CN103294855A

CN103294855A - Method for solid-propellant plume characteristic virtual experiments and flume data structure gridding

Info

Publication number: CN103294855A
Application number: CN2013101803493A
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: 2013-09-11
Anticipated expiration: 2033-05-15
Also published as: CN103294855B

Abstract

The invention discloses a method for solid-propellant plume characteristic virtual experiments and flume data structure gridding. The method includes 1, initializing parameter setting and storing, 2, calculating energy characteristic parameters, 3, calculating engine plume fields, 4, performing grinding processing on gaseous-product flume field data structures, and 5, performing gridding processing on condensed-phase-product flume field data structures. The step 4 includes reading gaseous-product flume field data in jet stream areas, establishing structure grid charts and performing gridding processing on the gaseous-product flume field data structures. The step 5 includes initialing parameter setting, reading particle trajectory data, acquiring grid quantity at inlets of spraying tubes, determining up and down borders of grids and performing gridding processing on the condensed-phase-product flume field data structures. The method is simple in procedure, reasonable in design, convenient to implement and good in using effect, plume characteristic virtual experiments can be simply, conveniently and rapidly completed, and plume field data based on unstructured grids can be converted into corresponding data based on structured grids for follow-up calculation.

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

Development along with mechanization, informationization technology, the modern weapons system more and more adopts radar, photoelectricity etc. from motion tracking, control and guidance means, aspects such as the automaticity of armament systems, attack precision are significantly improved, and have promoted the fighting efficiency that plays the arrow armament systems greatly.But meanwhile, the cigarette flame problem harmfulness that plays in the emission of arrow weapon and the delivery process manifests day by day, can influence very big to armament systems informationization, intellectuality, stealthy voltinism, to armament systems fast, precision strike, function such as stealthy caused severe bad influence, even become my army's bullet arrow weapon of restriction bring into normal play usefulness, new equipment is ordered goods and the major technique bottleneck of new-type weapon and equipment development.Especially in recent years, occur the problem that propellant loading smog blocks guidance signal in the heavy antitank missile development process, dealing with problems, it is huge to expend.

Solid propellant is the emission energy that plays the arrow armament systems, and its low signature performance is the key factor that guarantees that armament systems battlefield mission is finished.Plume is the penniform high-speed and high-temperature gas-flow that ejects from rocket tube, rocket plume is that a kind of gas molecule concentration is big, electron density and electron collision frequency very high weak plasma all, can interact between itself and the radar microwave, microwave signal power is greatly reduced, influence the guidance of guided missile.And the occupied space of fluid motion of the penniform high-speed and high-temperature gas-flow that plume is rocket tube to eject.For estimating solid propellant plume characteristic, some developed countries have all set up the dependence test appraisal procedure in the world, have built various experiment test facilities and have come solid propellant characteristic signal performance is detected and characterizes.Domestic on the basis to external test facilities research, set up low cost that a cover has 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 to expend lot of manpower and material resources, lead time prolongs significantly, thereby brings enormous economic loss and political fallout, nowadays presses for virtual test the solid propellant correlated performance is estimated fast.And virtual test is to resolve by means of the high speed of computing machine,, not only can be used as the preliminary preparation of true test or substitute traditional test (as some limiting conditions) to a certain extent carrying out simulation test based on propellant combustion and the mobile mathematical model of products of combustion by the actual tests requirement; And can significantly reduce true test number (TN), reduce testing expenses, shorten the test period; Simultaneously, have interactivity preferably, make various Test Information in time feed back; In addition, virtual test is not subjected to 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, when the mathematical model that propellant combustion and products of combustion are flowed is carried out simulation test, usually the plume after all adopting FLUNT software to SOLID PROPELLANT COMBUSTION is simulated, and after the plume that adopts FLUNT software to finish designed solid propellant calculates, just can export * .out file automatically and use for microwave attenuation calculating, infrared radiation calculating and photoelectric characteristic calculating.But because the flow field data that are based on non-structured grid of preserving among FULENT software saving file * _ tec.dat, and jet pipe zone and jet flow zone have been comprised.Since microwave attenuation calculates, infrared radiation calculates and subsequent calculations such as photoelectric characteristic calculating in only at the jet flow zone, thereby the flow field data extract that FULENT software need be calculated the jet flow zone that obtains, back come out to carry out structured grid conversion, and converts corresponding data based on structured grid to so that the subsequent calculations use.In addition, because FULENT can only preserve the particle trajectory historical data, and infrared radiation calculating and photoelectric characteristic calculating needs is number density and the temperature of different-diameter particle, thereby also need handle by the flow field data of FULENT software being calculated the jet flow zone that obtains, back, and correspondingly draw in the jet flow zone number density and the temperature of the interior different-diameter particle of each structured grid on each bar particle trajectory.

Summary of the invention

Technical matters to be solved by this invention is at 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 simple, reasonable in design and realize convenient, result of use is good, can finish solid propellant plume characteristic virtual test easy, fast and can become based on the flow field data-switching of non-structured grid based on the corresponding data of structured grid so that subsequent calculations is used.

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 this method may further comprise the steps:

Step 1, initial parameter are set and storage:

At first, by the parameter input unit of joining with data processor, the component information of designed solid propellant component utilized quantity N and each component is prepared in input, and the information synchronization of importing is stored in the data storage cell that joins 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 used component of the designed solid propellant of preparation; 0＜m _i＜100, m ₁+ m ₂+ ... + m _N=100, N 〉=2;

Afterwards, in the products of combustion database of setting up in advance, select all products of combustion that produce after the designed SOLID PROPELLANT COMBUSTION by described parameter input unit; Store the attribute information of multiple products of combustion in the 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 designed SOLID PROPELLANT COMBUSTION after the quantity m of the products of combustion that produces and the quantity Q of condensed phase product set, and comprise Q condensed phase product and (m-Q) individual gas-phase product in the products of combustion that produces after the designed SOLID PROPELLANT COMBUSTION, wherein m and Q are positive integer, and Q 〉=1; When Q=1, the condensed phase product that is produced in the products of combustion after the designed SOLID PROPELLANT COMBUSTION is Al ₂O ₃Particle;

Step 2, energy response calculation of parameter, its computation process is as follows:

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

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

Step 203, adiabatic combustion temperature are calculated: the chamber temperature computation model of setting up in the described data processor invocation step 201 calculates the adiabatic combustion temperature when being in chemistry balance state after the 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 scope are set: by described parameter input unit geometric parameter and the jet flow computational fields scope of engine jet pipe are set; Wherein, the geometric parameter of engine jet pipe includes port radius r ₁, throat radius r ₂, the outlet radius r ₃, converging portion length d 1, throat's cylindrical section length d 2, angle of flare α and expansion segment length d 3, wherein entry radius r ₁Be the entry radius of engine jet pipe, throat radius r ₂Be the throat radius of engine jet pipe, the outlet radius r ₃The port radius that goes out for engine jet pipe, converging portion length d 1 is the length of engine jet pipe entrance to the nozzle throat front end, throat's cylindrical section length d 2 is the throat length of engine jet pipe, angle of flare α is the wall of engine jet pipe expansion segment and the angle between its axis, and expansion segment length d 3 is the terminal length to nozzle exit of engine jet pipe throat; Jet flow computational fields scope comprises jet flow axial length x _mWith jet flow radical length y _m, jet flow axial length x wherein _mFor engine jet pipe exports to the length d 4 of jet flow lower exit, jet flow radical length y _mFor the engine jet pipe axis arrives the radially length of outer boundary of jet flow;

Step 302, firing chamber running parameter are set: at 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, again to products of combustion equilibrium composition set; Then, by described parameter input unit to designed SOLID PROPELLANT COMBUSTION after the Al that produces ₂O ₃The mean grain size D of particle _nSet;

When equilibrium composition is set to products of combustion, comprise equilibrium composition and the Al of (m-Q) the individual gas-phase product that produces after the designed SOLID PROPELLANT COMBUSTION in the products of combustion equilibrium composition that sets ₂O ₃The equilibrium composition of particle; The equilibrium composition of (m-Q) the individual gas-phase product that sets is respectively the equilibrium composition of (m-Q) the individual gas-phase product that produces after the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202; When in the step 1 during Q=1, the Al that sets ₂O ₃The equilibrium composition of particle is produced Al after by the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202 ₂O ₃The equilibrium composition of particle; When Q in the step 1＞1, the Al that sets ₂O ₃The equilibrium composition of particle after by the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202 the equilibrium composition sum n of generation Q condensed phase product _{Condensed phase}

Step 303, engine plume calculate: at first, according to the jet pipe geometric parameter that sets in the step 301 and jet flow computational fields scope, adopt described data processor to set up the two-dimentional axisymmetric model that the inside and outside plume of described engine jet pipe is carried out numerical evaluation; Afterwards, described data processor calls the 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 FULENT software, and the firing chamber running parameter that sets in the jet pipe geometric parameter that sets in the energy response parameter that calculates in the integrating step two, step 301 and jet flow computational fields scope and the step 302, designed solid propellant is carried out plume calculate, and export plume result of calculation automatically; Wherein, comprise gas-phase product plume result of calculation and condensed phase product plume result of calculation in the plume result of calculation of exporting;

Step 4, the gridding of gas-phase product plume data structure are handled, and its processing procedure is as follows:

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

Non-structured grid point extracts on step 402, the axial coordinate axle: adopt and extract all non-structured grid points that are positioned on the axial coordinate axle in the non-structured grid node of described data processor all from the zone of jet flow described in the step 401, the non-structured grid point total quantity of extracting that is positioned on the axial coordinate axle is N _XWherein, the axial coordinate axle is the abscissa axis at the central axis place of described engine jet pipe, the radial coordinate y that is positioned at the non-structured grid point on the axial coordinate axle that extracts in this step _h=0 and its axial coordinate x _h〉=0, wherein h is positive integer, and h=1,2 ..., N _X

Non-structured grid point extracts on step 403, the radial coordinate axle: adopt and extract all non-structured grid points that are positioned on the radial coordinate axle in the non-structured grid node of described data processor all from the zone of jet flow described in the step 401, the non-structured grid point total quantity of extracting in this step that is positioned on the radial coordinate axle is N _{Y goes out}Wherein, the radial coordinate axle is that the axis of ordinates at place, described engine jet pipe exit and the axial coordinate value in engine jet pipe exit are 0, is positioned at the axial coordinate x of the non-structured grid point on the 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 structured grid figure: with N _XBar straight line x=x _hAnd N _{Y goes out}Bar straight line y=y _K1Behind the quadrature, construct one and comprise (N _X-1) * (N _{Y goes out}-1) the structured grid figure of individual rectangular node;

Step 405, the gridding of gas-phase product plume data structure are handled: adopt described data processor that the vapor phase product stream field data on four summits of each rectangular node among the constructed structured grid figure in the step 404 is carried out assignment again respectively; Assignment method is all identical again for the vapor phase product stream field data on each summit in all rectangular nodes, when wherein carrying out again assignment for the vapor phase product stream field data on arbitrary summit of any rectangular node among the constructed structured grid figure, described data processor is found out in all the non-structured grid nodes from the zone of jet flow described in the step 401 earlier with current by the nearest non-structured grid node of assignment vertex distance, and the vapor phase product stream field data of the non-structured grid node found out is composed to current by the summit of assignment;

Step 5, the gridding of condensed phase product plume data structure are handled: described data processor utilizes the particle trajectory data of the M of a structured grid figure different-grain diameter particle constructed in the step 404 to carry out the structured grid processing respectively, and process is as follows:

Step 501, structured grid processing initial parameter are set: adopt described parameter input unit to the value of M and the particle diameter D of M different-grain diameter particle _NrSet respectively; Wherein, r is positive integer, and r=1,2 ..., M; The different-grain diameter number of particles of M for handling;

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

Step 503, engine jet pipe entrance rectangular node quantity are obtained and the up-and-down boundary of each nozzle entry rectangular node is determined: at first, read the flow field data of all non-structured grid nodes in the engine jet pipe zone of designed solid propellant in the gas-phase product plume result of calculation that adopts described data processor to export from step 303; Afterwards, adopt and extract all non-structured grid nodes that are positioned on the straight line x=-Δ d in the non-structured grid node of described data processor all from the engine jet pipe zone of reading, and the non-structured grid point total quantity of extracting that is positioned on the straight line x=-Δ d is N _{Y goes into}Wherein, be positioned at the axial coordinate x of the non-structured grid node on the straight line x=-Δ d _K2=-Δ d and its radial coordinate y _K2〉=0, wherein k2 is positive integer, and k2=1,2 ..., N _{Y goes into}Δ d=d1+d2+d3; The nozzle entry rectangular node quantity of obtaining is (N _{Y goes into}-1) individual, the up-and-down boundary of each nozzle entry rectangular node is respectively two neighbouring straight line y=y _K2

Step 504, the gridding of condensed phase product plume data structure are handled: adopt data processor and with (the N described in the step 503 _{Y goes into}-1) individual nozzle entry rectangular node carries out the processing of particle trajectory structured grid as initial grid respectively, and each nozzle entry rectangular node is all identical as the process that initial grid carries out the processing of particle trajectory structured grid; And, when carrying out the processing of particle trajectory structured grid with any nozzle entry rectangular node as initial grid, all to carrying out the structured grid processing with current institute processing nozzle entry rectangular node respectively as M different-grain diameter particle trajectory of initial grid, and the structured grid disposal route of M different-grain diameter particle trajectory is all identical; Wherein, when arbitrary particle trajectory in M the different-grain diameter particle trajectory carried out the structured grid processing, calculate respectively current handle particle trajectory in described structured grid figure by way of all rectangular nodes in the particle trajectory gridded data, and each rectangular node in the particle trajectory gridded data include 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: in the step 504 to current handle particle trajectory in described structured grid figure by way of all rectangular nodes in particle trajectory gridded data when calculating, according to by way of order before and after the installation position of rectangular node by earlier to after calculate.

Above-mentioned solid propellant plume characteristic virtual test and plume data structure gridding method is characterized in that: M=8 in the 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 the designed SOLID PROPELLANT COMBUSTION that sets in the 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 the step 303 designed solid propellant is carried out plume when calculating, the governing equation of the condensed phase product that adopts is Lagrangian particle model trajectory.

Above-mentioned solid propellant plume characteristic virtual test and plume data structure gridding method is characterized in that: when in the step 504 arbitrary particle trajectory in M the different-grain diameter particle trajectory being carried out the structured grid processing, its processing procedure is as follows:

Step 5041, the initial grid of engine jet pipe entrance are determined and the mass particle flow rate

Calculate: find out the current particle trajectory data of handling 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 the particle trajectory data of finding out and the step 503, the current initial grid of nozzle entry of handling particle trajectory is determined; The data of storing in the file that the file that comprises mass particle file, particle temperature in the particle trajectory data and change with track found out, particle diameter change with track and the time step file of particle trajectory;

After treating that the current initial grid of nozzle entry of handling particle trajectory is determined, described data processor find out the summit one of the initial grid of definite nozzle entry and the vapor phase product stream field data on summit two, and in the vapor phase product stream field data on the summit of finding out, find out the density of gas phase ρ at one place, summit _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 two places, summit _G2With gas phase axial velocity u _G2, wherein summit one is the summit, upper left side of the initial grid of nozzle entry of current processing particle trajectory, and summit two is the summit, lower left of the initial grid of nozzle entry of current processing particle trajectory; Afterwards, described data processor is according to formula

Calculate the current interior mass particle flow rate of the initial grid of nozzle entry of handling particle trajectory; In the formula, M is the different-grain diameter number of particles that the need that set in the step 501 are handled; f _PtogFor the flow rate of condensed phase and gas phase than and

When in the step 1 during Q=1, the n in the formula _xBy being produced Al after the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202 ₂O ₃The equilibrium composition of particle; And when Q in the step 1＞1, the n in the formula _xBe the n described in the step 302 _{Condensed phase}

Be the gas phase flow rate in the initial grid of nozzle entry of current processing particle trajectory, and

In the formula

S wherein _GridArea by the initial grid of nozzle entry of current processing particle trajectory;

Step 5042, the initial grid in engine jet pipe exit are determined: described data processor is according to axial coordinate and the radial coordinate of finding out each tracing point in the current particle trajectory data of handling particle trajectory in the step 5041, and constructed structured grid figure in the integrating step 404, the current particle trajectory of handling is determined at the initial grid in engine jet pipe exit;

Step 5043, the processing of particle trajectory structured grid: described data processor is according to structured grid figure constructed in the step 404, and in the axial coordinate of each tracing point in the particle trajectory data of finding out in the integrating step 5041 and radial coordinate and the step 5042 the determined current particle trajectory of handling at the initial grid in engine jet pipe exit, find out among the described structured grid figure current handle particle trajectory by way of all rectangular nodes, and corresponding calculate by way of each rectangular node in the particle trajectory gridded data; And, current handle particle trajectory by way of all rectangular nodes in the computing method of particle trajectory gridded data all identical, for current handle particle trajectory by way of any rectangular node, the computation process of its particle trajectory gridded data is as follows:

Step I, mass particle are calculated: in described data processor is found out in step 5041 the current mass particle file of handling particle trajectory, find out the current particle trajectory of handling at the mass particle m of engine jet pipe porch _Grain, and the mass particle m in the current institute calculating rectangular node _Grid=m _Grain

Step II, population density are calculated: described data processor is according to formula

Calculate the population density N in the current institute calculating rectangular node _pDt is current the residence time of processing particle trajectory in current institute calculating rectangular node, and dt is the time step sum of current all tracing points of processing particle trajectory in current institute calculating rectangular node; In the formula,

Mass particle flow rate by what calculate in the step 5041 in the initial grid of nozzle entry of current processing particle trajectory;

Step III, particle average quality and medial temperature: described data processor is respectively according to formula With

Calculate the particle average quality D in the current institute calculating rectangular node _pWith particle medial temperature T _pIn the formula, k3 is positive integer, and k3=1,2 ..., K, wherein K is current the tracing point total quantity of processing particle trajectory in current institute calculating rectangular node, and D _Pk3And T _Pk3Be respectively particle diameter and the particle temperature at k3 tracing point place in K the tracing point; Dt is current the residence time of processing particle trajectory in current institute calculating rectangular node;

The step IV, repeatedly the repeating step I is to the step III, until calculate current handle particle trajectory by way of all rectangular nodes in the particle trajectory gridded data;

Step 5044, repeatedly repeating step 5041 is to step 5043, until finishing with the structured grid processing procedure of current institute processing nozzle entry rectangular node as M different-grain diameter particle trajectory of initial grid;

Step 505, repeatedly repeating step 5041 is to step 5044, until finishing with (N _{Y goes into}-1) individual nozzle entry rectangular node is as the particle trajectory structured grid processing procedure of initial grid.

Above-mentioned solid propellant plume characteristic virtual test and plume data structure gridding method is characterized in that: in the step III to the particle average quality D in the current institute calculating rectangular node _pWith particle medial temperature T _pBefore calculating, elder generation is according to up-and-down boundary radial coordinate and border, the left and right sides axial coordinate of current institute calculating rectangular node, and axial coordinate and the radial coordinate of each tracing point in the particle trajectory data of finding out in the integrating step 5041, to current handle particle trajectory in current institute calculating rectangular node tracing point total quantity K and axial coordinate and the radial coordinate of K tracing point determine respectively.

Above-mentioned solid propellant plume characteristic virtual test and plume data structure gridding method, it is characterized in that: in the step 303 designed solid propellant is carried out plume when calculating, the governing equation of the gas-phase product that adopts is 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: in the step 302 to products of combustion when equilibrium composition is set, when in the step 1 during Q=1, the equilibrium composition of m the products of combustion that produces after the designed SOLID PROPELLANT COMBUSTION that calculates in the input step 202 respectively by described parameter input unit, perhaps described data processor call parameters arranges the equilibrium composition that module is transferred out m the products of combustion that produces after the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202 automatically; When Q in the step 1＞1, earlier according to the equilibrium composition of m the products of combustion that produces after the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202, calculate the equilibrium composition sum m of the Q that produces a condensed phase product after the designed SOLID PROPELLANT COMBUSTION _{Condensed phase}Afterwards, import equilibrium composition sum m respectively by described parameter input unit _{Condensed phase}With the equilibrium composition of (m-Q) the individual gas-phase product that produces after the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202, perhaps described data processor call parameters arranges module and transfers out the equilibrium composition sum m that calculates in advance automatically _{Condensed phase}Equilibrium composition with (m-Q) the individual gas-phase product that produces after the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202.

Above-mentioned solid propellant plume characteristic virtual test and plume data structure gridding method, it is characterized in that: after extracting all non-structured grid points that are positioned on the axial coordinate axle in the step 402, described data processor is arranged according to axial coordinate all the non-structured grid points that are positioned on the axial coordinate axle that extract by little extremely big order, and marks from left to right on described axial coordinate axle; After extracting all non-structured grid points that are positioned on the radial coordinate axle in the step 403, described data processor is arranged according to radial coordinate all the non-structured grid points that are positioned on the radial coordinate axle that extract by little extremely big order, and marks 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 of setting up in the step 201 is

In the formula (1): j is positive integer, and j=1,2 ..., A, A are the kind of the contained chemical element of 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 the SOLID PROPELLANT COMBUSTION;

μ wherein _sBe the chemical potential (KJ/mol) of the s kind products of combustion by the input of described parameter input unit in advance, n _sMolal quantity (mol/Kg) and the n of contained s kind products of combustion when being in chemistry balance state after the 1000g SOLID PROPELLANT COMBUSTION _s〉=0, a _SjAtomicity for contained j kind chemical element in the 1mol s kind products of combustion; b _jBe the atomicity of contained j kind chemical element in the 1000g solid propellant, π _jBe Lagrange multiplier;

The chamber temperature computation model of setting up is the adiabatic temperature computation model, and the adiabatic temperature computation model of setting up is

H in the formula (2) _C1Be adiabatic temperature T=T ₁The time the enthalpy of 1000g products of combustion, H _C2Be adiabatic temperature T=T ₂The time the enthalpy of 1000g products of combustion, H _C1＜H _p＜H _C2, and T _C1And T _C2All according to formula

N wherein _sThe molal quantity (mol/Kg) of contained s kind products of combustion when being in chemistry balance state after the 1000g SOLID PROPELLANT COMBUSTION, H _CsBe 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), and T is adiabatic temperature, α _S1, α _S2, α _S3, α _S4, α _S5And α _S6Be the thermodynamic function temperature coefficient of the s kind products of combustion by the input of described parameter input unit in advance; M wherein _iBe the relative molecular mass of the used i kind of preparation solid propellant component, H _iBe the enthalpy of the 1mol i kind component by the input of described parameter input unit in advance, W _iMass percent for the used i kind of preparation solid propellant component.

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

1, simple, the reasonable in design and realization convenience of method step.

2, input cost is low and use easy and simple to handlely, has obviously simplified the formula development process of solid propellant, has shortened the formula development cycle greatly, has significantly reduced the formula development cost.

3, in the solid propellant prescription design process, only need the component information of used each component of input preparation solid propellant, adopt data processor just can carry out plume characteristic virtual test (namely solid propellant being carried out the plume analog computation) to designed solid propellant automatically afterwards, and can carry out the structured grid processing to plume result of calculation automatically, and after the structured grid processing, can utilize result directly to carry out microwave attenuation calculates, 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 guarantee.Treat that microwave attenuation calculates, infrared radiation calculates or photoelectric characteristic calculate finish after, can adjust accordingly according to the prescription of result of calculation to designed solid propellant, thereby provide great convenience for the prescription design of solid propellant.

4, practical value height, can bring very big facility to the formula development process of low signature solid propellant, in the actual mechanical process, after designed solid propellant being carried out automatically the plume analog computation and tackle plume result of calculation mutually to carry out the structured grid processing, can easy, fast and accurately go out to carry out subsequent calculations such as microwave attenuation calculating, infrared radiation calculating or photoelectric characteristic calculating.In the actual mechanical process, only need to adjust the weight proportion of used each component of the designed solid propellant of preparation, data processor just can be finished plume analog computation and structured grid processing procedure automatically, and can calculate according to microwave attenuation, subsequent calculations results such as infrared radiation calculating or photoelectric characteristic calculating, just can be easy, intuitively and accurately draw the weight proportion of used each component of the designed solid propellant of preparation to each Effect on Performance of designed solid propellant, thereby shortened formula development cycle of solid propellant greatly, significantly reduced the formula development cost, for the design of the prescription of solid propellant provides great convenience.

5, result of use is good and popularizing application prospect is extensive, widely applicable, in the optimal design process of the easy input propellant formulation of energy, can finish propellant formulation optimal design process economical, efficiently, and have plurality of advantages such as result accuracy height, processing speed be fast, only need a few minutes just can finish the structured grid processing procedure, practicality is very strong.

In sum, the inventive method step simple, reasonable in design and realize convenient, result of use is good, can finish solid propellant plume characteristic virtual test easy, fast and can become based on the flow field data-switching of non-structured grid based on the corresponding data of structured grid so that subsequent calculations is used.

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

Description of drawings

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.

The method flow block diagram that Fig. 3 handles for gas-phase product plume data structure gridding of the present invention.

The method flow block diagram that Fig. 4 handles for condensed phase product plume data structure gridding of the present invention.

Embodiment

As shown in Figure 1 a kind of solid propellant plume characteristic virtual test and plume data structure gridding method may further comprise the steps:

Step 1, initial parameter are set and storage:

At first, by the parameter input unit of joining with data processor, the component information of designed solid propellant component utilized quantity N and each component is prepared in input, and the information synchronization of importing is stored in the data storage cell that joins 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 used component of the designed solid propellant of preparation; 0＜m _i＜100, m ₁+ m ₂+ ... + m _N=100, N 〉=2.

Afterwards, in the products of combustion database of setting up in advance, select all products of combustion that produce after the designed SOLID PROPELLANT COMBUSTION by described parameter input unit; Store the attribute information of multiple products of combustion in the 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 designed SOLID PROPELLANT COMBUSTION after the quantity m of the products of combustion that produces and the quantity Q of condensed phase product set, and comprise Q condensed phase product and (m-Q) individual gas-phase product in the products of combustion that produces after the designed SOLID PROPELLANT COMBUSTION, wherein m and Q are positive integer, and Q 〉=1; When Q=1, the condensed phase product that is produced in the products of combustion after the designed SOLID PROPELLANT COMBUSTION is Al ₂O ₃Particle.

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

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

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

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

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

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

Step 203, adiabatic combustion temperature are calculated: the chamber temperature computation model of setting up in the described data processor invocation step 201 calculates the adiabatic combustion temperature when being in chemistry balance state after the 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 scope are set: by described parameter input unit geometric parameter and the jet flow computational fields scope of engine jet pipe are set; Wherein, the geometric parameter of engine jet pipe includes port radius r ₁, throat radius r ₂, the outlet radius r ₃, converging portion length d 1, throat's cylindrical section length d 2, angle of flare α and expansion segment length d 3, wherein entry radius r ₁Be the entry radius of engine jet pipe, throat radius r ₂Be the throat radius of engine jet pipe, the outlet radius r ₃The port radius that goes out for engine jet pipe, converging portion length d 1 is the length of engine jet pipe entrance to the nozzle throat front end, throat's cylindrical section length d 2 is the throat length of engine jet pipe, angle of flare α is the wall of engine jet pipe expansion segment and the angle between its axis, and expansion segment length d 3 is the terminal length to nozzle exit of engine jet pipe throat; Jet flow computational fields scope comprises jet flow axial length x _mWith jet flow radical length y _m, jet flow axial length x wherein _mFor engine jet pipe exports to the length d 4 of jet flow lower exit, jet flow radical length y _mFor the engine jet pipe axis arrives the radially length of outer boundary of jet flow, see Fig. 2 for details.

Step 302, firing chamber running parameter are set: at 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, again to products of combustion equilibrium composition set; Then, by described parameter input unit to designed SOLID PROPELLANT COMBUSTION after the Al that produces ₂O ₃The mean grain size D of particle _nSet.

Step 303, engine plume calculate: at first, according to the jet pipe geometric parameter that sets in the step 301 and jet flow computational fields scope, adopt described data processor to set up the two-dimentional axisymmetric model that the inside and outside plume of described engine jet pipe is carried out numerical evaluation; Afterwards, described data processor calls the 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 FULENT software, and the firing chamber running parameter that sets in the jet pipe geometric parameter that sets in the energy response parameter that calculates in the integrating step two, step 301 and jet flow computational fields scope and the step 302, designed solid propellant is carried out plume calculate, and export plume result of calculation automatically.Wherein, comprise gas-phase product plume result of calculation and condensed phase product plume result of calculation in the plume result of calculation of exporting.

In the present embodiment, the FLUENT software that adopts is ANSYS FLUENT software.

In the present embodiment, carry out the engine plume in the step 303 when calculating, gas-phase product governing equation be turbulence model, and described turbulence model adopts the k-ε model (being Realizable k-ε turbulent model) of the correction of two equations.The grid that adopts in the plume computational fields grid chart of the designed solid propellant that GAMBIT software generates is rectangular node.

And, in the step 303 designed solid propellant being carried out plume when calculating, the governing equation of the condensed phase product that adopts is Lagrangian particle model trajectory.

In addition, carry out in the step 303 also needing to import by described parameter input unit earlier the finite rate Chemical Reaction Model of products of combustion before the calculating of engine plume.The finite rate Chemical Reaction Model of importing, with in the step 1 by described parameter input unit in the products of combustion database of setting up in advance, select the products of combustion that produces after the SOLID PROPELLANT COMBUSTION of estimating corresponding.

The actual plume that carries out is when calculating, during the finite rate Chemical Reaction Model of input products of combustion, with reference to the Wang Sunyuan chief editor who published in 1991 " Tao Yang that the Zhao Jianhang chief editor's that rocket charge thermal performance handbook, Science Press in 2002 publish " numerical simulation of burning " or 2008 09 month publishing house of the National University of Defense technology publish, Fang Dingxi, Tang Qiangang chief editor's documents such as " the rocket engine theories of combustion " are determined the finite rate Chemical Reaction Model of importing.

For example, in the products of combustion that produces after the SOLID PROPELLANT COMBUSTION, comprise O ₂, H ₂O, CO, CO ₂, H, H ₂, O, OH, N ₂Deng 9 gaseous components with coagulate phase component Al ₂O ₃The time, Chemical Reaction Model is the chemical dynamic model of 9 components, 10 reactions, and the chemical dynamic model of 9 components, 10 reactions of adopting sees table 1 for details:

The chemical dynamic model reaction mechanism tables of data of table 19 component 10 reactions

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

In the products of combustion that produces after the 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 with coagulate phase component Al ₂O ₃The time, Chemical Reaction Model is the chemical dynamic model of 12 components 17, and the chemical dynamic model of 12 components, 17 reactions of adopting sees table 2 for details:

The chemical dynamic model reaction mechanism tables of data of table 212 component 17 reactions

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

In the present embodiment, the gas-phase product plume result of calculation of exporting in the step 303 is the result of calculation that is stored in * _ tec.dat file, and * _ tec.dat file is finished the back text of the Tecplot form of preservation automatically for FULENT software calculates.

For example, in the products of combustion that produces after the designed SOLID PROPELLANT COMBUSTION, comprise O ₂, H ₂O, CO, CO ₂, H, H ₂, O, OH, N ₂Deng 9 gaseous components with coagulate phase component Al ₂O ₃The time, shown in preceding 3 row of * _ tec.dat file the contents 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"

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

The 1st row is the file header of fixing with the TITLE beginning.

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

The 3rd row is with the VARIABLES beginning, and N=17841 thereafter is the information of unique care in the step 401, represents and has 17841 non-structured grid points in the plume.

Be 29 continuous flow field variable data pieces since the 4th row, at first be the axial coordinate data (corresponding the 1st to N non-structured grid point successively) of N non-structured grid point, next be the radial coordinate data of N non-structured grid point ..., be N O at last ₂Component source item number certificate.Between the text data with single space-separated, and for having the exponential scheme of 5 position effective digitals behind the radix point.

In the present embodiment, the flow field data of all non-structured grid nodes are the data of storing in * _ tec.dat file in the designed solid propellant jet flow zone that reads out in the step 401.

And the flow field data that read comprise non-structured grid number of spots N and a plurality of flow fields variable data piece corresponding with N non-structured grid point respectively.In the present embodiment, the flow field data that read comprise non-structured grid number of spots N=17841 with respectively with 17841 29 flow field variable data pieces that non-structured grid point is corresponding.

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

In the present embodiment, F2=m-Q=9.And F=F1+F2=16.And 16 dynamic one-dimension array are respectively applied to store the axial coordinate of N non-structured grid point, radial coordinate, temperature, pressure, OH component mole fraction, H ₂The component mole fraction, CO component mole fraction, CO ₂The component mole fraction, H ₂O component mole fraction, O ₂The component mole fraction, O component mole fraction, H component mole fraction, N ₂The component mole fraction, condensed phase concentration, vapor axial speed and density of gas phase; After 16 dynamic one-dimension array are created, from * _ tec.dat file, read corresponding data and store.And the quantity of the data of storing is N in 16 dynamic one-dimension array.

Wherein, abscissa axis and axis of ordinates form a two-dimentional rectangular coordinate system.

Step 404, structure structured grid figure: with N _XBar straight line x=x _hAnd N _{Y goes out}Bar straight line y=y _K1Behind the quadrature, construct one and comprise (N _X-1) * (N _{Y goes out}-1) the structured grid figure of individual rectangular node; Wherein, h=1,2 ..., N _XK1=1,2 ..., N _{Y goes out}

In the present embodiment, after extracting all non-structured grid points that are positioned on the axial coordinate axle in the step 402, described data processor is arranged according to axial coordinate all the non-structured grid points that are positioned on the axial coordinate axle that extract by little extremely big order, and marks from left to right on described axial coordinate axle; After extracting all non-structured grid points that are positioned on the radial coordinate axle in the step 403, described data processor is arranged according to radial coordinate all the non-structured grid points that are positioned on the radial coordinate axle that extract by little extremely big order, and marks from the bottom to top on described radial coordinate axle.

In the present embodiment, described jet flow zone is a rectangular area, and its a plurality of rectangular nodes by axial coordinate 〉=0 in the plume computational fields grid chart of GAMBIT software generation are formed.Because the outer boundary in jet flow zone overlaps in the outer boundary that is transformed into the jet flow zone behind the structured grid figure and the plume computational fields grid chart of GAMBIT software generation.Therefore, at first determine (radial coordinate=0 on the abscissa axis, axial coordinate 〉=0) the non-structured grid point of all, above-mentioned non-structured grid point is by all the non-structured grid nodes in the described jet flow of the traversal zone, and extract and satisfy radial coordinate=0, the non-structured grid node of all of axial coordinate 〉=0 and sort from small to large according to axial coordinate after obtain; Afterwards, determine axis of ordinates (radial coordinate 〉=0, axial coordinate=0) the non-structured grid point of all on, above-mentioned non-structured grid point is by all the non-structured grid nodes in the described jet flow of the traversal zone, and extract and satisfy radial coordinate 〉=0, the non-structured grid node of all of axial coordinate=0 also sorts to obtain according to radial coordinate from small to large.

After treating that all non-structured grid points on the abscissa axis and all the non-structured grid points on the axis of ordinates are all determined, just can construct structured grid figure according to the form of the orthogonal grid of straight line orthorhombic form, the quantity of rectangular node is (N among the constructed structured grid figure _X-1) * (N _{Y goes out}-1) individual, and four summits of each rectangular node are the structured grid point, and the quantity of structured grid point is N among the constructed structured grid figure _X* N _{Y goes out}Individual.

Step 405, the gridding of gas-phase product plume data structure are handled: adopt described data processor that the vapor phase product stream field data on four summits of each rectangular node among the constructed structured grid figure in the step 404 is carried out assignment again respectively; Assignment method is all identical again for the vapor phase product stream field data on each summit in all rectangular nodes, when wherein carrying out again assignment for the vapor phase product stream field data on arbitrary summit of any rectangular node among the constructed structured grid figure, described data processor is found out in all the non-structured grid nodes from the zone of jet flow described in the step 401 earlier with current by the nearest non-structured grid node of assignment vertex distance, and the vapor phase product stream field data of the non-structured grid node found out is composed to current by the summit of assignment.

Wherein, the method flow block diagram that the present invention adopts the gridding of gas-phase product plume data structure to handle sees Fig. 3 for details.

In the present embodiment, when carrying out gas-phase product plume data structure gridding processing in the step 405, need N among the constructed structured grid figure _X* N _{Y goes out}Individual structured grid point carries out assignment again respectively.And, the principle of each structured grid point being carried out again assignment is: filter out in the non-structured grid node of all from described jet flow zone from the nearest non-structured grid node of this structured grid point, and the flow field data of the burn non-structured grid node of selecting are composed to this structured grid point.

In the present embodiment, after finishing the gridding of gas-phase product plume data structure in the step 405 and handling, also need the result stores synchronized to the data storage cell that joins with described data processor.

Step 501, structured grid processing initial parameter are set: adopt described parameter input unit to the value of M and the particle diameter D of M different-grain diameter particle _NrSet respectively; Wherein, r is positive integer, and r=1,2 ..., M.

In the present embodiment, M=8 in the 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 the designed SOLID PROPELLANT COMBUSTION that sets in the step 302 ₂O ₃The mean grain size of particle.

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

Actual particle diameter D to M different-grain diameter particle _NrWhen setting, with reference to the Al that produces after the designed SOLID PROPELLANT COMBUSTION that sets in the step 302 ₂O ₃The mean grain size D of particle _nSetting, specifically is at mean grain size D _nThe left and right sides respectively symmetry choose a plurality of particle diameters.That is to say, in the particle diameter distribution field that adopts FLUNT software to calculate, at mean grain size D _nThe left and right sides respectively symmetry choose a plurality of particle diameters.

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

In the present embodiment, the file that the mass particle file that reads, particle temperature change with track, particle diameter are respectively * _ mass.fvp, * _ temp.fvp, * _ diam.fvp and * _ time.fvp file of preserving automatically after the calculating of FULENT software is finished with the file of track variation and the time step file of particle trajectory.

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

FVPARTICLES 2 1

Tag Names

0

Variable Names

2

Particle Time Step

particle_id

Except the 6th row represents name variable (Particle Time Step) and different, other 3 * .fvp(are that the file header of * _ mass.fvp, * _ temp.fvp and * _ diam.fvp) is identical.From eighth row opening entry particle trajectory data, the contents are as follows:

1141

-0.0496738 0.0248277 0 0 0

-0.0495869 0.0248273 0 7.74289e-006 0

-0.0491527 0.0248255 0 3.87144e-005 0

-0.0491265 0.0248254 0 2.3338e-006 0

-0.0486923 0.0248235 0 3.87165e-005 0

Eighth row is 1 integer, represents total track on this track NL (namely 1141) that counts.So since the 9th the row 1141 line items the data of 1141 tracing points, every row is made of 5 fields.Preceding 3 fields represent the x of this point respectively, y, and the z coordinate, for two-dimensional case z=0, the 4th field is the time step at this tracing point place, the 5th sequence number (since 0) that field is this track.Article 1, track then is the data segment of the 2nd track after finishing, and the data segment of every track represents from the data of the NL behavior identical strip path curve of following 1 row beginning all only to comprise the row beginning of an integer (NL).

Step 503, engine jet pipe entrance rectangular node quantity are obtained and the up-and-down boundary of each nozzle entry rectangular node is determined: at first, read the flow field data of all non-structured grid nodes in the engine jet pipe zone of designed solid propellant in the gas-phase product plume result of calculation that adopts described data processor to export from step 303; Afterwards, adopt and extract all non-structured grid nodes that are positioned on the straight line x=-Δ d in the non-structured grid node of described data processor all from the engine jet pipe zone of reading, and the non-structured grid point total quantity of extracting that is positioned on the straight line x=-Δ d is N _{Y goes into}Wherein, be positioned at the axial coordinate x of the non-structured grid node on the straight line x=-Δ d _K2=-Δ d and its radial coordinate y _K2〉=0, wherein k2 is positive integer, and k2=1,2 ..., N _{Y goes into}Δ d=d1+d2+d3; The nozzle entry rectangular node quantity of obtaining is (N _{Y goes into}-1) individual, the up-and-down boundary of each nozzle entry rectangular node is respectively two neighbouring straight line y=y _K2Wherein, the rectangular node of described engine jet pipe porch is the nozzle entry rectangular node.

In the present embodiment, before engine jet pipe entrance rectangular node quantity obtained, earlier at described engine jet pipe internal build structured grid, and when described engine jet pipe internal build structured grid, adopt earlier and extract all non-structured grid nodes that are positioned on the straight line x=-Δ d in the non-structured grid node of described data processor all from the engine jet pipe zone of reading, and the non-structured grid point total quantity of extracting that is positioned on the straight line x=-Δ d is N _{Y goes into}, the radial coordinate y that is positioned at the non-structured grid point on the straight line x=-Δ d that extracts _{K goes into}〉=0, wherein k goes into to be positive integer, and k go into=1,2 ..., N _{Y goes into}Afterwards, adopt in the non-structured grid node of described data processor all from the engine jet pipe zone of reading, extract all non-structured grid points that are positioned on the axle of axial coordinate described in the step 402, the non-structured grid point total quantity of extracting that is positioned on the axial coordinate axle is N _{The X pipe}, the radial coordinate y that is positioned at the non-structured grid point on the axial coordinate axle that extract this moment _{The h pipe}=0 and its axial coordinate x _{The h pipe}≤ 0, wherein the h pipe is negative integer, and h pipe=-1 ,-2 ... ,-N _{The X pipe}+ 1 ,-N _{The X pipe}With N _{The X pipe}Bar straight line x=x _{The h pipe}And N _{Y goes into}Bar straight line y=y _{K goes into}Behind the quadrature, construct one and comprise (N _{The X pipe}-1) * (N _{Y goes into}-1) the structured grid figure of individual rectangular node.

Wherein, when h pipe=-N _{The X pipe}The time, x _{The h pipe}=-Δ d; When h pipe=-N _{The X pipe}+ 1 o'clock, x _{The h pipe}=c1.And, straight line x=-Δ d, straight line x=c1 and N _{Y goes into}Bar straight line y=y _{K goes into}Described engine jet pipe porch is divided into (N _{Y goes into}-1) individual rectangular node.

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

Wherein, c1 be the described engine jet pipe inside of extracting be positioned on the described axial coordinate axle and with the abscissa value of the nearest non-structured grid point of described engine jet pipe entrance.

Because all particle trajectories all originate from the engine jet pipe entrance in the engine jet pipe plume, 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, and wherein the boundary line, the left side of each nozzle entry rectangular node all is positioned on the axis of ordinates.In the present embodiment, when carrying out condensed phase product plume data structure gridding processing in the step 504, the particle trajectory total quantity that needs to handle is M * (N _{Y goes into}-1) bar, wherein the quantity of handling particle trajectory as the need of initial grid with each nozzle entry rectangular node is the M bar.

In the present embodiment, finish the gridding of condensed phase product plume data structure in the step 504 and handle, also need and to handle M * (N that the back obtains _{Y goes into}-1) the equal stores synchronized of structured grid result of bar particle trajectory is to described data storage cell.

In the present embodiment, in the step 504 to current handle particle trajectory in described structured grid figure by way of all rectangular nodes in particle trajectory gridded data when calculating, according to by way of order before and after the installation position of rectangular node by earlier to after calculate.

In the present embodiment, when in the step 504 arbitrary particle trajectory in M the different-grain diameter particle trajectory being carried out the structured grid processing, its processing procedure is as follows:

Calculate: find out the current particle trajectory data of handling 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 the particle trajectory data of finding out and the step 503, the current initial grid of nozzle entry of handling particle trajectory is determined wherein the current initial grid of nozzle entry of handling particle trajectory is the initial grid of current processing particle trajectory in the engine jet pipe porch; The data of storing in the file that the file that comprises mass particle file, particle temperature in the particle trajectory data and change with track found out, particle diameter change with track and the time step file of particle trajectory.

Calculate the current interior mass particle flow rate of the initial grid of nozzle entry of handling particle trajectory; In the formula, M is the different-grain diameter number of particles that the need that set in the step 501 are handled; f _PtogFor the flow rate of condensed phase and gas phase than and When in the step 1 during Q=1, the n in the formula _xBy being produced Al after the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202 ₂O ₃The equilibrium composition of particle; And when Q in the step 1＞1, the n in the formula _xBe the n described in the step 302 _{Condensed phase}

In the formula

S wherein _GridArea by the initial grid of nozzle entry of current processing particle trajectory.

That is to say, in the present embodiment, when carrying out in the step 303 carrying out condensed phase product plume data structure gridding processing in the calculating of engine plume and the step 5, in the products of combustion that produces after the designed SOLID PROPELLANT COMBUSTION, comprise except Al ₂O ₃During other type condensed phase product of particle and so on, all other type condensed phase product is used as Al ₂O ₃Particle is handled, and has so not only reduced calculated amount significantly, and the harmful effect that the accuracy of plume result of calculation and condensed phase product plume data structure gridding result is caused is very little.

Wherein, described data processor find out the summit one of the initial grid of definite nozzle entry and the vapor phase product stream field data on summit two, be respectively after the gridding of gas-phase product plume data structure is finished dealing with in the step 405, the summit one of the current initial grid of nozzle entry of handling particle trajectory and summit two be the vapor phase product stream field data after the assignment again separately.

Step 5042, the initial grid in engine jet pipe exit (being the jet flow porch) are determined: described data processor is according to axial coordinate and the radial coordinate of finding out each tracing point in the current particle trajectory data of handling particle trajectory in the step 5041, and constructed structured grid figure in the integrating step 404, the current particle trajectory of handling is determined at the initial grid in engine jet pipe exit.

In the present embodiment, the current particle trajectory of handling when the initial grid in engine jet pipe exit is determined, is traveled through current all tracing points of handling on the particle trajectory, and the corresponding radial coordinate R that finds out first tracing point of axial coordinate 〉=0 _P0, then according to R _P0The current jet flow entrance grid (being the initial grid in engine jet pipe exit) of handling particle trajectory is determined.

Since on each bar particle trajectory mass particle remain constant, thereby current handle particle trajectory by way of all rectangular nodes in mass particle remain constantly, and be equal to m _Grain

Calculate the population density N in the current institute calculating rectangular node _pDt is current the residence time of processing particle trajectory in current institute calculating rectangular node, and dt is the time step sum of current all tracing points of processing particle trajectory in current institute calculating rectangular node; In the formula, Mass particle flow rate by what calculate in the step 5041 in the initial grid of nozzle entry of current processing particle trajectory.

Step III, particle average quality and medial temperature: described data processor is respectively according to formula

With

Calculate the particle average quality D in the current institute calculating rectangular node _pWith particle medial temperature T _pIn the formula, k3 is positive integer, and k3=1,2 ..., K, wherein K is current the tracing point total quantity of processing particle trajectory in current institute calculating rectangular node, and D _Pk3And T _Pk3Be respectively particle diameter and the particle temperature at k3 tracing point place in K the tracing point; Dt is current the residence time of processing particle trajectory in current institute calculating rectangular node.

In the present embodiment, in the step III to the particle average quality D in the current institute calculating rectangular node _pWith particle medial temperature T _pWhen calculating, elder generation is according to up-and-down boundary radial coordinate and border, the left and right sides axial coordinate of current institute calculating rectangular node, and axial coordinate and the radial coordinate of each tracing point in the particle trajectory data of finding out in the integrating step 5041, to current handle particle trajectory in current institute calculating rectangular node tracing point total quantity K and axial coordinate and the radial coordinate of K tracing point determine respectively.

Actual to current when handling the tracing point total quantity K of particle trajectory in current institute calculating rectangular node and determining, travel through the current tracing point of handling on the particle trajectory, and find out axial coordinate between border, the left and right sides axial coordinate of current institute calculating rectangular node and the tracing point of radial coordinate between the up-and-down boundary radial coordinate of current institute calculating rectangular node.K tracing point is divided into a plurality of orbit segments with the current particle trajectory of handling in the current institute calculating rectangular node, and the time step sum of a plurality of described orbit segments (being the time step sum of K tracing point) just is dt.

Wherein, the method flow block diagram that the present invention adopts the gridding of condensed phase product plume data structure to handle sees Fig. 4 for details.

In the present embodiment, to products of combustion when equilibrium composition is set, the products of combustion equilibrium composition that sets is for according to gibbs minimum free energy principle in the step 302, and the chemical equilibrium that calculates products of combustion is formed.

In the present embodiment, in the step 302 to products of combustion when equilibrium composition is set, when in the step 1 during Q=1, the equilibrium composition of m the products of combustion that produces after the designed SOLID PROPELLANT COMBUSTION that calculates in the input step 202 respectively by described parameter input unit, perhaps described data processor call parameters arranges the equilibrium composition that module is transferred out m the products of combustion that produces after the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202 automatically; When Q in the step 1＞1, earlier according to the equilibrium composition of m the products of combustion that produces after the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202, calculate the equilibrium composition sum m of the Q that produces a condensed phase product after the designed SOLID PROPELLANT COMBUSTION _{Condensed phase}Afterwards, import equilibrium composition sum m respectively by described parameter input unit _{Condensed phase}With the equilibrium composition of (m-Q) the individual gas-phase product that produces after the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202, perhaps described data processor call parameters arranges module and transfers out the equilibrium composition sum m that calculates in advance automatically _{Condensed phase}Equilibrium composition with (m-Q) the individual gas-phase product that produces after the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202.

According to thermodynamic principles, the products of combustion of solid propellant can be considered ideal gas under hot conditions, then the free energy of total 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 minimum of system.Therefore, under certain pressure and temperature condition, obtain a component value that can make system free energy minimum meet law of conservation of mass again, then this group component value is the products of combustion equilibrium composition of system under this condition.The summation of its free energy function is minimum principle when reaching chemical equilibrium according to system, adopts the mathematical method of convergence rapidly, can separate the chemical equilibrium of any complication system by iteration and form.

In the present embodiment, the minimum free energy mathematical model of setting up in the step 201 is In the formula (1): j is positive integer, and j=1,2 ..., A, A are the kind of the contained chemical element of 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 the SOLID PROPELLANT COMBUSTION;

μ wherein _sBe the chemical potential (KJ/mol) of the s kind products of combustion by the input of described parameter input unit in advance, n _sMolal quantity (mol/Kg) and the n of contained s kind products of combustion when being in chemistry balance state after the 1000g SOLID PROPELLANT COMBUSTION _s〉=0, a _SjAtomicity for contained j kind chemical element in the 1mol s kind products of combustion; b _jBe the atomicity of contained j kind chemical element in the 1000g solid propellant, π _jBe Lagrange multiplier.

During actual the use, Free energy Minimization is obtained exactly at the one group of n that satisfies under formula (1) condition _sValue makes system free energy minimum, wherein s=1,2 ... m, and n _s〉=0, this is the constrained extremal problem of multivariate function, then can find the solution with lagrange's method of multipliers.

When reality is found the solution the chemical equilibrium composition, also can adopt Henan science tech publishing house in " chemical propellant calculating energy " book by Tian Deyu, Liu Jianhong work of publishing in 1999, the chemical equilibrium that the 6.3rd joint in the chapter 6 " fundamental equation that energy response is calculated " was put down in writing in " chemical equilibrium that contains the condensed phase products of combustion is formed " is formed computing method and is calculated.

The chamber temperature computation model of setting up is the adiabatic temperature computation model, and the adiabatic temperature computation model of setting up is H in the formula (2) _C1Be adiabatic temperature T=T ₁The time the enthalpy of 1000g products of combustion, H _C2Be adiabatic temperature T=T ₂The time the enthalpy of 1000g products of combustion, H _C1＜H _p＜H _C2, and T _C1And T _C2All according to formula

N wherein _sThe molal quantity (mol/Kg) of contained s kind products of combustion when being in chemistry balance state after the 1000g SOLID PROPELLANT COMBUSTION, H _CsBe 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), and T is adiabatic temperature, α _S1, α _S2, α _S3, α _S4, α _S5And α _S6Be the thermodynamic function temperature coefficient of the s kind products of combustion by the input of described parameter input unit in advance;

M wherein _iBe the relative molecular mass of the used i kind of preparation solid propellant component, H _iBe the enthalpy of the 1mol i kind component by the input of described parameter input unit in advance, W _iMass percent for the used i kind of preparation solid propellant component.

In the present embodiment, when carrying out equilibrium composition calculating in the step 202, described data processor call parameters computing module is according to chemical formula and the quality proportioning m of used each component of the designed solid propellant of the preparation of importing in the step 1 _i, and in conjunction with the relative molecular mass of each component, to a _SjAnd b _jCalculate; Afterwards, described data processor is in conjunction with the μ that imports in advance _sAnd π _j, and according to formula

Calculate n _s, just obtain the products of combustion equilibrium composition after the designed SOLID PROPELLANT COMBUSTION this moment;

When carrying out adiabatic combustion temperature calculating in the step 203, the products of combustion equilibrium composition after the designed SOLID PROPELLANT COMBUSTION that calculates in the described data processor integrating step 202, and according to formula

Calculate chamber temperature T _cWherein,

M wherein _iFor preparing the relative molecular mass of the used i kind of designed solid propellant component, H _iBe the enthalpy of 1mol i kind component, W _iFor preparing the mass percent of the used i kind of designed solid propellant component.Wherein, W _iQuality proportioning m with used each component of the input designed solid propellant of preparation in the step 1 _iConsistent.

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

Claims

1. a solid propellant plume characteristic virtual test and plume data structure gridding method is characterized in that this method may further comprise the steps:

Step 1, initial parameter are set and storage:

At first, by the parameter input unit of joining with data processor, the component information of designed solid propellant component utilized quantity N and each component is prepared in input, and the information synchronization of importing is stored in the data storage cell that joins 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 used component of the designed solid propellant 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, the gridding of gas-phase product plume data structure are handled: adopt described data processor that the vapor phase product stream field data on four summits of each rectangular node among the constructed structured grid figure in the step 404 is carried out assignment again respectively; Assignment method is all identical again for the vapor phase product stream field data on each summit in all rectangular nodes, when wherein carrying out again assignment for the vapor phase product stream field data on arbitrary summit of any rectangular node among the constructed structured grid figure, described data processor is found out in all the non-structured grid nodes in the zone of jet flow described in the step 401 earlier with current by the nearest non-structured grid node of assignment vertex distance, and the vapor phase product stream field data of the non-structured grid node found out is composed to current by the summit of assignment;

Step 501, structured grid processing initial parameter are set: adopt described parameter input unit to the value of M and the particle diameter D of M different-grain diameter particle _NrSet respectively; Wherein, r is positive integer, and r=1,2 ..., M;

2. according to the described solid propellant plume of claim 1 characteristic virtual test and plume data structure gridding method, it is characterized in that: in the step 504 to current handle particle trajectory in described structured grid figure by way of all rectangular nodes in particle trajectory gridded data when calculating, according to by way of order before and after the installation position of rectangular node by earlier to after calculate.

3. according to claim 1 or 2 described solid propellant plume characteristic virtual test and plume data structure gridding methods, it is characterized in that: M=8 in the 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 the designed SOLID PROPELLANT COMBUSTION that sets in the step 302 ₂O ₃The mean grain size of particle.

4. according to claim 1 or 2 described solid propellant plume characteristic virtual test and plume data structure gridding methods, it is characterized in that: in the step 303 designed solid propellant is carried out plume when calculating, the governing equation of the condensed phase product that adopts is Lagrangian particle model trajectory.

5. according to the described solid propellant plume of claim 4 characteristic virtual test and plume data structure gridding method, it is characterized in that: when in the step 504 arbitrary particle trajectory in M the different-grain diameter particle trajectory being carried out the structured grid processing, its processing procedure is as follows:

When in the step 1 during Q=1, the n in the formula _xBy being produced Al after the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202 ₂O ₃The equilibrium composition of particle; And when Q in the step 1＞1, n in the formula _xBe the n described in the step 302 _{Condensed phase}

In the formula

Calculate the population density N in the current institute calculating rectangular node _pDt is current the residence time of processing particle trajectory in current institute calculating rectangular node, and dt is the time step sum of current all tracing points of processing particle trajectory in current institute calculating rectangular node; In the formula, Mass particle flow rate by what calculate in the step 5041 in the initial grid of nozzle entry of current processing particle trajectory;

With

6. according to the described solid propellant plume of claim 5 characteristic virtual test and plume data structure gridding method, it is characterized in that: in the step III to the particle average quality D in the current institute calculating rectangular node _pWith particle medial temperature T _pBefore calculating, elder generation is according to up-and-down boundary radial coordinate and border, the left and right sides axial coordinate of current institute calculating rectangular node, and axial coordinate and the radial coordinate of each tracing point in the particle trajectory data of finding out in the integrating step 5041, to current handle particle trajectory in current institute calculating rectangular node tracing point total quantity K and axial coordinate and the radial coordinate of K tracing point determine respectively.

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

8. according to claim 1 or 2 described solid propellant plume characteristic virtual test and plume data structure gridding methods, it is characterized in that: in the step 302 to products of combustion when equilibrium composition is set, when in the step 1 during Q=1, the equilibrium composition of m the products of combustion that produces after the designed SOLID PROPELLANT COMBUSTION that calculates in the input step 202 respectively by described parameter input unit, perhaps described data processor call parameters arranges the equilibrium composition that module is transferred out m the products of combustion that produces after the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202 automatically; When Q in the step 1＞1, earlier according to the equilibrium composition of m the products of combustion that produces after the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202, calculate the equilibrium composition sum n of the Q that produces a condensed phase product after the designed SOLID PROPELLANT COMBUSTION _{Condensed phase}Afterwards, import equilibrium composition sum m respectively by described parameter input unit _{Condensed phase}With the equilibrium composition of (m-Q) the individual gas-phase product that produces after the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202, perhaps described data processor call parameters arranges module and transfers out the equilibrium composition sum m that calculates in advance automatically _{Condensed phase}Equilibrium composition with (m-Q) the individual gas-phase product that produces after the designed SOLID PROPELLANT COMBUSTION that calculates in the step 202.

9. according to claim 1 or 2 described solid propellant plume characteristic virtual test and plume data structure gridding methods, it is characterized in that: after extracting all non-structured grid points that are positioned on the axial coordinate axle in the step 402, described data processor is arranged according to axial coordinate all the non-structured grid points that are positioned on the axial coordinate axle that extract by little extremely big order, and marks from left to right on described axial coordinate axle; After extracting all non-structured grid points that are positioned on the radial coordinate axle in the step 403, described data processor is arranged according to radial coordinate all the non-structured grid points that are positioned on the radial coordinate axle that extract by little extremely big order, and marks from the bottom to top on described radial coordinate axle.

10. according to claim 1 or 2 described solid propellant plume characteristic virtual test and plume data structure gridding methods, it is characterized in that: the minimum free energy mathematical model of setting up in the step 201 is

H in the formula (2) _C1Be adiabatic temperature T=T ₁The time the enthalpy of 1000g products of combustion, H _C2Be adiabatic temperature T=T ₂The time the enthalpy of 1000g products of combustion, H _C1＜H _p＜H _C2, and T _C1And T _C2All according to formula N wherein _sThe molal quantity (mol/Kg) of contained s kind products of combustion when being in chemistry balance state after the 1000g SOLID PROPELLANT COMBUSTION, H _CsBe 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), and T is adiabatic temperature, α _S1, α _S2, α _S3, α _S4, α _S5And α _S6Be the thermodynamic function temperature coefficient of the s kind products of combustion by the input of described parameter input unit in advance;