the FLUENT calculation process;
s3, establishing a parabolic model, modeling by using Gambit software, selecting a grid type to divide a grid, setting boundary conditions, and outputting a case file;
s4, opening FLUENT software, and importing the case file into the FLUENT software;
s5, detecting the grids, checking whether the divided grids are correct and setting grid units;
s6, importing a custom function UDF by FLUENT software;
s7, selecting a correct radiation model, an energy model and a turbulence model, and setting material properties, flow field pressure and temperature;
s8, in FLUENT, performing dynamic grid calculation, selecting a dynamic grid calculation module, and setting the overall calculation parameters and modes of the dynamic grid;
s9, selecting a solving method, and determining solving precision;
s10, initializing a boundary, setting iteration parameters, and calculating by using a FLUENT solver;
s11, look at residual map, velocity, pressure and temperature map.
Optionally, the control equation in step S1 specifically includes:
the corresponding heat flow is also simplified to:
in the formula, U is a conservation variable vector, E, F is convection flux in x and r directions under a cylindrical coordinate system, Ev and Fv are respectively convection flux in x and r directions, G, Gv is a source item generated by adopting the cylindrical coordinate system for an unbonded part and a bonded part, W is a mass and energy source item caused by a physicochemical process, and q isx、qrTotal and vibrational heat flow, q, respectivelynCombining the total heat conduction and diffusion heat flows after each internal energy mode for the heat flow q, wherein rho is the total density of the mixed gas, p is the pressure of the mixed gas, and u and v are two coordinates respectivelyThe velocity component in the direction, H is the enthalpy per unit mass of the mixed gas, and τ is the stress tensor.
Optionally, a custom function UDF is constructed in step S2, and is used for laser energy setting, dynamic boundary setting, and plasma parameter adjustment in the FLUENT calculation process, which specifically includes:
injecting laser energy: the instantaneous energy injection model is adopted, plasma ionization is complete and no energy loss exists, laser pulse energy is completely absorbed by the plasma with certain deposition efficiency, the shape of the plasma is a sphere, and if the radius is r, the formula is obtained:
calculating a moving boundary: when the flexible boundary calculation is carried out, a dynamic grid calculation module needs to be selected, and the DEFINE _ CG _ MOTION macro in the UDF is used for writing and realizing functions;
implementation of plasma equation: the method comprises the steps of modifying physical quantities of a flow field and calculating integration by utilizing a general solution macro DEFINE _ ADJUST in FLUENT, wherein DEFINE _ ADJUST mainly integrates the whole flow field, then the boundary is adjusted by analyzing a calculation result, and the macro defined by the function needs to be called for each iteration of each step or each solution of a transport equation.
Optionally, the grid unit in step S5 is mm, the flow field pressure in step S7 is 1atm, and the temperature is 298.15K.
Optionally, in step S8, the dynamic mesh calculation is performed in FLUENT, a dynamic mesh calculation module is selected, and the dynamic mesh overall calculation parameters and modes are set, which specifically includes:
processing the propeller as a dynamic boundary by using a dynamic mesh module provided by FLUENT, calling UDF to read flow field information when the calculation of each time step is finished in the calculation, and calculating the speed obtained by the propeller according to the force borne by the wall surface;
when the moving grid is selected for calculation and a boundary motion file is input, the required motion boundary type and motion boundary correspond to the motion boundary condition, so that a moving grid area is selected through a Setup-dynamic mesh-Create/Edit-dynamic mesh command;
for a rigid motion boundary, selecting a RigidBody option, wherein motion attributes and grid options need to be explained;
for the deformed boundary, a Deforming option is selected, and a geometric definition and a grid option need to be explained.
According to the specific steps provided by the invention, the invention discloses the following technical effects: according to the detonation laser thruster analysis method based on FLUENT simulation, the change reason of the turning point of the thrust in the laser propelling process is discussed by utilizing FLUENT simulation software under the traditional parabolic detonation model, and corresponding gas can be adopted in the rocket launching process according to the change of the thrust in the laser propelling process, so that the impulse can be effectively prevented from rapidly dropping along with the rising of the rocket height, and the speed stability in the rocket flying process is ensured.
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In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a flow chart of a flow field calculation of a detonation laser thruster analysis method based on FLUENT simulation;
FIG. 2 is a flow field pressure diagram of a thrust turning point of a detonation laser thruster analysis method based on FLUENT simulation;
FIG. 3 is a pressure diagram of a thrust turning point two-flow field of a detonation laser thruster analysis method based on FLUENT simulation;
FIG. 4 is a three-flow field pressure diagram of a thrust turning point of the detonation laser thruster analysis method based on FLUENT simulation.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide a detonation laser thruster analysis method based on FLUENT simulation, which is characterized in that dynamic mesh modeling is applied, a user-defined function UDF is constructed, and the variation of thrust in the detonation laser propulsion process is researched by simulating by utilizing FLUENT software.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
The invention provides a knocking laser thruster analysis method based on FLUENT simulation, which comprises the following specific steps of:
s1, determining a control equation according to a laser wave absorption stage and a subsequent shock wave attenuation stage in the working process of the detonation mode;
the detonation mode working process is a typical abnormal process and comprises a laser absorption wave stage and a subsequent shock wave attenuation stage; for the laser absorption wave stage, due to the existence of the high-speed developed laser supporting detonation wave or combustion wave, thermodynamic non-equilibrium and chemical non-equilibrium factors need to be considered, at the moment, the control equation system keeps a complete form, and each flux also keeps unchanged:
for the subsequent shock wave attenuation stage, after the laser pulse is finished, the laser absorbs an energy source item, simultaneously, thermodynamic imbalance and chemical imbalance are reduced to a secondary position, at the moment, the gas flow state is chemical equilibrium and thermodynamic equilibrium, a control equation set is an axial symmetry flow equation considering the characteristics of high-temperature real gas, and each vector becomes:
the corresponding heat flow is also simplified to:
in the formula, U is a conservation variable vector, E, F is convection flux in x and r directions under a cylindrical coordinate system, Ev and Fv are respectively convection flux in x and r directions, G, Gv is a source item generated by adopting the cylindrical coordinate system for an unbonded part and a bonded part, W is a mass and energy source item caused by a physicochemical process, and q isxQr total and vibrational heat flows, qnCombining total heat conduction and diffusion heat flows of all internal energy modes for a heat flow q, wherein rho is the total density of the mixed gas, p is the pressure of the mixed gas, u and v are velocity components in two coordinate directions respectively, H is the enthalpy of the mixed gas with unit mass, and tau is the stress tensor;
s2, constructing a custom function UDF for laser energy setting, dynamic boundary setting and plasma parameter adjustment in the FLUENT calculation process, wherein the custom function UDF specifically comprises the following steps: a laser energy injection program, a motion boundary setting program and a plasma equation realization program;
UDF (user defined functions) is written in C language, can be loaded into FLUENT in a compiling or interpreting mode, and can be used for controlling some model parameters or calculation processes in the FLUENT calculation process; the UDF can realize more functions, and the laser energy injection, the dynamic boundary calculation and the plasma equation realization are realized by mainly utilizing the UDF;
laser energy injection procedure: DEFINE _ SOURCE in UDF is used to DEFINE various SOURCE terms in FLUENT's solution for transport equations, including: continuity, momentum equation, k, e, energy and component mass fractions, etc.; the invention mainly compiles the function to realize the injection of laser energy, and the specific format is as follows: DEFINE _ SOURCE (name, c, t, dS, eqn); the laser injection model mainly adopts an instantaneous energy injection model, namely, plasma is completely ionized and has no energy loss, laser pulse energy is completely absorbed by the plasma with certain deposition efficiency, the shape of the plasma is a sphere, and if the radius is r, a formula can be obtained:
here, the energy conversion efficiency is η 40%;
motion boundary setting program: when the floating grid computing is to be performed, a moving grid computing module needs to be selected, and a DEFINE _ CG _ MOTION macro in the UDF is used for writing and realizing functions, wherein the specific format is as follows: DEFINE _ CG _ MOTION (name, dt, vel, omega, time, dtime);
implementation procedure of plasma equation: the method comprises the following steps of modifying physical quantities of a flow field and calculating products by utilizing a general solution macro DEFINE _ ADJUST in FLUENT, wherein DEFINE _ ADJUST mainly integrates the whole flow field, then the boundary is adjusted by analyzing a calculation result, the macro defined by the function needs to be called for each iteration of each step or each solution of a transport equation, and the macro format is as follows: DEFINE _ ADJUST (name, d);
s3, establishing a parabolic model, modeling by using Gambit software, selecting a grid type to divide a grid, setting boundary conditions, and outputting a case file;
s4, opening FLUENT software, and importing the case file into the FLUENT software;
s5, detecting the grids, checking whether the divided grids are correct and setting the grid unit as mm;
s6, importing a custom function UDF by FLUENT software;
s7, selecting a correct radiation model, an energy model and a turbulence model, setting material properties, setting the flow field pressure to be 1atm and the temperature to be 298.15K;
s8, in FLUENT, performing dynamic grid calculation, selecting a dynamic grid calculation module, and setting the overall calculation parameters and modes of the dynamic grid;
in FLUENT, a dynamic mesh model is generally used for simulating the motion situation of a basin shape changing along with time caused by the motion of a basin boundary; generally this flow can be divided into two cases: the linear velocity or the angular velocity of the object changing along with time can move in a determined form, or an undetermined motion (the linear velocity or the angular velocity is obtained according to the stress balance of the gravity center of the object), the motion condition of each step is calculated according to the motion condition of the previous step, the body grid needs to be updated in each step, and the motion is automatically completed by FLUENT according to the new position of the boundary condition of each step;
in FLUENT, a dynamic grid computing module needs to be selected for dynamic grid computing, and overall computing parameters and modes of the dynamic grid are set; processing the propeller as a moving boundary by using a dynamic mesh module provided by FLUENT; when the calculation of each time step in the calculation is finished, calling the UDF to read flow field information, calculating the speed obtained by the propeller according to the force borne by the wall surface, and selecting a motion grid calculation and inputting a boundary motion file, wherein the type and the motion boundary of the motion boundary required correspond to motion boundary conditions, so that a motion grid area is selected through a Setup-dynamic mesh-Create/Edit-dynamic mesh command; for a rigid motion boundary, selecting a RigidBlock option to explain motion attributes and grid options, and for a deformation boundary, selecting a Deforming option to explain geometric definitions and grid options;
s9, selecting a solving method, and determining solving precision;
s10, initializing a boundary, setting iteration parameters, and calculating by using a FLUENT solver;
s11, checking a residual error map, a speed map, a pressure map and a temperature map;
as shown in fig. 2 to 4, the main reasons for analyzing the existence of three turning points are: the turning point is that the high-pressure air mass acts on the wall surface to achieve the maximum thrust, and the maximum thrust is caused by the high pressure behind the reflected wave after the shock wave reaches the top end of the thruster and then is reflected; the second turning point marks that the high-pressure air mass moves because the flow field changes gradually, and the low-pressure area begins to leave the top end of the thruster and moves to the side wall; the third turning point is that the shock wave gradually leaves the thruster, part of high-pressure air mass does not act on the thruster, and the thrust is gradually zero.
According to the detonation laser thruster analysis method based on FLUENT simulation, the change reason of the turning point of the thrust in the laser propelling process is discussed by utilizing FLUENT simulation software under the traditional parabolic detonation model, and corresponding gas can be adopted in the rocket launching process according to the change of the thrust in the laser propelling process, so that the impulse can be effectively prevented from rapidly dropping along with the rising of the rocket height, and the speed stability in the rocket flying process is ensured.
The principles and embodiments of the present invention have been described herein using specific examples, which are provided only to help understand the method and the core concept of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (5)
1. A detonation laser thruster analysis method based on FLUENT simulation is characterized by comprising the following steps:
s1, determining a control equation according to a laser wave absorption stage and a subsequent shock wave attenuation stage in the working process of the detonation mode;
s2, constructing a user-defined function UDF for laser energy setting, dynamic boundary setting and plasma parameter adjustment in the FLUENT calculation process;
s3, establishing a parabolic model, modeling by using Gambit software, selecting a grid type to divide a grid, setting boundary conditions, and outputting a case file;
s4, opening FLUENT software, and importing the case file into the FLUENT software;
s5, detecting the grids, checking whether the divided grids are correct and setting grid units;
s6, importing a custom function UDF by FLUENT software;
s7, selecting a correct radiation model, an energy model and a turbulence model, and setting material properties, flow field pressure and temperature;
s8, in FLUENT, performing dynamic grid calculation, selecting a dynamic grid calculation module, and setting the overall calculation parameters and modes of the dynamic grid;
s9, selecting a solving method, and determining solving precision;
s10, initializing a boundary, setting iteration parameters, and calculating by using a FLUENT solver;
s11, look at residual map, velocity, pressure and temperature map.
2. The method for analyzing the knocking laser thruster based on FLUENT simulation as claimed in claim 1, wherein the control equation in the step S1 specifically comprises:
the corresponding heat flow is also simplified to:
in the formula, U is a conservation variable vector, E, F is convection flux in x and r directions under a cylindrical coordinate system, Ev and Fv are respectively convection flux in x and r directions, G, Gv is a source item generated by adopting the cylindrical coordinate system for an unbonded part and a bonded part, W is a mass and energy source item caused by a physicochemical process, and q isx、qrTotal and vibrational heat flow, q, respectivelynAnd combining the total heat conduction and diffusion heat flow of each internal energy mode for the heat flow q, wherein rho is the total density of the mixed gas, p is the pressure of the mixed gas, u and v are velocity components in two coordinate directions respectively, H is the enthalpy of the mixed gas with unit mass, and tau is the stress tensor.
3. The method for analyzing a knocking laser thruster based on FLUENT simulation of claim 1, wherein the step S2 is to construct a custom function UDF for laser energy setting, dynamic boundary setting and plasma parameter adjustment in FLUENT calculation, which specifically comprises:
injecting laser energy: the instantaneous energy injection model is adopted, plasma ionization is complete and no energy loss exists, laser pulse energy is completely absorbed by the plasma with certain deposition efficiency, the shape of the plasma is a sphere, and if the radius is r, the formula is obtained:
wherein, the energy conversion efficiency is eta which is 40 percent;
calculating a moving boundary: when the flexible boundary calculation is carried out, a dynamic grid calculation module needs to be selected, and the DEFINE _ CG _ MOTION macro in the UDF is used for writing and realizing functions;
implementation of plasma equation: the method comprises the steps of modifying physical quantities of a flow field and calculating integration by utilizing a general solution macro DEFINE _ ADJUST in FLUENT, wherein DEFINE _ ADJUST mainly integrates the whole flow field, then the boundary is adjusted by analyzing a calculation result, and the macro defined by the function needs to be called for each iteration of each step or each solution of a transport equation.
4. The FLUENT simulation-based knocking laser thruster analysis method according to claim 1, wherein the grid unit in the step S5 is mm, the flow field pressure in the step S7 is 1atm, and the temperature is 298.15K.
5. The method for analyzing a knocking laser thruster based on FLUENT simulation of claim 1, wherein the step S8 is to perform dynamic grid calculation in FLUENT, select a dynamic grid calculation module, and set the overall calculation parameters and modes of the dynamic grid, specifically comprising:
processing the propeller as a Dynamic boundary by using a Dynamic Mesh module provided by FLUENT, calling UDF to read flow field information when the calculation of each time step is finished in the calculation, and calculating the speed obtained by the propeller according to the force borne by the wall surface;
when the moving grid is selected for calculation and a boundary motion file is input, the required motion boundary type and motion boundary correspond to the motion boundary condition, so that a moving grid area is selected through a Setup-Dynamic Mesh-Create/Edit-Dynamic Mesh command;
for a Rigid motion boundary, selecting a Rigid Body option, wherein motion attributes and grid options need to be explained;
for the deformed boundary, a Deforming option is selected, and a geometric definition and a grid option need to be explained.
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