CN103294855B

CN103294855B - Solid propellant plume characteristic virtual test and plume data structure gridding method

Info

Publication number: CN103294855B
Application number: CN201310180349.3A
Authority: CN
Inventors: 赵凤起; 肖川; 李猛; 徐司雨; 罗阳; 向红军; 王宏; 梁勇
Original assignee: Xian Modern Chemistry Research Institute
Current assignee: Xian Modern Chemistry Research Institute
Priority date: 2013-05-15
Filing date: 2013-05-15
Publication date: 2016-03-09
Anticipated expiration: 2033-05-15
Also published as: CN103294855A

Abstract

The invention discloses a kind of solid propellant plume characteristic virtual test and plume data structure gridding method, comprise step: one, Initial parameter sets and storage; Two, energy response parameter calculates; Three, engine plume calculates; Four, gas-phase product plume data structure gridding process, process is as follows: spout area vapor phase product stream field data reads, build Structure Network trrellis diagram gentle phase product plume data structure gridding process; Five, condensed phase product plume data structure gridding process, process is as follows: Initial parameter sets, particle trajectory digital independent, nozzle entry place number of grid obtain and each grid up-and-down boundary is determined and condensed phase product plume data structure gridding process.The inventive method step is simple, reasonable in design and realization is convenient, result of use is good, can complete plume characteristic virtual test easy, fast and the flow field data based on unstrctured grid can be converted to the corresponding data of structure based grid so that subsequent calculations uses.

Description

Solid propellant plume characteristic virtual test and plume data structure gridding method

Technical field

The invention belongs to solid propellant plume technical field of data processing, especially relate to a kind of solid propellant plume characteristic virtual test and plume data structure gridding method.

Background technology

Along with the development of mechanization, informationization technology, Modern weapon system more and more adopts radar, photoelectricity etc. from motion tracking, control and guidance means, the aspect such as automaticity, attack precision of armament systems is significantly improved, and improves the fighting efficiency playing arrow armament systems greatly.But meanwhile, the cigarette flame problem harmfulness played in arrow arm discharge and carry process manifests day by day, very large to weapon system, intellectuality, stealthyization performance impact, to armament systems fast, precision strike, the function such as stealthy cause serious adverse effect, even become bring into normal play usefulness, new equipment of my army's bullet arrow weapon of restriction and ordered goods and the major technology bottleneck of new-type weapon and equipment development.Especially in recent years, occur in heavy antitank missile development process that propellant loading smog blocks the problem of guidance signal, dealing with problems, it is huge to expend.

Solid propellant is the transmitting energy playing arrow armament systems, and its low signature performance is the key factor ensureing that armament systems battlefield mission completes.Plume is the penniform high-speed and high-temperature gas-flow ejected from rocket tube, rocket plume is that a kind of Gas Molecular Density is large, electron density and all very high weak plasma of electron collision frequency, can interact between itself and radar microwave, microwave signal power is greatly reduced, affects the guidance of guided missile.And the space occupied by fluid motion of the plume penniform high-speed and high-temperature gas-flow that to be rocket tube eject.For evaluating solid propellant plume characteristic, some developed countries all establish dependence test appraisal procedure in the world, have built various experiment test facility and have detected solid propellant characteristic signal performance and characterize.On the domestic basis studying external test facilities, setting up and a set of having there is the low cost of independent intellectual property rights, manageable solid propellant plume Characteristics Detection system.But in low characteristic signal propellant development and evaluation procedure, deal with problems and need the manpower and materials of at substantial, lead time significantly extends, and thus brings huge economic loss and political fallout, nowadays carries out Fast Evaluation in the urgent need to virtual test to solid propellant correlated performance.And virtual test resolves by means of the high speed of computing machine, by actual tests requirement, simulation test is carried out to the mathematical model based on propellant combustion and products of combustion flowing, not only can substitute traditional test (as some limiting conditions) as the preliminary preparation of actual experimental or to a certain extent; And can significantly reduce actual experimental number of times, reduce testing expenses, shorten the test period; Meanwhile, there is good interactivity, various Test Information is fed back in time; In addition, virtual test is by the restriction of meteorological condition, place, time and number of times, and process of the test can conveniently realize playback, reproduction and repetition.

At present, to propellant combustion and products of combustion flowing mathematical model carry out simulation test time, usually FLUENT software is all adopted to simulate the plume after SOLID PROPELLANT COMBUSTION, and after adopting FLUENT software to complete the plume calculating of designed solid propellant, just automatically can export * .out file and calculate and photoelectric characteristic calculating for microwave attenuation calculating, infrared radiation.But be flow field data based on unstrctured grid due to what preserve in FLUENT software saving file * _ tec.dat, and contain jet pipe region and spout area.Because in the subsequent calculations such as microwave attenuation calculating, infrared radiation calculating and photoelectric characteristic calculating for spout area, thus need flow field data that after being calculated by FLUENT software, institute obtains spout area to extract and carry out structured grid conversion, and convert the corresponding data of structure based grid to so that subsequent calculations use.In addition, because FLUENT can only preserve particle trajectory historical data, and infrared radiation calculates and photoelectric characteristic calculating it is desirable that the number density of different-diameter particle and temperature, thus also need by after FLUENT software is calculated obtain spout area flow field data process, and corresponding number density and the temperature drawing in spout area different-diameter particle in each structured grid on each particle trajectory.

Summary of the invention

Technical matters to be solved by this invention is for above-mentioned deficiency of the prior art, a kind of solid propellant plume characteristic virtual test and plume data structure gridding method are provided, its method step is simple, reasonable in design and realization is convenient, result of use is good, can complete solid propellant plume characteristic virtual test easy, fast and the flow field data based on unstrctured grid can be converted to the corresponding data of structure based grid so that subsequent calculations uses.

For solving the problems of the technologies described above, the technical solution used in the present invention is: a kind of solid propellant plume characteristic virtual test and plume data structure gridding method, is characterized in that the method comprises the following steps:

Step one, Initial parameter sets and storage:

First, by the parameter input unit connected with data processor, the component information of the component quantity N that the designed solid propellant of input preparation is used and each component, and inputted synchronizing information is stored in the data storage cell that connects with described data processor; Wherein, the component information of each component includes chemical formula and quality proportioning m _i, i is positive integer, and i=1,2 ..., N; Wherein, N is the quantity of the designed solid propellant component used of preparation; 0 < m _i< 100, m ₁+ m ₂+ ... + m _n=100, N>=2;

Afterwards, by described parameter input unit in the products of combustion database set up in advance, all products of combustion produced after selecting designed SOLID PROPELLANT COMBUSTION; The attribute information of multiple products of combustion is stored in described products of combustion database; Wherein, the attribute information of each products of combustion includes chemical formula, relative molecular mass and phase, and wherein phase is gas phase or condensed phase; Simultaneously, by described parameter input unit to after designed SOLID PROPELLANT COMBUSTION produce products of combustion the quantity Q of quantity m and condensed phase product set, and the products of combustion produced after designed SOLID PROPELLANT COMBUSTION comprises Q condensed phase product and (m-Q) individual gas-phase product, wherein m and Q is positive integer, and Q>=1; As Q=1, after designed SOLID PROPELLANT COMBUSTION the condensed phase product produced in products of combustion be Al ₂o ₃particle;

Step 2, energy response parameter calculate, and its computation process is as follows:

Step 201, modeling: according to principle of minimum free energy, set up minimum free energy mathematical model and chamber temperature computation model;

Step 202, equilibrium composition calculate: the minimum free energy mathematical model set up in described data processor invocation step 201, and initial parameter set in integrating step one, calculate the products of combustion equilibrium composition after designed SOLID PROPELLANT COMBUSTION, and the equilibrium composition of m products of combustion that the products of combustion equilibrium composition calculated produces after comprising designed SOLID PROPELLANT COMBUSTION;

Step 203, adiabatic combustion temperature calculate: the chamber temperature computation model set up in described data processor invocation step 201, is in adiabatic combustion temperature during chemistry balance state after calculating designed SOLID PROPELLANT COMBUSTION;

Step 3, plume calculate, and its computation process is as follows:

Step 301, jet pipe geometric parameter and jet flow computational fields range set: the geometric parameter of engine jet pipe and jet flow computational fields scope are set by described parameter input unit; Wherein, the geometric parameter of engine jet pipe includes port radius r ₁, throat radius r ₂, exit radius r ₃, converging portion length d1, throat cylindrical section length d2, angle of flare α and expansion segment length d3, wherein entry radius r ₁for the entry radius of engine jet pipe, throat radius r ₂for the throat radius of engine jet pipe, exit radius r ₃for the exit radius of engine jet pipe, converging portion length d1 is the length of engine jet pipe entrance to nozzle throat front end, throat cylindrical section length d2 is the throat length of engine jet pipe, angle of flare α is the angle between the wall of engine jet pipe expansion segment and its axis, and expansion segment length d3 is the length of engine jet pipe throat end to nozzle exit; Jet flow computational fields scope comprises jet flow axial length x _mwith jet flow radical length y _m, wherein jet flow axial length x _mfor engine jet pipe exports to the length d4 of jet flow lower exit, jet flow radical length y _mfor engine jet pipe axis is to the length of the radial outer boundary of jet flow;

Step 302, combustion chamber operational setting parameter: first, by described parameter input unit to pressure P in the firing chamber of engine _c, environmental pressure and environment temperature T _ringset respectively; Afterwards, then to products of combustion equilibrium composition set; Then, by described parameter input unit to after designed SOLID PROPELLANT COMBUSTION produce Al ₂o ₃the mean grain size D of particle _nset;

When products of combustion equilibrium composition is set, the equilibrium composition of (m-Q) the individual gas-phase product produced after set products of combustion equilibrium composition comprises designed SOLID PROPELLANT COMBUSTION and Al ₂o ₃the equilibrium composition of particle; After the equilibrium composition of set (m-Q) individual gas-phase product is respectively the designed SOLID PROPELLANT COMBUSTION calculated in step 202 produce the equilibrium composition of (m-Q) individual gas-phase product; When in step one during Q=1, set Al ₂o ₃the equilibrium composition of particle is produced Al by after the designed SOLID PROPELLANT COMBUSTION that calculates in step 202 ₂o ₃the equilibrium composition of particle; When in step one during Q > 1, set Al ₂o ₃the equilibrium composition of particle by after the designed SOLID PROPELLANT COMBUSTION that calculates in step 202 the equilibrium composition sum n of generation Q condensed phase product _{condensed phase};

Step 303, engine plume calculate: first, according to jet pipe geometric parameter set in step 301 and jet flow computational fields scope, adopt described data processor to set up and the two-dimensional axial symmetric model of numerical evaluation is carried out to plume inside and outside described engine jet pipe; Afterwards, described data processor calls CFD front processor, generate the plume computational fields grid chart of designed solid propellant, and described CFD front processor is GAMBIT software; Then, described data processor calls FLUENT software, and the combustion chamber operational parameter set by jet pipe geometric parameter set in the energy response parameter calculated in integrating step two, step 301 and jet flow computational fields scope and step 302, plume calculating is carried out to designed solid propellant, and automatically exports plume result of calculation; Wherein, the plume result of calculation exported comprises gas-phase product plume result of calculation and condensed phase product plume result of calculation;

Step 4, gas-phase product plume data structure gridding process, its processing procedure is as follows:

Step 401, spout area vapor phase product stream field data read: the flow field data reading all unstrctured grid nodes in the spout area of designed solid propellant in the gas-phase product plume result of calculation adopting described data processor to export from step 303; Described spout area is the rectangular area at described engine jet pipe outlet rear;

On step 402, axial coordinate axle, unstrctured grid point extracts: adopt described data processor from all unstrctured grid nodes spout area described in step 401, extract all unstrctured grid points be positioned on axial coordinate axle, the unstrctured grid point total quantity be positioned on axial coordinate axle extracted is N _x; Wherein, axial coordinate axle is the abscissa axis at the central axis place of described engine jet pipe, the radial coordinate y being positioned at the unstrctured grid point on axial coordinate axle extracted in this step _h=0 and its axial coordinate x _h>=0, wherein h is positive integer, and h=1,2 ..., N _x;

On step 403, radial coordinate axle, unstrctured grid point extracts: adopt described data processor from all unstrctured grid nodes spout area described in step 401, extract all unstrctured grid points be positioned on radial coordinate axle, the unstrctured grid point total quantity be positioned on radial coordinate axle extracted in this step is N _{y goes out}; Wherein, radial coordinate axle is the axis of ordinates at place, described engine jet pipe exit and the axial coordinate value in engine jet pipe exit is 0, is positioned at the axial coordinate x of the unstrctured grid point on radial coordinate axle _k1=0 and its radial coordinate y _k1>=0, wherein k1 is positive integer, and k1=1,2 ..., N _{y goes out};

Step 404, structure Structure Network trrellis diagram: by N _xbar straight line x=x _hand N _{y goes out}bar straight line y=y _k1after orthogonal, construct one and comprise (N _x-1) × (N _{y goes out}-1) the Structure Network trrellis diagram of individual rectangular node;

Step 405, gas-phase product plume data structure gridding process: adopt described data processor to carry out assignment again respectively to the vapor phase product stream field data on four summits of each rectangular node in Structure Network trrellis diagram constructed in step 404; In all rectangular nodes, assignment method is all identical again for the vapor phase product stream field data on each summit, wherein for when in constructed Structure Network trrellis diagram, the vapor phase product stream field data on arbitrary summit of any one rectangular node carries out again assignment, described data processor is first found out and is assigned the nearest unstrctured grid node of vertex distance with current from all unstrctured grid nodes spout area described in step 401, and the vapor phase product stream field data of found out unstrctured grid node is assigned to the current summit be assigned;

Step 5, condensed phase product plume data structure gridding process: described data processor to utilize in step 404 constructed Structure Network trrellis diagram to carry out Structure Network respectively to the particle trajectory data of M different-grain diameter particle and to format process, and process is as follows:

Step 501, Structure Network are formatted process Initial parameter sets: adopt described parameter input unit to the particle diameter D of the value of M and M different-grain diameter particle _nrset respectively; Wherein, r is positive integer, and r=1,2 ..., M; M is the different-grain diameter number of particles need carrying out processing;

Step 502, particle trajectory digital independent: all particle trajectory data reading designed solid propellant in the condensed phase product plume result of calculation adopting described data processor to export from step 303; Wherein, the condensed phase product plume result of calculation read comprises mass particle file, particle temperature with the file of trail change, the file of particle diameter with trail change and the time step file of particle trajectory;

Step 503, engine jet pipe entrance rectangular node quantity obtain and the up-and-down boundary of each nozzle entry rectangular node is determined: first, read the flow field data of all unstrctured grid nodes in the engine jet pipe region of designed solid propellant in the gas-phase product plume result of calculation adopting described data processor to export from step 303; Afterwards, adopt described data processor from all unstrctured grid nodes read engine jet pipe region, extract all unstrctured grid nodes be positioned on straight line x=-Δ d, and the unstrctured grid point total quantity be positioned on straight line x=-Δ d extracted is N _{y enters}; Wherein, the axial coordinate x of the unstrctured grid node on straight line x=-Δ d is positioned at _k2=-Δ d and its radial coordinate y _k2>=0, wherein k2 is positive integer, and k2=1,2 ..., N _{y enters}; Δ d=d1+d2+d3; The nozzle entry rectangular node quantity obtained is (N _{y enters}-1) individual, the up-and-down boundary of each nozzle entry rectangular node is respectively two neighbouring straight line y=y _k2;

Step 504, condensed phase product plume data structure gridding process: adopt data processor with (N described in step 503 _{y enters}-1) individual nozzle entry rectangular node carries out particle trajectory Structure Network respectively as starting mesh and to format process, and it is all identical that each nozzle entry rectangular node carries out the format process of process of particle trajectory Structure Network as starting mesh; And, carry out using any one nozzle entry rectangular node as starting mesh particle trajectory Structure Network format process time, all to format process to carrying out Structure Network using current handled nozzle entry rectangular node respectively as M different-grain diameter particle trajectory of starting mesh, and the Structure Network of M different-grain diameter particle trajectory is formatted, disposal route is all identical; Wherein, to arbitrary particle trajectory in M different-grain diameter particle trajectory carry out Structure Network format process time, calculate the particle trajectory gridded data of current handled particle trajectory in all rectangular nodes of described Structure Network trrellis diagram midway warp respectively, and the particle trajectory gridded data in each rectangular node includes mass particle, population density, average particle diameter and particle medial temperature.

Above-mentioned solid propellant plume characteristic virtual test and plume data structure gridding method, it is characterized in that: when the particle trajectory gridded data of current handled particle trajectory in all rectangular nodes of described Structure Network trrellis diagram midway warp being calculated in step 504, according to institute by way of rectangular node installation position tandem by first extremely after calculate.

Above-mentioned solid propellant plume characteristic virtual test and plume data structure gridding method, is characterized in that: M=8 in step 501, and the particle diameter D of 8 different-grain diameter particles _nrbe respectively D _n1, D _n2, D _n3, D _n4, D _n5, D _n6, D _n7and D _n8, wherein, D _n1< D _n2< D _n3< D _n4< D _n< D _n5< D _n6< D _n7< D _n8, wherein, D _nby being produced Al after SOLID PROPELLANT COMBUSTION designed by set in step 302 ₂o ₃the mean grain size of particle.

Above-mentioned solid propellant plume characteristic virtual test and plume data structure gridding method, is characterized in that: in step 303 to designed solid propellant carry out plume calculate time, adopt the governing equation of condensed phase product to be Lagrangian particle-trajectory model.

Above-mentioned solid propellant plume characteristic virtual test and plume data structure gridding method, is characterized in that: in step 504 to arbitrary particle trajectory in M different-grain diameter particle trajectory carry out Structure Network format process time, its processing procedure is as follows:

Step 5041, engine jet pipe entrance starting mesh are determined and mass particle flow rate calculate: the particle trajectory data finding out current handled particle trajectory in all particle trajectory data that described data processor reads in step 502, and according to the up-and-down boundary of determined each nozzle entry rectangular node in the radial coordinate of the engine jet pipe porch tracing point in found out particle trajectory data and step 503, the nozzle entry starting mesh of current handled particle trajectory is determined; Find out particle trajectory data and comprise mass particle file, particle temperature with the file of trail change, particle diameter with the data stored in the file of trail change and the time step file of particle trajectory;

After the nozzle entry starting mesh of current handled particle trajectory is determined, described data processor finds out the summit one of determined nozzle entry starting mesh and the vapor phase product stream field data on summit two, and finds out the density of gas phase ρ at summit one place in the vapor phase product stream field data on the summit one found out _g1with gas phase axial velocity u _g1, and in the vapor phase product stream field data on the summit two found out, find out the density of gas phase ρ at summit two place _g2with gas phase axial velocity u _g2, wherein summit one is the summit, upper left side of the nozzle entry starting mesh of current handled particle trajectory, and summit two is the summit, lower left of the nozzle entry starting mesh of current handled particle trajectory; Afterwards, described data processor is according to formula calculate the mass particle flow rate in the nozzle entry starting mesh of current handled particle trajectory; In formula, M is the different-grain diameter number of particles that need set in step 501 carry out processing; f _ptogfor condensed phase and gas phase flow rate ratio and when in step one during Q=1, the n in formula _xby being produced Al after SOLID PROPELLANT COMBUSTION designed by calculating in step 202 ₂o ₃the equilibrium composition of particle; And when in step one during Q > 1, the n in formula _xfor the n described in step 302 _{condensed phase}; for the gas phase flow rate in the nozzle entry starting mesh of current handled particle trajectory, and

\overset{\cdot}{m_{g}} = \frac{\overset{\cdot}{m_{g 1}} + \overset{\cdot}{m_{g 2}}}{2},

In formula wherein S _gridfor the area of the nozzle entry starting mesh of current handled particle trajectory;

Step 5042, engine jet pipe exit starting mesh are determined: described data processor according in step 5041 find out axial coordinate and the radial coordinate of each tracing point in the particle trajectory data of current handled particle trajectory, and Structure Network trrellis diagram constructed in integrating step 404, current handled particle trajectory is determined at the starting mesh in engine jet pipe exit;

Step 5043, particle trajectory Structure Network are formatted process: described data processor is according to Structure Network trrellis diagram constructed in step 404, and the determined current handled starting mesh of particle trajectory in engine jet pipe exit in the axial coordinate of each tracing point in the particle trajectory data found out in integrating step 5041 and radial coordinate and step 5042, find out current handled particle trajectory in described Structure Network trrellis diagram by way of all rectangular nodes, and corresponding calculate by way of each rectangular node in particle trajectory gridded data; And, current handled particle trajectory by way of all rectangular nodes in the computing method of particle trajectory gridded data all identical, for current handled particle trajectory by way of any one rectangular node, the computation process of its particle trajectory gridded data is as follows:

Step I, mass particle calculate: in the mass particle file of the current handled particle trajectory that described data processor is found out in step 5041, find out the current handled mass particle m of particle trajectory in engine jet pipe porch _grain, and the mass particle m in current calculated rectangular node _grid=m _grain;

Step II, population density calculate: described data processor is according to formula calculate the population density N in current calculated rectangular node _p; Dt is the residence time of current handled particle trajectory in current calculatings rectangular node, and dt is the time step sum of all tracing points of particle trajectory handled by current in current calculating rectangular node; In formula, for the mass particle flow rate in the nozzle entry starting mesh of current handled particle trajectory that calculates in step 5041;

Step III, average particle diameter and medial temperature: described data processor is respectively according to formula with calculate the average particle diameter D in current calculated rectangular node _pwith particle medial temperature T _p; In formula, k3 is positive integer, and k3=1,2 ..., K, wherein K is the tracing point total quantity of current handled particle trajectory in current calculating rectangular node, and D _pk3and T _pk3be respectively particle diameter and the particle temperature at kth 3 tracing point places in K tracing point; Dt is the residence time of current handled particle trajectory in current calculating rectangular node, dt _k3by the residence time of kth 3 tracing points in K tracing point in current calculating rectangular node;

Step IV, repeatedly repeat step I to step III, until calculate current handled particle trajectory by way of all rectangular nodes in particle trajectory gridded data;

Step 5044, repeatedly repeat step 5041 to step 5043, the processing procedure until the Structure Network completed using current handled nozzle entry rectangular node as M different-grain diameter particle trajectory of starting mesh is formatted;

Step 505, repeatedly repeat step 5041 to step 5044, until complete with (N _{y enters}-1) individual nozzle entry rectangular node to be formatted processing procedure as the particle trajectory Structure Network of starting mesh.

Above-mentioned solid propellant plume characteristic virtual test and plume data structure gridding method, is characterized in that: to the average particle diameter D in current calculated rectangular node in step III _pwith particle medial temperature T _pbefore calculating, first according to up-and-down boundary radial coordinate and the right boundary axial coordinate of current calculated rectangular node, and the axial coordinate of each tracing point in the particle trajectory data found out in integrating step 5041 and radial coordinate, the axial coordinate of the tracing point total quantity K of current handled particle trajectory in current calculated rectangular node and K tracing point and radial coordinate are determined respectively.

Above-mentioned solid propellant plume characteristic virtual test and plume data structure gridding method, it is characterized in that: when plume calculating being carried out to designed solid propellant in step 303, adopt the governing equation of gas-phase product to be turbulence model, and described turbulence model is the k-ε model of the correction of two equations.

Above-mentioned solid propellant plume characteristic virtual test and plume data structure gridding method, it is characterized in that: when products of combustion equilibrium composition being set in step 302, when in step one during Q=1, by the equilibrium composition of m products of combustion produced after SOLID PROPELLANT COMBUSTION designed by calculating in described parameter input unit respectively input step 202, or described data processor call parameters arranges the equilibrium composition of m the products of combustion produced after module transfers out the designed SOLID PROPELLANT COMBUSTION calculated in step 202 automatically; When in step one during Q > 1, first according to the equilibrium composition of m the products of combustion produced after SOLID PROPELLANT COMBUSTION designed by calculating in step 202, after calculating designed SOLID PROPELLANT COMBUSTION produce the equilibrium composition sum m of Q condensed phase product _{condensed phase}; Afterwards, equilibrium composition sum m is inputted respectively by described parameter input unit _{condensed phase}with calculate in step 202 designed by the equilibrium composition of (m-Q) individual gas-phase product that produces after SOLID PROPELLANT COMBUSTION, or described data processor call parameters arranges module and automatically transfers out the equilibrium composition sum m precalculating and draw _{condensed phase}with calculate in step 202 designed by the equilibrium composition of (m-Q) individual gas-phase product that produces after SOLID PROPELLANT COMBUSTION.

Above-mentioned solid propellant plume characteristic virtual test and plume data structure gridding method, it is characterized in that: after extracting all unstrctured grid points be positioned on axial coordinate axle in step 402, the extracted all unstrctured grid points be positioned on axial coordinate axle arrange according to axial coordinate order from small to large by described data processor, and mark from left to right on described axial coordinate axle; After extracting all unstrctured grid points be positioned on radial coordinate axle in step 403, the extracted all unstrctured grid points be positioned on radial coordinate axle arrange according to radial coordinate order from small to large by described data processor, and mark from the bottom to top on described radial coordinate axle.

Above-mentioned solid propellant plume characteristic virtual test and plume data structure gridding method, is characterized in that: the minimum free energy mathematical model set up in step 201 is in formula (1): j is positive integer, and j=1,2 ..., the kind of A, A chemical element contained by solid propellant; S is positive integer, and s=1,2 ..., m, m are the kind number of contained products of combustion when being in chemistry balance state after SOLID PROPELLANT COMBUSTION; wherein μ _sfor the chemical potential (KJ/mol) of s kind products of combustion inputted by described parameter input unit in advance, n _sthe molal quantity (mol/Kg) of contained s kind products of combustion during for being in chemistry balance state after 1000g SOLID PROPELLANT COMBUSTION and n _s>=0, a _sjfor the atomicity of jth kind chemical element contained in 1mol s kind products of combustion; b _jfor the atomicity of jth kind chemical element contained in 1000g solid propellant, π _jfor Lagrange multiplier;

The chamber temperature computation model set up is adiabatic temperature computation model, and the adiabatic temperature computation model set up is h in formula (2) _c1for adiabatic temperature T=T ₁time the enthalpy of 1000g products of combustion, H _c2for adiabatic temperature T=T ₂time the enthalpy of 1000g products of combustion, H _c1< H _p< H _c2, and H _c1and H _c2all according to formula calculate, wherein n _sthe molal quantity (mol/Kg) of contained s kind products of combustion during for being in chemistry balance state after 1000g SOLID PROPELLANT COMBUSTION, H _csfor the enthalpy of 1mol s kind products of combustion when adiabatic temperature is T, H _cs=RT (α _s1+ α _s2t/2+ α _s3t ²/ 3+ α _s4t ³/ 4+ α _s5t ⁴/ 5+ α _s6t ⁵/ 6), wherein, R is universal gas constant (Kgm/molK), T is adiabatic temperature, α _s1, α _s2, α _s3, α _s4, α _s5and α _s6for the Temperature Coefficients For Thermodyamic Function of s kind products of combustion inputted by described parameter input unit in advance; wherein M _ifor the relative molecular mass of preparation solid propellant i-th kind of component used, H _ifor the enthalpy of 1mol i-th kind of component inputted by described parameter input unit in advance, W _ifor the mass percent of preparation solid propellant i-th kind of component used.

The present invention compared with prior art has the following advantages:

1, method step simple, reasonable in design and realize convenient.

2, input cost is low and use easy and simple to handle, significantly simplify the formula development process of solid propellant, substantially reduces the formula development cycle, greatly reduce formula development cost.

3, in formula design of solid propellant process, only need input the component information of preparation solid propellant each component used, adopt data processor just automatically can carry out plume characteristic virtual test (namely carrying out plume analog computation to solid propellant) to designed solid propellant afterwards, and automatically can carry out Structure Network to plume result of calculation and to format process, and Structure Network is formatted after process, result can be utilized directly to carry out microwave attenuation calculating, the subsequent calculations such as infrared radiation calculating and photoelectric characteristic calculating, not only computation process is simple, and the accuracy of result of calculation is easy to ensure.Calculate until microwave attenuation, infrared radiation calculates or after photoelectric characteristic calculated, can adjust accordingly according to the formula of result of calculation to designed solid propellant, thus be that the formula Design of solid propellant provides great convenience.

4, practical value is high, great convenience can be brought to the formula development process of low signature solid propellant, in actual mechanical process, carry out Structure Network format after process by automatically carrying out plume analog computation to designed solid propellant and tackling plume result of calculation mutually, easy, fast and accurately can go out carry out microwave attenuation calculating, infrared radiation calculates or the subsequent calculations such as photoelectric characteristic calculating.In actual mechanical process, only need adjust the weight proportion of the designed solid propellant each component used of preparation, data processor just automatically can complete plume analog computation and Structure Network and to format processing procedure, and can calculate according to microwave attenuation, the subsequent calculations results such as infrared radiation calculating or photoelectric characteristic calculating, just can be easy, intuitively and accurately show that the weight proportion of the designed solid propellant each component used of preparation is on the impact of each performance of designed solid propellant, thus the formula development cycle of solid propellant is substantially reduced, greatly reduce formula development cost, for the formula Design of solid propellant provides great convenience.

5, result of use is good and popularizing application prospect is extensive, widely applicable, in the process of optimization of the easy input propellant formulation of energy, can economical, complete propellant formulation process of optimization efficiently, and there is the plurality of advantages such as result accuracy is high, processing speed is fast, only need a few minutes just can complete Structure Network to format processing procedure, practicality is very strong.

In sum, the inventive method step is simple, reasonable in design and realization is convenient, result of use is good, can complete solid propellant plume characteristic virtual test easy, fast and the flow field data based on unstrctured grid can be converted to the corresponding data of structure based grid so that subsequent calculations uses.

Below by drawings and Examples, technical scheme of the present invention is described in further detail.

Accompanying drawing explanation

Fig. 1 is method flow block diagram of the present invention.

Fig. 2 is the structural representation of engine jet pipe of the present invention and jet flow computational fields.

Fig. 3 is the method flow block diagram of gas-phase product plume data structure gridding process of the present invention.

Fig. 4 is the method flow block diagram of condensed phase product plume data structure gridding process of the present invention.

Embodiment

A kind of solid propellant plume characteristic virtual test as shown in Figure 1 and plume data structure gridding method, comprise the following steps:

Step one, Initial parameter sets and storage:

First, by the parameter input unit connected with data processor, the component information of the component quantity N that the designed solid propellant of input preparation is used and each component, and inputted synchronizing information is stored in the data storage cell that connects with described data processor; Wherein, the component information of each component includes chemical formula and quality proportioning m _i, i is positive integer, and i=1,2 ..., N; Wherein, N is the quantity of the designed solid propellant component used of preparation; 0 < m _i< 100, m ₁+ m ₂+ ... + m _n=100, N>=2.

Afterwards, by described parameter input unit in the products of combustion database set up in advance, all products of combustion produced after selecting designed SOLID PROPELLANT COMBUSTION; The attribute information of multiple products of combustion is stored in described products of combustion database; Wherein, the attribute information of each products of combustion includes chemical formula, relative molecular mass and phase, and wherein phase is gas phase or condensed phase; Simultaneously, by described parameter input unit to after designed SOLID PROPELLANT COMBUSTION produce products of combustion the quantity Q of quantity m and condensed phase product set, and the products of combustion produced after designed SOLID PROPELLANT COMBUSTION comprises Q condensed phase product and (m-Q) individual gas-phase product, wherein m and Q is positive integer, and Q>=1; As Q=1, after designed SOLID PROPELLANT COMBUSTION the condensed phase product produced in products of combustion be Al ₂o ₃particle.

Wherein, phase is the products of combustion of gas phase is gas-phase product, and the products of combustion that phase is condensed phase is condensed phase product.

In the present embodiment, designed solid propellant is that solid contains aluminium composite propellant.

Step 201, modeling: according to principle of minimum free energy, set up minimum free energy mathematical model and chamber temperature computation model.

Step 202, equilibrium composition calculate: the minimum free energy mathematical model set up in described data processor invocation step 201, and initial parameter set in integrating step one, calculate the products of combustion equilibrium composition after designed SOLID PROPELLANT COMBUSTION, and the equilibrium composition of m products of combustion that the products of combustion equilibrium composition calculated produces after comprising designed SOLID PROPELLANT COMBUSTION.

Equilibrium composition sum=1 of m the products of combustion produced after designed SOLID PROPELLANT COMBUSTION.

In the present embodiment, the equilibrium composition of each products of combustion calculated is when being in thermochemical equilibrium state after designed SOLID PROPELLANT COMBUSTION, the molar content of each products of combustion.

Step 203, adiabatic combustion temperature calculate: the chamber temperature computation model set up in described data processor invocation step 201, is in adiabatic combustion temperature during chemistry balance state after calculating designed SOLID PROPELLANT COMBUSTION.

Step 3, plume calculate, and its computation process is as follows:

Step 301, jet pipe geometric parameter and jet flow computational fields range set: the geometric parameter of engine jet pipe and jet flow computational fields scope are set by described parameter input unit; Wherein, the geometric parameter of engine jet pipe includes port radius r ₁, throat radius r ₂, exit radius r ₃, converging portion length d1, throat cylindrical section length d2, angle of flare α and expansion segment length d3, wherein entry radius r ₁for the entry radius of engine jet pipe, throat radius r ₂for the throat radius of engine jet pipe, exit radius r ₃for the exit radius of engine jet pipe, converging portion length d1 is the length of engine jet pipe entrance to nozzle throat front end, throat cylindrical section length d2 is the throat length of engine jet pipe, angle of flare α is the angle between the wall of engine jet pipe expansion segment and its axis, and expansion segment length d3 is the length of engine jet pipe throat end to nozzle exit; Jet flow computational fields scope comprises jet flow axial length x _mwith jet flow radical length y _m, wherein jet flow axial length x _mfor engine jet pipe exports to the length d4 of jet flow lower exit, jet flow radical length y _mfor engine jet pipe axis is to the length of the radial outer boundary of jet flow, refer to Fig. 2.

Step 302, combustion chamber operational setting parameter: first, by described parameter input unit to pressure P in the firing chamber of engine _c, environmental pressure and environment temperature T _ringset respectively; Afterwards, then to products of combustion equilibrium composition set; Then, by described parameter input unit to after designed SOLID PROPELLANT COMBUSTION produce Al ₂o ₃the mean grain size D of particle _nset.

When products of combustion equilibrium composition is set, the equilibrium composition of (m-Q) the individual gas-phase product produced after set products of combustion equilibrium composition comprises designed SOLID PROPELLANT COMBUSTION and Al ₂o ₃the equilibrium composition of particle; After the equilibrium composition of set (m-Q) individual gas-phase product is respectively the designed SOLID PROPELLANT COMBUSTION calculated in step 202 produce the equilibrium composition of (m-Q) individual gas-phase product; When in step one during Q=1, set Al ₂o ₃the equilibrium composition of particle is produced Al by after the designed SOLID PROPELLANT COMBUSTION that calculates in step 202 ₂o ₃the equilibrium composition of particle; When in step one during Q > 1, set Al ₂o ₃the equilibrium composition of particle by after the designed SOLID PROPELLANT COMBUSTION that calculates in step 202 the equilibrium composition sum n of generation Q condensed phase product _{condensed phase}.

Step 303, engine plume calculate: first, according to jet pipe geometric parameter set in step 301 and jet flow computational fields scope, adopt described data processor to set up and the two-dimensional axial symmetric model of numerical evaluation is carried out to plume inside and outside described engine jet pipe; Afterwards, described data processor calls CFD front processor, generate the plume computational fields grid chart of designed solid propellant, and described CFD front processor is GAMBIT software; Then, described data processor calls FLUENT software, and the combustion chamber operational parameter set by jet pipe geometric parameter set in the energy response parameter calculated in integrating step two, step 301 and jet flow computational fields scope and step 302, plume calculating is carried out to designed solid propellant, and automatically exports plume result of calculation.Wherein, the plume result of calculation exported comprises gas-phase product plume result of calculation and condensed phase product plume result of calculation.

In the present embodiment, the FLUENT software adopted is ANSYSFLUENT software.

In the present embodiment, carry out engine plume in step 303 when calculating, gas-phase product governing equation be turbulence model, and described turbulence model adopts the k-ε model (i.e. Realizablek-ε turbulentmodel) of the correction of two equations.The grid adopted in the plume computational fields grid chart of the designed solid propellant of GAMBIT Software Create is rectangular node.

Further, in step 303 to designed solid propellant carry out plume calculate time, adopt the governing equation of condensed phase product to be Lagrangian particle-trajectory model.

In addition, before carrying out the calculating of engine plume in step 303, also need first by the finite-rate reaction model of described parameter input unit input products of combustion.The finite-rate reaction model inputted, with in step one by described parameter input unit in the products of combustion database set up in advance, select evaluate SOLID PROPELLANT COMBUSTION after the products of combustion that produces corresponding.

Actual carry out plume calculate time, when inputting the finite-rate reaction model of products of combustion, " numerical simulation of burning " that " the rocket charge thermal performance handbook " of the Wang Sunyuan chief editor that reference is published for 1991, the Zhao Jianhang of Science Press's publication in 2002 edit or the document such as the Tao Yang of publishing house of National University of Defense technology publication in 2008 09 month, " the rocket engine theory of combustion " of Fang Dingxi, Tang Qiangang chief editor are determined inputted finite-rate reaction model.

Such as, when in the products of combustion produced after SOLID PROPELLANT COMBUSTION, O is comprised ₂, H ₂o, CO, CO ₂, H, H ₂, O, OH, N ₂deng 9 gaseous components and solidifying phase component Al ₂o ₃time, Chemical Reaction Model is the chemical dynamic model that 9 components 10 are reacted, and the chemical dynamic model that 9 components 10 adopted are reacted refers to table 1:

The chemical dynamic model reaction mechanism tables of data that table 19 component 10 is reacted

Chemical equation	A(cm3/mol·s)	n	E(j)
				CO+O+M＝CO ₂+M	8.310E-12	0	-9.70E+03
CO+OH＝CO ₂+H	6.323E+06	-1.5	-2.08E+03
				H ₂+OH＝H ₂O+H	1.024E+08	1.6	1.38E+04
H ₂+O＝OH+H	5.119E+04	2.67	2.63E+04

Chemical equation	A(cm3/mol·s)	n	E(j)
				H+O ₂＝OH+O	1.987E+14	0	7.03E+04
OH+OH＝H ₂O+O	1.506E+09	1.14	4.14E+02
				H+H+M＝H ₂+M	1.493E-06	-1	0
O+O+M＝O ₂+M	2.409E-07	-1	0
				O+H+M＝OH+M	7.829E-06	-1	0
H+OH+M＝H ₂O+M	3.673E-02	-2	0

When in the products of combustion produced after SOLID PROPELLANT COMBUSTION, comprise O ₂, H ₂o, CO, CO ₂, H, H ₂, O, OH, N ₂, HCL, CL, CL ₂deng 12 gaseous components and solidifying phase component Al ₂o ₃time, Chemical Reaction Model is the chemical dynamic model of 12 components 17, and the chemical dynamic model that 12 components 17 adopted are reacted refers to table 2:

The chemical dynamic model reaction mechanism tables of data that table 212 component 17 is reacted

Step 401, spout area vapor phase product stream field data read: the flow field data reading all unstrctured grid nodes in the spout area of designed solid propellant in the gas-phase product plume result of calculation adopting described data processor to export from step 303; Described spout area is the rectangular area at described engine jet pipe outlet rear.

In the present embodiment, the gas-phase product plume result of calculation exported in step 303 is be stored in the result of calculation in * _ tec.dat file, and * _ tec.dat file is FLUENT software has calculated the text of the Tecplot form of rear automatic preservation.

Such as, when in the products of combustion produced after designed SOLID PROPELLANT COMBUSTION, O is comprised ₂, H ₂o, CO, CO ₂, H, H ₂, O, OH, N ₂deng 9 gaseous components and solidifying phase component Al ₂o ₃time, the front 3 row contents of * _ tec.dat file are as follows:

TITLE＝"title"

VARIABLES＝X，Y，"temperature"，"pressure"，"molef-OH"，"molef-H ₂"，"molef-CO"，"molef-CO ₂"，"molef-H ₂O"，"molef-O ₂"，"molef-O"，"molef-H"，"molef-N ₂"，"dpm-concentration"，"axial-velocity"，"radial-velocity"，"mach-number"，"density"，"turb-kinetic-energy"，"turb-diss-rate"，"n2-src"，"oh-src"，"o-src"，"h2-src"，"h-src"，"co2-src"，"co-src"，"h2o-src"，"o2-src"

ZONET＝"Rampant"，N＝17841，E＝17472，ET＝QUADRILATERAL，F＝FEBLOCK

1st row starts with TITLE, is fixing file header.

2nd row starts with VARIABLES, is thereafter 29 the flow field name variables preserved in file, with CSV between different variable.These 29 flow field variablees are followed successively by: axial coordinate, radial coordinate, temperature, pressure, OH component molar mark, H ₂component molar mark, CO component molar mark, CO ₂component molar mark, H ₂o component molar mark, O ₂component molar mark, O component molar mark, H component molar mark, N ₂component molar mark, discrete phase concentration, vapor axial speed, gas phase radial velocity, Mach number, density of gas phase, tubulence energy, DIFFUSION IN TURBULENCE speed, N ₂component source item, OH component source item, O component source item, H ₂component source item, H component source item, CO ₂component source item, CO component source item, H ₂o component source item, O ₂component source item.

3rd row starts with VARIABLES, and N=17841 is thereafter unique information be concerned about in step 401, represents in plume and has 17841 unstrctured grid points.

Continuous print 29 flow field variable data blocks from the 4th row, first be the axial coordinate data (being corresponding in turn to the 1st to N number of unstrctured grid point) of N number of unstrctured grid point, next be the radial coordinate data of N number of unstrctured grid point ..., be finally N number of O ₂component source item number certificate.With single space-separated between text data, and for having the exponential scheme of 5 position effective digitals after radix point.

In the present embodiment, the flow field data of all unstrctured grid nodes in the designed solid propellant spout area read out in step 401 are the data stored in * _ tec.dat file.

Further, the flow field data read comprise unstrctured grid point quantity N and multiple flow fields variable data block corresponding with N number of unstrctured grid point respectively.In the present embodiment, the flow field data read comprise unstrctured grid point quantity N=17841 and 29 corresponding with 17841 unstrctured grid points respectively flow field variable data blocks.

In the present embodiment, when the flow field data of unstrctured grid nodes all in the spout area of designed solid propellant being read in step 401, first F dynamically one-dimension array is set up, wherein F=F1+F2, wherein F1=7, F2=m-Q, m-Q by after designed SOLID PROPELLANT COMBUSTION the quantity of generation gas-phase product.F dynamically one-dimension array is respectively used to F the flow field variable data storing N number of unstrctured grid point, and F flow field variable data is respectively axial coordinate, radial coordinate, temperature, pressure, the equilibrium composition of (m-Q) individual gas-phase product, condensed phase concentration, vapor axial speed and density of gas phase.

In the present embodiment, F2=m-Q=9.And F=F1+F2=16.Further, 16 dynamic one-dimension array are respectively used to the axial coordinate storing N number of unstrctured grid point, radial coordinate, temperature, pressure, OH component molar mark, H ₂component molar mark, CO component molar mark, CO ₂component molar mark, H ₂o component molar mark, O ₂component molar mark, O component molar mark, H component molar mark, N ₂component molar mark, condensed phase concentration, vapor axial speed and density of gas phase; After 16 dynamic one-dimension array create, from * _ tec.dat file, read corresponding data store.Further, in 16 dynamic one-dimension array store data quantity be N number of.

On step 402, axial coordinate axle, unstrctured grid point extracts: adopt described data processor from all unstrctured grid nodes spout area described in step 401, extract all unstrctured grid points be positioned on axial coordinate axle, the unstrctured grid point total quantity be positioned on axial coordinate axle extracted is N _x; Wherein, axial coordinate axle is the abscissa axis at the central axis place of described engine jet pipe, the radial coordinate y being positioned at the unstrctured grid point on axial coordinate axle extracted in this step _h=0 and its axial coordinate x _h>=0, wherein h is positive integer, and h=1,2 ..., N _x.

On step 403, radial coordinate axle, unstrctured grid point extracts: adopt described data processor from all unstrctured grid nodes spout area described in step 401, extract all unstrctured grid points be positioned on radial coordinate axle, the unstrctured grid point total quantity be positioned on radial coordinate axle extracted in this step is N _{y goes out}; Wherein, radial coordinate axle is the axis of ordinates at place, described engine jet pipe exit and the axial coordinate value in engine jet pipe exit is 0, is positioned at the axial coordinate x of the unstrctured grid point on radial coordinate axle _k1=0 and its radial coordinate y _k1>=0, wherein k1 is positive integer, and k1=1,2 ..., N _{y goes out}.

Wherein, abscissa axis and axis of ordinates form a two-dimensional direct angle coordinate system.

Step 404, structure Structure Network trrellis diagram: by N _xbar straight line x=x _hand N _{y goes out}bar straight line y=y _k1after orthogonal, construct one and comprise (N _x-1) × (N _{y goes out}-1) the Structure Network trrellis diagram of individual rectangular node; Wherein, h=1,2 ..., N _x; K1=1,2 ..., N _{y goes out}.

In the present embodiment, after extracting all unstrctured grid points be positioned on axial coordinate axle in step 402, the extracted all unstrctured grid points be positioned on axial coordinate axle arrange according to axial coordinate order from small to large by described data processor, and mark from left to right on described axial coordinate axle; After extracting all unstrctured grid points be positioned on radial coordinate axle in step 403, the extracted all unstrctured grid points be positioned on radial coordinate axle arrange according to radial coordinate order from small to large by described data processor, and mark from the bottom to top on described radial coordinate axle.

In the present embodiment, described spout area is a rectangular area, and it is made up of multiple rectangular nodes of axial coordinate >=0 in the plume computational fields grid chart of GAMBIT Software Create.Because in the outer boundary of spout area after being transformed into Structure Network trrellis diagram and the plume computational fields grid chart of GAMBIT Software Create, the outer boundary of spout area overlaps.Therefore, first (radial coordinate=0 on abscissa axis is determined, axial coordinate >=0) all unstrctured grid points, above-mentioned unstrctured grid point is by all unstrctured grid nodes in the described spout area of traversal, and extract and meet radial coordinate=0, all unstrctured grid nodes of axial coordinate >=0 also obtain after sorting from small to large according to axial coordinate; Afterwards, determine axis of ordinates (radial coordinate >=0, axial coordinate=0) on all unstrctured grid points, above-mentioned unstrctured grid point is by all unstrctured grid nodes in the described spout area of traversal, and extract and meet radial coordinate >=0, all unstrctured grid nodes of axial coordinate=0 also sort to obtain according to radial coordinate from small to large.

After all unstrctured grid points on abscissa axis and all unstrctured grid points on axis of ordinates are all determined, the form forming rectangular node according to line orthogonal just can construct Structure Network trrellis diagram, and in constructed Structure Network trrellis diagram, the quantity of rectangular node is (N _x-1) × (N _{y goes out}-1) individual, and four of each rectangular node summits are Structured Grid Points, and in constructed Structure Network trrellis diagram, the quantity of Structured Grid Points is N _x× N _{y goes out}individual.

Step 405, gas-phase product plume data structure gridding process: adopt described data processor to carry out assignment again respectively to the vapor phase product stream field data on four summits of each rectangular node in Structure Network trrellis diagram constructed in step 404; In all rectangular nodes, assignment method is all identical again for the vapor phase product stream field data on each summit, wherein for when in constructed Structure Network trrellis diagram, the vapor phase product stream field data on arbitrary summit of any one rectangular node carries out again assignment, described data processor is first found out and is assigned the nearest unstrctured grid node of vertex distance with current from all unstrctured grid nodes spout area described in step 401, and the vapor phase product stream field data of found out unstrctured grid node is assigned to the current summit be assigned.

Wherein, the present invention adopt the method flow block diagram of gas-phase product plume data structure gridding process, refer to Fig. 3.

In the present embodiment, when carrying out the gridding process of gas-phase product plume data structure in step 405, need to N in constructed Structure Network trrellis diagram _x× N _{y goes out}individual Structured Grid Points carries out assignment again respectively.And, the principle of each Structured Grid Points being carried out again to assignment is: filter out from the nearest unstrctured grid node of this Structured Grid Points from all unstrctured grid nodes described spout area, and by burn the unstrctured grid node selected flow field data be assigned to this Structured Grid Points.

In the present embodiment, after completing gas-phase product plume data structure gridding process in step 405, also need result stores synchronized in the data storage cell connected with described data processor.

Step 501, Structure Network are formatted process Initial parameter sets: adopt described parameter input unit to the particle diameter D of the value of M and M different-grain diameter particle _nrset respectively; Wherein, r is positive integer, and r=1,2 ..., M.

In the present embodiment, M=8 in step 501, and the particle diameter D of 8 different-grain diameter particles _nrbe respectively D _n1, D _n2, D _n3, D _n4, D _n5, D _n6, D _n7and D _n8, wherein, D _n1< D _n2< D _n3< D _n4< D _n< D _n5< D _n6< D _n7< D _n8, wherein, D _nby being produced Al after SOLID PROPELLANT COMBUSTION designed by set in step 302 ₂o ₃the mean grain size of particle.

During actual use, can according to actual needs, adjust accordingly the value size of M, and the value of M is larger, particle trajectory gridded data result is more accurate.

The actual particle diameter D to M different-grain diameter particle _nrwhen setting, with reference to after designed SOLID PROPELLANT COMBUSTION set in step 302 produce Al ₂o ₃the mean grain size D of particle _nset, specifically at mean grain size D _nthe left and right sides respectively symmetry choose multiple particle diameter.That is, in the domain size distribution field adopting FLUENT software to calculate, at mean grain size D _nthe left and right sides respectively symmetry choose multiple particle diameter.

Step 502, particle trajectory digital independent: all particle trajectory data reading designed solid propellant in the condensed phase product plume result of calculation adopting described data processor to export from step 303; Wherein, the condensed phase product plume result of calculation read comprises mass particle file, particle temperature with the file of trail change, the file of particle diameter with trail change and the time step file of particle trajectory.

In the present embodiment, the mass particle file read, particle temperature are respectively FLUENT software with the file of trail change, particle diameter with the file of trail change and the time step file of particle trajectory and have calculated * _ mass.fvp, the * _ temp.fvp of rear automatic preservation, * _ diam.fvp and * _ time.fvp file.

Wherein, * _ mass.fvp, * _ temp.fvp, * _ diam.fvp and * _ time.fvp are the file of text formatting, and * _ mass.fvp, * _ temp.fvp, * _ diam.fvp are all identical with the file content storage format of * _ time.fvp.For time step file * _ time.fvp, its front 7 behavior file heads, content is as follows:

FVPARTICLES21

TagNames

0

VariableNames

2

ParticleTimeStep

particle_id

Except the 6th row represent name variable (ParticleTimeStep) and different except, the file header of other 3 * .fvp (i.e. * _ mass.fvp, * _ temp.fvp and * _ diam.fvp) is identical.From eighth row, record particle trajectory data, content is as follows:

Eighth row is 1 integer, and the total track represented on this track is counted NL (namely 1141).The data of 1141 tracing points of 1141 line items so from the 9th row, often row is made up of 5 fields.Front 3 fields represent the x of this point respectively, y, z coordinate, and for two-dimensional case z=0, the 4th field is the time step at this tracing point place, and the 5th field is the sequence number (from 0) of this article of track.Article 1, track is then the data segment of the 2nd article of track after terminating, and the data segment of every bar track all starts with the row only comprising an integer (NL), represents the data of the NL behavior identical strip path curve from lower 1 row.

Step 503, engine jet pipe entrance rectangular node quantity obtain and the up-and-down boundary of each nozzle entry rectangular node is determined: first, read the flow field data of all unstrctured grid nodes in the engine jet pipe region of designed solid propellant in the gas-phase product plume result of calculation adopting described data processor to export from step 303; Afterwards, adopt described data processor from all unstrctured grid nodes read engine jet pipe region, extract all unstrctured grid nodes be positioned on straight line x=-Δ d, and the unstrctured grid point total quantity be positioned on straight line x=-Δ d extracted is N _{y enters}; Wherein, the axial coordinate x of the unstrctured grid node on straight line x=-Δ d is positioned at _k2=-Δ d and its radial coordinate y _k2>=0, wherein k2 is positive integer, and k2=1,2 ..., N _{y enters}; Δ d=d1+d2+d3; The nozzle entry rectangular node quantity obtained is (N _{y enters}-1) individual, the up-and-down boundary of each nozzle entry rectangular node is respectively two neighbouring straight line y=y _k2.Wherein, the rectangular node of described engine jet pipe porch is nozzle entry rectangular node.

In the present embodiment, before engine jet pipe entrance rectangular node quantity is obtained, first at described engine jet pipe internal build structured grid, and when described engine jet pipe internal build structured grid, first adopt described data processor from all unstrctured grid nodes read engine jet pipe region, extract all unstrctured grid nodes be positioned on straight line x=-Δ d, and the unstrctured grid point total quantity be positioned on straight line x=-Δ d extracted is N _{y enters}, the radial coordinate y being positioned at the unstrctured grid point on straight line x=-Δ d extracted _{k enters}>=0, wherein k enters for positive integer, and k enter=1,2 ..., N _{y enters}; Afterwards, adopt described data processor from all unstrctured grid nodes read engine jet pipe region, extract all unstrctured grid points be positioned on the axle of axial coordinate described in step 402, the unstrctured grid point total quantity be positioned on axial coordinate axle extracted is N _x-tube, now the extracted radial coordinate y being positioned at the unstrctured grid point on axial coordinate axle _{h manages}=0 and its axial coordinate x _{h manages}≤ 0, wherein h pipe is negative integer, and h pipe=-1 ,-2 ... ,-N _x-tube+ 1 ,-N _x-tube.By N _x-tubebar straight line x=x _{h manages}and N _{y enters}bar straight line y=y _{k enters}after orthogonal, construct one and comprise (N _x-tube-1) × (N _{y enters}-1) the Structure Network trrellis diagram of individual rectangular node.

Wherein, as h pipe=-N _x-tubetime, x _{h manages}=-Δ d; As h pipe=-N _x-tubewhen+1, x _{h manages}=c1.Further, straight line x=-Δ d, straight line x=c1 and N _{y enters}bar straight line y=y _{k enters}described engine jet pipe porch is divided into (N _{y enters}-1) individual rectangular node.

Wherein, described nozzle entry rectangular node is the rectangular node being positioned at engine jet pipe porch.

Wherein, c1 is the inner abscissa value being positioned at unstrctured grid point on described axial coordinate axle and nearest with described engine jet pipe entrance of extracted described engine jet pipe.

Because particle trajectories all in engine jet pipe plume all originates from engine jet pipe entrance, and the particle trajectory starting point in each nozzle entry rectangular node is the mid point in this boundary line, nozzle entry rectangular node left side, wherein the boundary line, the left side of each nozzle entry rectangular node is all positioned on axis of ordinates.In the present embodiment, when carrying out the data structure gridding process of condensed phase product plume in step 504, the particle trajectory total quantity that need process is M × (N _{y enters}-1) bar, the quantity of the need process particle trajectory wherein using each nozzle entry rectangular node as starting mesh is M bar.

In the present embodiment, in step 504, complete condensed phase product plume data structure gridding process, also need the M × (N will obtained after process _{y enters}-1) Structure Network of bar particle trajectory is formatted in the equal stores synchronized of result to described data storage cell.

In the present embodiment, when the particle trajectory gridded data of current handled particle trajectory in all rectangular nodes of described Structure Network trrellis diagram midway warp being calculated in step 504, according to institute by way of rectangular node installation position tandem by first extremely after calculate.

In the present embodiment, in step 504 to arbitrary particle trajectory in M different-grain diameter particle trajectory carry out Structure Network format process time, its processing procedure is as follows:

Step 5041, engine jet pipe entrance starting mesh are determined and mass particle flow rate calculate: the particle trajectory data finding out current handled particle trajectory in all particle trajectory data that described data processor reads in step 502, and according to the up-and-down boundary of determined each nozzle entry rectangular node in the radial coordinate of the engine jet pipe porch tracing point in found out particle trajectory data and step 503, determine the nozzle entry starting mesh of current handled particle trajectory, wherein the nozzle entry starting mesh of current handled particle trajectory is the current handled starting mesh of particle trajectory in engine jet pipe porch; Find out particle trajectory data and comprise mass particle file, particle temperature with the file of trail change, particle diameter with the data stored in the file of trail change and the time step file of particle trajectory.

\overset{\cdot}{m_{g}} = \frac{\overset{\cdot}{m_{g 1}} + \overset{\cdot}{m_{g 2}}}{2},

In formula wherein S _gridfor the area of the nozzle entry starting mesh of current handled particle trajectory.

That is, in the present embodiment, when carrying out in step 303 carrying out the data structure gridding process of condensed phase product plume in the calculating of engine plume and step 5, when comprising except Al in the products of combustion produced after designed SOLID PROPELLANT COMBUSTION ₂o ₃during other type condensed phase product of particle and so on, all other type condensed phase product is used as Al ₂o ₃particle processes, and so not only drastically reduce the area calculated amount, and the harmful effect caused the accuracy of plume result of calculation and condensed phase product plume data structure gridding result is very little.

Wherein, described data processor find out determine the summit one of nozzle entry starting mesh and the vapor phase product stream field data on summit two, be respectively after in step 405, gas-phase product plume data structure gridding process completes, the summit one of the nozzle entry starting mesh of current handled particle trajectory and the summit two vapor phase product stream field data separately again after assignment.

Step 5042, engine jet pipe exit (i.e. jet inlets place) starting mesh are determined: described data processor according in step 5041 find out axial coordinate and the radial coordinate of each tracing point in the particle trajectory data of current handled particle trajectory, and Structure Network trrellis diagram constructed in integrating step 404, current handled particle trajectory is determined at the starting mesh in engine jet pipe exit.

In the present embodiment, to current handled particle trajectory when the starting mesh in engine jet pipe exit is determined, travel through all tracing points on current handled particle trajectory, and the corresponding radial coordinate R finding out first tracing point of axial coordinate>=0 _p0, then according to R _p0the jet inlets grid (i.e. the starting mesh in engine jet pipe exit) of current handled particle trajectory is determined.

Step I, mass particle calculate: in the mass particle file of the current handled particle trajectory that described data processor is found out in step 5041, find out the current handled mass particle m of particle trajectory in engine jet pipe porch _grain, and the mass particle m in current calculated rectangular node _grid=m _grain.

Because on each bar particle trajectory, mass particle remains constant, thus current handled particle trajectory by way of all rectangular nodes in mass particle remain constant, and be equal to m _grain.

Step II, population density calculate: described data processor is according to formula calculate the population density N in current calculated rectangular node _p; Dt is the residence time of current handled particle trajectory in current calculatings rectangular node, and dt is the time step sum of all tracing points of particle trajectory handled by current in current calculating rectangular node; In formula, for the mass particle flow rate in the nozzle entry starting mesh of current handled particle trajectory that calculates in step 5041.

Step III, average particle diameter and medial temperature: described data processor is respectively according to formula with calculate the average particle diameter D in current calculated rectangular node _pwith particle medial temperature T _p; In formula, k3 is positive integer, and k3=1,2 ..., K, wherein K is the tracing point total quantity of current handled particle trajectory in current calculating rectangular node, and D _pk3and T _pk3be respectively particle diameter and the particle temperature at kth 3 tracing point places in K tracing point; Dt is the residence time of current handled particle trajectory in current calculating rectangular node, dt _k3by the residence time of kth 3 tracing points in K tracing point in current calculating rectangular node.

In the present embodiment, to the average particle diameter D in current calculated rectangular node in step III _pwith particle medial temperature T _pwhen calculating, first according to up-and-down boundary radial coordinate and the right boundary axial coordinate of current calculated rectangular node, and the axial coordinate of each tracing point in the particle trajectory data found out in integrating step 5041 and radial coordinate, the axial coordinate of the tracing point total quantity K of current handled particle trajectory in current calculated rectangular node and K tracing point and radial coordinate are determined respectively.

When reality is determined the current handled tracing point total quantity K of particle trajectory in current calculated rectangular node, travel through the tracing point on current handled particle trajectory, and find out axial coordinate between the right boundary axial coordinate of current calculated rectangular node and the tracing point of radial coordinate between the up-and-down boundary radial coordinate of current calculated rectangular node.Current handled particle trajectory in current calculated rectangular node is divided into multiple orbit segment by K tracing point, and the time step sum of multiple described orbit segment (i.e. the time step sum of K tracing point) is just dt.

Wherein, the present invention adopt the method flow block diagram of condensed phase product plume data structure gridding process, refer to Fig. 4.

In the present embodiment, when setting products of combustion equilibrium composition in step 302, set products of combustion equilibrium composition is according to Metal Phase principle, calculates the chemical equilibrium composition of products of combustion.

In the present embodiment, when products of combustion equilibrium composition being set in step 302, when in step one during Q=1, by the equilibrium composition of m products of combustion produced after SOLID PROPELLANT COMBUSTION designed by calculating in described parameter input unit respectively input step 202, or described data processor call parameters arranges the equilibrium composition of m the products of combustion produced after module transfers out the designed SOLID PROPELLANT COMBUSTION calculated in step 202 automatically; When in step one during Q > 1, first according to the equilibrium composition of m the products of combustion produced after SOLID PROPELLANT COMBUSTION designed by calculating in step 202, after calculating designed SOLID PROPELLANT COMBUSTION produce the equilibrium composition sum m of Q condensed phase product _{condensed phase}; Afterwards, equilibrium composition sum m is inputted respectively by described parameter input unit _{condensed phase}with calculate in step 202 designed by the equilibrium composition of (m-Q) individual gas-phase product that produces after SOLID PROPELLANT COMBUSTION, or described data processor call parameters arranges module and automatically transfers out the equilibrium composition sum m precalculating and draw _{condensed phase}with calculate in step 202 designed by the equilibrium composition of (m-Q) individual gas-phase product that produces after SOLID PROPELLANT COMBUSTION.

According to thermodynamic principles, the products of combustion of solid propellant can be considered ideal gas under the high temperature conditions, then the free energy of whole system just equals the summation of each component free energy of this system, oneself knows that the free energy of material is the function of pressure, temperature and concentration, when this system reaches chemical equilibrium, the free energy minimization of system.Therefore, under certain pressure and temperature condition, obtain a component value that system free energy minimization can be made to meet again law of conservation of mass, then this group component value is the products of combustion equilibrium composition of system under this condition.When reaching chemical equilibrium according to system, the summation of its free energy function is minimum principle, adopts the mathematical method of convergence rapidly, can be separated the chemical equilibrium composition of any complication system by iteration.

In the present embodiment, the minimum free energy mathematical model set up in step 201 is in formula (1): j is positive integer, and j=1,2 ..., the kind of A, A chemical element contained by solid propellant; S is positive integer, and s=1,2 ..., m, m are the kind number of contained products of combustion when being in chemistry balance state after SOLID PROPELLANT COMBUSTION; wherein μ _sfor the chemical potential (KJ/mol) of s kind products of combustion inputted by described parameter input unit in advance, n _sthe molal quantity (mol/Kg) of contained s kind products of combustion during for being in chemistry balance state after 1000g SOLID PROPELLANT COMBUSTION and n _s>=0, a _sjfor the atomicity of jth kind chemical element contained in 1mol s kind products of combustion; b _jfor the atomicity of jth kind chemical element contained in 1000g solid propellant, π _jfor Lagrange multiplier.

During actual use, Free energy Minimization is obtained exactly and is being met one group of n under formula (1) condition _svalue makes system free energy minimization, wherein s=1,2 ... m, and n _s>=0, this is the constrained extremal problem of multivariate function, can solve with Lagrangian method.

When reality solves chemical equilibrium composition, also can adopt Henan science tech publishing house in " chemical propellant calculating energetics " book by Tian Deyu, Liu Jianhong work of publication in 1999, chemical equilibrium composition computing method described in Section 6.3 " chemical equilibrium containing condensed phase products of combustion forms " in chapter 6 " fundamental equation that energy response calculates " calculate.

In the present embodiment, carry out equilibrium composition in step 202 when calculating, described data processor call parameters computing module, the chemical formula of solid propellant each component used and quality proportioning m designed by the preparation inputted in step one _i, and in conjunction with the relative molecular mass of each component, to a _sjand b _jcalculate; Afterwards, described data processor combines the μ pre-entered _sand π _j, and according to formula calculate n _s, now just obtain the products of combustion equilibrium composition after designed SOLID PROPELLANT COMBUSTION;

When carrying out adiabatic combustion temperature calculating in step 203, the products of combustion equilibrium composition after the designed SOLID PROPELLANT COMBUSTION calculated in described data processor integrating step 202, and according to formula calculate chamber temperature T _c; Wherein, wherein M _ifor preparing the relative molecular mass of designed solid propellant i-th kind of component used, H _ifor the enthalpy of 1mol i-th kind of component, W _ifor preparing the mass percent of designed solid propellant i-th kind of component used.Wherein, W _iwith input the quality proportioning m preparing designed solid propellant each component used in step one _iunanimously.

The above; it is only preferred embodiment of the present invention; not the present invention is imposed any restrictions, every above embodiment is done according to the technology of the present invention essence any simple modification, change and equivalent structure change, all still belong in the protection domain of technical solution of the present invention.

Claims

1. solid propellant plume characteristic virtual test and a plume data structure gridding method, is characterized in that the method comprises the following steps:

Step one, Initial parameter sets and storage:

First, by the parameter input unit connected with data processor, the component information of the component quantity N that the designed solid propellant of input preparation is used and each component, and inputted synchronizing information is stored in the data storage cell that connects with described data processor; Wherein, the component information of each component includes chemical formula and quality proportioning m _i, i is positive integer, and i=1,2 ..., N; Wherein, N is the quantity of the designed solid propellant component used of preparation, 0 < m _i< 100, m ₁+ m ₂+ ... + m _n=100, N>=2;

Step 3, plume calculate, and its computation process is as follows:

Step 405, gas-phase product plume data structure gridding process: adopt described data processor to carry out assignment again respectively to the vapor phase product stream field data on four summits of each rectangular node in Structure Network trrellis diagram constructed in step 404; In all rectangular nodes, assignment method is all identical again for the vapor phase product stream field data on each summit, wherein for when in constructed Structure Network trrellis diagram, the vapor phase product stream field data on arbitrary summit of any one rectangular node carries out again assignment, find out in all unstrctured grid nodes of described data processor first in spout area described in step 401 and be assigned the nearest unstrctured grid node of vertex distance with current, and the vapor phase product stream field data of found out unstrctured grid node is assigned to the current summit be assigned;

Step 501, Structure Network are formatted process Initial parameter sets: adopt described parameter input unit to the particle diameter D of the value of M and M different-grain diameter particle _nrset respectively; Wherein, r is positive integer, and r=1,2 ..., M;

2. according to solid propellant plume characteristic virtual test according to claim 1 and plume data structure gridding method, it is characterized in that: when the particle trajectory gridded data of current handled particle trajectory in all rectangular nodes of described Structure Network trrellis diagram midway warp being calculated in step 504, according to institute by way of rectangular node installation position tandem by first extremely after calculate.

3., according to the solid propellant plume characteristic virtual test described in claim 1 or 2 and plume data structure gridding method, it is characterized in that: M=8 in step 501, and the particle diameter D of 8 different-grain diameter particles _nrbe respectively D _n1, D _n2, D _n3, D _n4, D _n5, D _n6, D _n7and D _n8, wherein, D _n1< D _n2< D _n3< D _n4< D _n< D _n5< D _n6< D _n7< D _n8, wherein, D _nby being produced Al after SOLID PROPELLANT COMBUSTION designed by set in step 302 ₂o ₃the mean grain size of particle.

4. according to the solid propellant plume characteristic virtual test described in claim 1 or 2 and plume data structure gridding method, it is characterized in that: in step 303 to designed solid propellant carry out plume calculate time, adopt the governing equation of condensed phase product to be Lagrangian particle-trajectory model.

5. according to solid propellant plume characteristic virtual test according to claim 4 and plume data structure gridding method, it is characterized in that: in step 504 to arbitrary particle trajectory in M different-grain diameter particle trajectory carry out Structure Network format process time, its processing procedure is as follows:

After the nozzle entry starting mesh of current handled particle trajectory is determined, described data processor finds out the summit one of determined nozzle entry starting mesh and the vapor phase product stream field data on summit two, and finds out the density of gas phase ρ at summit one place in the vapor phase product stream field data on the summit one found out _g1with gas phase axial velocity u _g1, and in the vapor phase product stream field data on the summit two found out, find out the density of gas phase ρ at summit two place _g2with gas phase axial velocity u _g2, wherein summit one is the summit, upper left side of the nozzle entry starting mesh of current handled particle trajectory, and summit two is the summit, lower left of the nozzle entry starting mesh of current handled particle trajectory; Afterwards, described data processor is according to formula calculate the mass particle flow rate in the nozzle entry starting mesh of current handled particle trajectory; In formula, M is the different-grain diameter number of particles that need set in step 501 carry out processing; f _ptogfor condensed phase and gas phase flow rate ratio and when in step one during Q=1, the n in formula _xby being produced Al after SOLID PROPELLANT COMBUSTION designed by calculating in step 202 ₂o ₃the equilibrium composition of particle; And when in step one during Q > 1, n in formula _xfor the n described in step 302 _{condensed phase}; for the gas phase flow rate in the nozzle entry starting mesh of current handled particle trajectory, and in formula wherein S _gridfor the area of the nozzle entry starting mesh of current handled particle trajectory;

6. according to solid propellant plume characteristic virtual test according to claim 5 and plume data structure gridding method, it is characterized in that: to the average particle diameter D in current calculated rectangular node in step III _pwith particle medial temperature T _pbefore calculating, first according to up-and-down boundary radial coordinate and the right boundary axial coordinate of current calculated rectangular node, and the axial coordinate of each tracing point in the particle trajectory data found out in integrating step 5041 and radial coordinate, the axial coordinate of the tracing point total quantity K of current handled particle trajectory in current calculated rectangular node and K tracing point and radial coordinate are determined respectively.

7. according to the solid propellant plume characteristic virtual test described in claim 1 or 2 and plume data structure gridding method, it is characterized in that: when plume calculating being carried out to designed solid propellant in step 303, adopt the governing equation of gas-phase product to be turbulence model, and described turbulence model is the k-ε model of the correction of two equations.

8. according to the solid propellant plume characteristic virtual test described in claim 1 or 2 and plume data structure gridding method, it is characterized in that: when products of combustion equilibrium composition being set in step 302, when in step one during Q=1, by the equilibrium composition of m products of combustion produced after SOLID PROPELLANT COMBUSTION designed by calculating in described parameter input unit respectively input step 202, or described data processor call parameters arranges the equilibrium composition of m the products of combustion produced after module transfers out the designed SOLID PROPELLANT COMBUSTION calculated in step 202 automatically, when in step one during Q > 1, first according to the equilibrium composition of m the products of combustion produced after SOLID PROPELLANT COMBUSTION designed by calculating in step 202, after calculating designed SOLID PROPELLANT COMBUSTION produce the equilibrium composition sum n of Q condensed phase product _{condensed phase}, afterwards, equilibrium composition sum m is inputted respectively by described parameter input unit _{condensed phase}with calculate in step 202 designed by the equilibrium composition of (m-Q) individual gas-phase product that produces after SOLID PROPELLANT COMBUSTION, or described data processor call parameters arranges module and automatically transfers out the equilibrium composition sum m precalculating and draw _{condensed phase}with calculate in step 202 designed by the equilibrium composition of (m-Q) individual gas-phase product that produces after SOLID PROPELLANT COMBUSTION.

9. according to the solid propellant plume characteristic virtual test described in claim 1 or 2 and plume data structure gridding method, it is characterized in that: after extracting all unstrctured grid points be positioned on axial coordinate axle in step 402, the extracted all unstrctured grid points be positioned on axial coordinate axle arrange according to axial coordinate order from small to large by described data processor, and mark from left to right on described axial coordinate axle; After extracting all unstrctured grid points be positioned on radial coordinate axle in step 403, the extracted all unstrctured grid points be positioned on radial coordinate axle arrange according to radial coordinate order from small to large by described data processor, and mark from the bottom to top on described radial coordinate axle.

10. according to the solid propellant plume characteristic virtual test described in claim 1 or 2 and plume data structure gridding method, it is characterized in that: the minimum free energy mathematical model set up in step 201 is in formula (1): j is positive integer, and j=1,2 ..., the kind of A, A chemical element contained by solid propellant; S is positive integer, and s=1,2 ..., m, m are the kind number of contained products of combustion when being in chemistry balance state after SOLID PROPELLANT COMBUSTION; wherein μ _sfor the chemical potential (KJ/mol) of s kind products of combustion inputted by described parameter input unit in advance, n _sthe molal quantity (mol/Kg) of contained s kind products of combustion during for being in chemistry balance state after 1000g SOLID PROPELLANT COMBUSTION and n _s>=0, a _sjfor the atomicity of jth kind chemical element contained in 1mol s kind products of combustion; b _jfor the atomicity of jth kind chemical element contained in 1000g solid propellant, π _jfor Lagrange multiplier;