CN103279616A - Virtual test method for influence of solid propellant smoke upon visible-light guidance signals - Google Patents

Abstract

The invention discloses a virtual test method for influence of solid propellant smoke upon visible-light guidance signals. The method includes the steps of firstly, calculating a plume field and storing data; structurally gridding gaseous product plume field data; thirdly, structurally gridding condensed-phase product plume field data; fourthly, performing virtual test on influence upon visible-light guidance signals, namely setting initial parameters, determining incoming direction of the guidance signals, determining particle trajectories in a guidance signal influence grid, calculating particle trajectory gridded data, converting attenuation coefficients of the particle trajectories, and calculating attenuation coefficients of visible-light guidance signals in the incoming direction. The method has the advantages that the steps are simple, the design is reasonable, the method is convenient to implement and effective in using, and the results of influence of the solid propellant smoke upon the visible-light guidance signals can be acquired simply, quickly and accurately.

Description

A kind of solid propellant smog influences visible light guidance signal virtual test method

Technical field

The invention belongs to solid propellant smog optical guidance effect of signals studying technological domain, especially relating to a kind of solid propellant smog influences visible light guidance signal virtual test 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 largely.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.That guidance signal usually adopts is infrared, ultraviolet, laser, visible light etc.Nowadays, the visible light system has begun to be widely used in guided weapon system, and automaticity and attack precision that it has significantly improved armament systems have promoted the fighting efficiency that plays the arrow armament systems largely.

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.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 institute's test solid propellant calculates, just can export * .out file automatically and use for microwave attenuation calculating, infrared radiation calculating and photoelectric characteristic calculating.The characteristic signal of rocket exhaust plume (Exhaust Plume Signature) is a kind of term that includes system or rocket engine exhaust over-all properties or characteristic, and this performance or characteristic can be used as flat pad or the guided missile that detection, identification or interception are executed the task.The characteristic signal characteristic of plume mainly comprises 4 parameters such as the distributing of cigarette, radiation energy, visibility (visual range/visibility distance) and radar wave absorption.Solid propellant smog is the important characterization parameter of plume characteristic signal, it can be subdivided into from appearance features: smog and secondary smog, one time smog mainly is made of the phase particle that coagulates of rocket tube ejection, main existence form is metal hydroxides, oxide and chloride etc., the metal oxide (Al that the metal powder in the composite propellant (aluminium, magnesium etc.) burning produces ₂O ₃, MgO etc.) be the main source of a smog; Secondary smog is made up of condensable gas in the combustion gas, is the result of combustion gas and atmospheric interaction.Form HCl, HF after AP in the composite propellant and the fluorine component combustion decomposition, under specific temperature and humidity condition, the azeotropic drop smoke, mists and clouds of combine with air formation water and HCl, HF.

But nowadays 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 bring enormous economic loss and political fallout, nowadays press 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, by the actual tests requirement mathematical model that flows based on SOLID PROPELLANT COMBUSTION, products of combustion and visible light guidance signal are passed through the solid propellant plume and carry out microcomputer modelling and find the solution, not only can be used as the preliminary preparation of true test or substitute traditional test (as some limiting conditions) to a certain extent; 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.

Summary of the invention

Technical matters to be solved by this invention is at above-mentioned deficiency of the prior art, provide a kind of solid propellant smog to influence visible light guidance signal virtual test method, its method step simple, reasonable in design and realize convenient, result of use is good, can be easy, fast and accurately obtain solid propellant smog to the result that influences of visible light guidance signal.

For solving the problems of the technologies described above, the technical solution used in the present invention is: a kind of solid propellant smog influences visible light guidance signal virtual test method, it is characterized in that this method may further comprise the steps:

Step 1, plume are calculated and the data storage: adopt data processor to call FULENT software institute's test solid propellant is carried out exporting and be stored to plume result of calculation in the data storage cell that joins with described data processor automatically after plume calculates; 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 2, the gridding of gas-phase product plume data structure are handled, and its processing procedure is as follows:

Step 201, jet flow zone vapor phase product stream field data reads: adopt in the gas-phase product plume result of calculation that described data processor exports from step 1, read the vapor phase product stream field data of all non-structured grid nodes in the jet flow zone; Described jet flow zone is the rectangular area at used engine jet pipe outlet rear when plume calculates in the step 1;

Non-structured grid point extracts on step 202, the axial coordinate axle: adopt the non-structured grid node of described data processor all in the zone of jet flow described in the step 201, extraction is positioned at all the non-structured grid points on the axial coordinate axle, and the non-structured grid point total quantity of extracting in this step 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, is positioned at the radial coordinate y of the non-structured grid point on the axial coordinate axle _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 203, the radial coordinate axle: adopt the non-structured grid node of described data processor all in the zone of jet flow described in the step 201, extraction is positioned at all the non-structured grid points on the radial coordinate axle, and the non-structured grid point total quantity of extracting 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 204, 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 205, 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 204 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 201 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 3, 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 204 to carry out the structured grid processing respectively, and process is as follows:

Step 301, 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;

Step 302, 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 1, to export; Wherein, the condensed phase product plume result of calculation that reads comprises that particle diameter is with the file of track variation and the time step file of particle trajectory;

Step 303, 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 in the gas-phase product plume result of calculation that adopts described data processor to export from step 1; Afterwards, adopt and extract all non-structured grid nodes that are positioned on the straight line x=-Δ d the non-structured grid node of described data processor all in the engine jet pipe zone of reading, 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 is that described engine jet pipe entrance is to the distance between the nozzle exit; The rectangular node that is positioned at described engine jet pipe porch in the step 204 among the constructed structured grid figure is the nozzle entry rectangular node, and described nozzle entry rectangular node quantity 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 4, visible light guidance signal influence virtual test, and its test process is as follows:

Step 401, initial parameter are set: adopt described parameter input unit input test wavelength of visible light λ;

Step 402, guidance signal incident direction are determined: adopt described parameter input unit that the incoming position of visible light is set earlier, again according to the incident direction x=x of the incoming position that sets to visible light _{Go into}Determine, and adopt described data processor to find out to be positioned at straight line x=x _{Go into}On all rectangular nodes; Wherein, x _{Go into}For setting the spacing between the outlet of incoming position and described engine jet pipe; Be positioned at straight line x=x _{Go into}On all rectangular nodes be guidance signal and influence grid;

Step 403, particle trajectory influence grid by way of guidance signal and determine: adopt described data processor to (the N described in the step 303 _{Y goes into}-1) individual nozzle entry rectangular node as all particle trajectories of initial grid by way of guidance signal influence grid and determine; Wherein, with (N _{Y goes into}-1) any nozzle entry rectangular node includes M different-grain diameter particle trajectory as the particle trajectory track of initial grid in the individual nozzle entry rectangular node, with (N _{Y goes into}-1) individual nozzle entry rectangular node is M * (N as all particle trajectory quantity of initial grid _{Y goes into}-1) individual;

Step 404, particle trajectory gridded data calculate: adopt described data processor to M * (N _{Y goes into}-1) gridded data of individual particle trajectory calculates respectively, and the gridded data computing method of all particle trajectories are all identical; Wherein, to M * (N _{Y goes into}When-1) gridded data of arbitrary particle trajectory calculates in the individual particle trajectory, adopt described data processor calculate current calculate particle trajectory population density and the average particle diameter in guidance signal influences grid;

Step 405, each particle trajectory attenuation coefficient convert: adopt described data processor to M * (N _{Y goes into}-1) attenuation coefficient of individual particle trajectory converts respectively, and the attenuation coefficient conversion method of all particle trajectories is all identical; Wherein, to M * (N _{Y goes into}When-1) attenuation coefficient of arbitrary particle trajectory converted in the individual particle trajectory, described data processor was according to formula κ ₀=π r ²* Q * n _pConvert κ in the formula ₀Be the attenuation coefficient of current institute conversion particle trajectory,

D be the current institute conversion particle trajectory that calculates in the step 404 the average particle diameter in guidance signal influences grid, n _pFor the current institute conversion particle trajectory that calculates in the step 404 the population density in guidance signal influences grid; Q be extinction efficiency and

In the formula

a _nAnd b _nRadius is the Mie scattering coefficient of the spheroidal particle of r when being λ for incident wavelength, Re (a _n+ b _n) expression gets a _n+ b _nReal part, n is positive integer;

Visible light guidance signal attenuation coefficient calculates on step 406, the incident direction: adopt described data processor with the M * (N that calculates in the step 405 _{Y goes into}-1) after the stack of the attenuation coefficient of individual particle trajectory, obtains the attenuation coefficient κ of visible light guidance signal on the incident direction.

Above-mentioned a kind of solid propellant smog influences visible light guidance signal virtual test method, it is characterized in that: when carrying out the initial parameter setting in the step 403, also need adopt the described parameter input unit input test incident optical length L of visible light, wherein L=2 * y _m, y _mFor jet flow radical length and its for the engine jet pipe axis to the jet flow length of outer boundary radially; After obtaining the attenuation coefficient κ of visible light guidance signal on the incident direction in the step 406, described data processor also needs according to formula T=e ^{-κ * L}Calculate the test spectral transmittance T of visible light.

Above-mentioned a kind of solid propellant smog influences visible light guidance signal virtual test method, it is characterized in that: in the step 404 to M * (N _{Y goes into}When-1) gridded data of arbitrary particle trajectory calculated in the individual particle trajectory, process was as follows:

Step 4041, 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 calculating particle trajectory in all particle trajectory data that adopt described data processor from step 302, to read, 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 303, the current initial grid of nozzle entry that calculates particle trajectory is determined;

After treating that the current initial grid of nozzle entry that calculates 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 from the vapor phase product stream field data on summit one, find out the density of gas phase ρ on summit one _G1With gas phase axial velocity u _G1, and from the vapor phase product stream field data on summit two, find out the density of gas phase ρ on summit two _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 calculating particle trajectory, and summit two is the summit, lower left of the initial grid of nozzle entry of current calculating 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 calculating particle trajectory

In the formula, M is the different-grain diameter number of particles that the need that set in the step 301 are handled; f _PtogFor the flow rate of condensed phase and gas phase than and

N in the formula _xBy the equilibrium composition sum of all condensed phase products of producing after the test SOLID PROPELLANT COMBUSTION;

Be the gas phase flow rate in the initial grid of nozzle entry of current processing particle trajectory, and ${\stackrel{\·}{m}}_g=\frac{{\stackrel{\·}{m}}_{g1}+{\stackrel{\·}{m}}_{g2}}{2},$ In the formula

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

Step 4042, population density are calculated: described data processor is according to formula

Calculate current calculate particle trajectory the population density in guidance signal influences grid; In the formula, dt by current calculating particle trajectory the residence time in guidance signal influences grid, and dt by current calculating particle trajectory the time step sum of all tracing points in guidance signal influences grid;

Mass particle flow rate by what calculate in the step 4041 in the initial grid of nozzle entry of current calculating particle trajectory;

Step 4043, average particle diameter calculate: described data processor is according to formula Calculate current calculate particle trajectory the average particle diameter D in guidance signal influences grid _pIn the formula, k3 is positive integer, and k3=1,2 ..., K, wherein K by current calculating particle trajectory the tracing point total quantity in guidance signal influences grid, and D _Pk3Particle diameter for k3 tracing point place in K the tracing point.

Above-mentioned a kind of solid propellant smog influences visible light guidance signal virtual test method, it is characterized in that: in the step 4043 to current calculate particle trajectory the average particle diameter D in guidance signal influences grid _pBefore calculating, earlier according to current calculate particle trajectory influence up-and-down boundary radial coordinate and border, the left and right sides axial coordinate of grid by way of guidance signal, and find out axial coordinate and the radial coordinate of each tracing point in the current particle trajectory data of calculating particle trajectory in the integrating step 4041, to current calculate particle trajectory tracing point total quantity K in guidance signal influences grid and axial coordinate and the radial coordinate of K tracing point determine respectively; Simultaneously, find out institute's memory contents in the file that particle diameter in the current particle trajectory data of calculating particle trajectory changes with track in the integrating step 4041, the particle diameter of each tracing point in K the tracing point is determined.

Above-mentioned a kind of solid propellant smog influences visible light guidance signal virtual test method, it is characterized in that: after obtaining the attenuation coefficient κ of visible light guidance signal on the incident direction in the step 406, described data processor also needs according to formula κ _t=c * κ revises the attenuation coefficient κ that obtains, and wherein c is correction factor and c=1.05～1.15.

Above-mentioned a kind of solid propellant smog influences visible light guidance signal virtual test method, it is characterized in that: when carrying out plume calculating in the step 1, described data processor is set up the two-dimentional axisymmetric model that the inside and outside plume of described engine jet pipe is carried out numerical evaluation earlier according to predefined jet pipe geometric parameter and jet flow computational fields scope; Afterwards, described data processor calls the CFD front processor, generate the plume computational fields grid chart of institute's test solid propellant, and described CFD front processor is GAMBIT software; Then, described data processor calls FULENT software, and in conjunction with the jet pipe geometric parameter, jet flow computational fields scope and the firing chamber running parameter that design in advance, institute's test solid propellant is carried out plume calculate, and output plume result of calculation; In the step 1 institute's test 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 a kind of solid propellant smog influences visible light guidance signal virtual test method, it is characterized in that: institute's test solid propellant is aluminized propellant in the step 1; The products of combustion that produces after the SOLID PROPELLANT COMBUSTION of testing comprise two types of gas-phase product and condensed phase products; Carry out plume in the step 1 when calculating, need input earlier the products of combustion equilibrium composition after the SOLID PROPELLANT COMBUSTION of testing; The products of combustion balance of importing comprises equilibrium composition and the Al of M gas-phase product ₂O ₃The equilibrium composition of particle; Wherein, M by after the test SOLID PROPELLANT COMBUSTION the quantity of generation gas-phase combustion product; The Al that sets ₂O ₃The equilibrium composition of particle by the equilibrium composition sum of all condensed phase products of producing after the test SOLID PROPELLANT COMBUSTION; M described in step 404, step 405 and the step 406 * (N _{Y goes into}-1) individual particle trajectory is Al ₂O ₃The track of particle; Before in the step 405 attenuation coefficient of arbitrary particle trajectory being converted, import Al by described parameter input unit earlier ₂O ₃The complex index of refraction of particle.

Above-mentioned a kind of solid propellant smog influences visible light guidance signal virtual test method, it is characterized in that: M=8 in the step 301, 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 _nFor by the predefined Al of described parameter input unit ₂O ₃The mean grain size of particle.

Above-mentioned a kind of solid propellant smog influences visible light guidance signal virtual test method, it is characterized in that: carry out in the step 1 also need carrying out the energy response calculation of parameter before the plume calculating, its computation process is as follows:

Step I, initial parameter are set and storage:

At first, by the component information of the described parameter input unit input preparation test solid propellant component utilized quantity H of institute and each component, 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 ..., H, H are the quantity that the used component of solid propellant is tested in preparation; Wherein, 0＜m _i＜100, m ₁+ m ₂+ ... + m _H=100, N 〉=2;

Afterwards, by described parameter input unit in the products of combustion database of setting up in advance, select all products of combustion of producing after the SOLID PROPELLANT COMBUSTION of testing; 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 the test SOLID PROPELLANT COMBUSTION after the quantity m of the products of combustion that produces and the quantity M of gas-phase product set;

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

Step III, equilibrium composition are calculated: the minimum free energy mathematical model of setting up in the described data processor invocation step II, and the initial parameter that sets in the integrating step I, calculate the products of combustion equilibrium composition after the SOLID PROPELLANT COMBUSTION of testing, and the products of combustion equilibrium composition that calculates comprise the equilibrium composition of m products of combustion producing after the SOLID PROPELLANT COMBUSTION of testing;

Step IV, adiabatic combustion temperature are calculated: the chamber temperature computation model of setting up in the described data processor invocation step II, calculate the adiabatic combustion temperature when being in chemistry balance state after the SOLID PROPELLANT COMBUSTION of testing.

Above-mentioned a kind of solid propellant smog influences visible light guidance signal virtual test method, it is characterized in that: when in the step 201 the vapor phase product stream field data of all non-structured grid nodes in the jet flow zone of institute's test solid propellant being read, at first set up F dynamically one-dimension array, F=F1+F2 wherein, F1=7 wherein, F2 by after the test 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, a F2 gas-phase product; Wherein, N is the quantity of all non-structured grid nodes in the jet flow zone; Gas-phase product plume result of calculation described in the step 201 is the result of calculation that is stored in after plume calculating is finished in the step 1 in * _ tec.dat file; Automatically * _ diam.fvp file of preserving after the file that particle diameter changes with track in the step 302 is finished for FULENT software calculates, * _ time.fvp file that the time step file of particle trajectory is preserved after finishing for FULENT software calculates automatically.

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 be automatically carry out the plume analog computation and the visible light influence is calculated to solid propellant afterwards, thus can be easy, fast and accurately institute's test solid propellant smog is estimated visible light guidance Effect on Performance.Afterwards,, to visible light guidance Effect on Performance estimation results the prescription of institute's test solid propellant is adjusted accordingly according to smog, thereby provide great convenience for the prescription design of solid propellant.

4, the visible light guidance signal influences that virtual test is simple, calculated amount is little, realization is convenient and result of calculation is accurate, after waiting to finish plume calculating, earlier automatically plume result of calculation is carried out the structured grid processing, and after the structured grid processing, can utilize the structured grid result to calculate institute's test solid propellant smog automatically to visible light guidance Effect on Performance result.Like this, by plume result of calculation being carried out the attenuation coefficient computation process that the structured grid processing has realized discretize, reduced the error of calculation that data fitting is brought, thereby increased substantially visible light guidance performance impact result's computational accuracy, and computation process is simple, realization is convenient, can obtain solid propellant smog fast to the result that influences of visible light guidance signal.

5, practical value height, can bring very big facility to the formula development process of low signature solid propellant, in the actual mechanical process, by after institute's test solid propellant being carried out automatically the plume analog computation and tackling plume result of calculation mutually and carry out the structured grid processing, can be easy, fast and accurately obtain solid propellant smog to the result that influences of visible light guidance signal.In the actual mechanical process, only need to adjust the weight proportion of used each component of preparation institute's test solid propellant, data processor just can be finished plume analog computation, structured grid processing and attenuation coefficient computation process automatically, therefore can easy, intuitively and accurately draw the weight proportion of used each component of preparation institute's test solid propellant to the influence of institute's test solid propellant smog optical guidance characteristic, 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.

6, 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.Simultaneously, of the present inventionly apply widely, can effectively promote being suitable for to guidance signals such as infrared, ultraviolet, laser.

In sum, the inventive method step simple, reasonable in design and realize convenient, result of use is good, can be easy, fast and accurately obtain solid propellant smog to the result that influences of visible light guidance signal.

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.

When Fig. 2 calculates for plume of the present invention the structural representation of the engine jet pipe that adopts and jet flow computational fields.

Embodiment

A kind of solid propellant smog as shown in Figure 1 influences visible light guidance signal virtual test method, may further comprise the steps:

Step 1, plume are calculated and the data storage: adopt data processor to call FULENT software institute's test solid propellant is carried out exporting and be stored to plume result of calculation in the data storage cell that joins with described data processor automatically after plume calculates; 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, when carrying out plume calculating in the step 1, described data processor is set up the two-dimentional axisymmetric model that the inside and outside plume of described engine jet pipe is carried out numerical evaluation earlier according to predefined jet pipe geometric parameter and jet flow computational fields scope; Afterwards, described data processor calls the CFD front processor, generate the plume computational fields grid chart of institute's test solid propellant, and described CFD front processor is GAMBIT software; Then, described data processor calls FULENT software, and in conjunction with the jet pipe geometric parameter, jet flow computational fields scope and the firing chamber running parameter that design in advance, institute's test solid propellant is carried out plume calculate, and output plume result of calculation.

The geometric parameter of described 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.

In the present embodiment, institute's test solid propellant is aluminized propellant in the step 1, and described aluminized propellant is composite propellant, double base propellant or modified double base propellant.

The products of combustion that produces after the SOLID PROPELLANT COMBUSTION of testing comprise two types of gas-phase product and condensed phase products, comprise gas-phase product plume result of calculation and condensed phase product plume result of calculation in the plume result of calculation of exporting.

When the firing chamber running parameter was set, its assignment procedure was as follows: at first, by described parameter input unit to pressure P in the firing chamber of engine _c, firing chamber adiabatic temperature, environmental pressure and environment temperature T _RingSet respectively; Afterwards, again to products of combustion equilibrium composition set; Then, by described parameter input unit to the test 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 in the products of combustion equilibrium composition that sets equilibrium composition and the Al of M gas-phase product producing after the SOLID PROPELLANT COMBUSTION of testing ₂O ₃The equilibrium composition of particle; Wherein, M by after the test SOLID PROPELLANT COMBUSTION the quantity of generation gas-phase combustion product; The Al that sets ₂O ₃The equilibrium composition of particle by the equilibrium composition sum of all condensed phase products of producing after the test SOLID PROPELLANT COMBUSTION.

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 1 when calculating, the gas-phase product that adopts 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 1 designed solid propellant being carried out plume when calculating, the governing equation of the condensed phase product that adopts is Lagrangian particle model trajectory.

Step 2, the gridding of gas-phase product plume data structure are handled, and its processing procedure is as follows:

Step 201, jet flow zone vapor phase product stream field data reads: adopt in the gas-phase product plume result of calculation that described data processor exports from step 1, read the vapor phase product stream field data of all non-structured grid nodes in the jet flow zone; Described jet flow zone is the rectangular area at used engine jet pipe outlet rear when plume calculates in the step 1.

In the present embodiment, the incoming position that sets is on the central axis of described engine jet pipe.

In the present embodiment, the plume of gas-phase product described in step 1 result of calculation 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 301, 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 vapor phase product stream field data that reads all non-structured grid nodes in the jet flow zone that reads out in the step 201 is the data of storing in * _ tec.dat file.

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 201 the vapor phase product stream field data of all non-structured grid nodes in the jet flow zone of institute's test solid propellant being read, at first set up F dynamically one-dimension array, F=F1+F2 wherein, F1=7 wherein, F2 by after the test 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, a F2 gas-phase product; Wherein, N is the quantity of all non-structured grid nodes in the jet flow zone.

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.

Non-structured grid point extracts on step 202, the axial coordinate axle: adopt the non-structured grid node of described data processor all in the zone of jet flow described in the step 201, extraction is positioned at all the non-structured grid points on the axial coordinate axle, and the non-structured grid point total quantity of extracting in this step 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, is positioned at the radial coordinate y of the non-structured grid point on the axial coordinate axle _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 203, the radial coordinate axle: adopt the non-structured grid node of described data processor all in the zone of jet flow described in the step 201, extraction is positioned at all the non-structured grid points on the radial coordinate axle, and the non-structured grid point total quantity of extracting 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}

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

Step 204, 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 205, 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 204 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 201 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.

In the present embodiment, after extracting all non-structured grid points that are positioned on the axial coordinate axle in the step 202, 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 203, 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.

In the present embodiment, when carrying out gas-phase product plume data structure gridding processing in the step 205, 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 205 and handling, also need the result stores synchronized to the data storage cell that joins with described data processor.

Step 3, 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 204 to carry out the structured grid processing respectively, and process is as follows:

Step 301, 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 301, 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 _nFor by the predefined Al of described parameter input unit 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 302, 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 1, to export; Wherein, the condensed phase product plume result of calculation that reads comprises that particle diameter is with the file of track variation and the time step file of particle trajectory.

In the present embodiment, particle diameter described in the step 302 is respectively and preserves * _ diam.fvp and * _ time.fvp file automatically after the calculating of FULENT software is finished with the file of track variation and the time step file of particle trajectory.

Simultaneously, the condensed phase product plume result of calculation that reads in the step 302 also comprises the file that particle temperature changes with track, be * _ temp.fvp, wherein * _ temp.fvp is the file of text formatting, and * _ diam.fvp, * _ temp.fvp are all identical with the content storage format of * _ time.fvp file.Be example with time step file * _ time.fvp, its preceding 7 behavior file heads the contents are as follows:

Be example with time step file * _ time.fvp, its preceding 7 behavior file heads the contents are as follows:

FVPARTICLES21

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 * _ temp.fvp and * _ diam.fvp) is identical.From eighth row opening entry particle trajectory data, the contents are as follows:

1141

-0.04967380.0248277000

-0.04958690.024827307.74289e-0060

-0.04915270.024825503.87144e-0050

-0.04912650.024825402.3338e-0060

-0.04869230.024823503.87165e-0050

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 303, 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 in the gas-phase product plume result of calculation that adopts described data processor to export from step 1; Afterwards, adopt and extract all non-structured grid nodes that are positioned on the straight line x=-Δ d the non-structured grid node of described data processor all in the engine jet pipe zone of reading, 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 is that described engine jet pipe entrance is to the distance between the nozzle exit; The rectangular node that is positioned at described engine jet pipe porch in the step 204 among the constructed structured grid figure is the nozzle entry rectangular node, and described nozzle entry rectangular node quantity 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 4, visible light guidance signal influence virtual test, and its test process is as follows:

Step 401, initial parameter are set: adopt described parameter input unit input test wavelength of visible light λ.

In the present embodiment, λ=0.7 μ m～0.9 μ m.

Step 402, guidance signal incident direction are determined: adopt described parameter input unit that the incoming position of visible light is set earlier, again according to the incident direction x=x of the incoming position that sets to visible light _{Go into}Determine, and adopt described data processor to find out to be positioned at straight line x=x _{Go into}On all rectangular nodes; Wherein, x _{Go into}For setting the spacing between the outlet of incoming position and described engine jet pipe; Be positioned at straight line x=x _{Go into}On all rectangular nodes be guidance signal and influence grid.

Work as x=x _{Go into}When boundary line between the adjacent two row rectangular nodes overlaps, be positioned at straight line x=x _{Go into}The one row rectangular node in left side is for being positioned at straight line x=x _{Go into}On all rectangular nodes.

Step 403, particle trajectory influence grid by way of guidance signal and determine: adopt described data processor to (the N described in the step 303 _{Y goes into}-1) individual nozzle entry rectangular node as all particle trajectories of initial grid by way of guidance signal influence grid and determine; Wherein, with (N _{Y goes into}-1) any nozzle entry rectangular node includes M different-grain diameter particle trajectory as the particle trajectory track of initial grid in the individual nozzle entry rectangular node, with (N _{Y goes into}-1) individual nozzle entry rectangular node is M * (N as all particle trajectory quantity of initial grid _{Y goes into}-1) individual.

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, be M with each nozzle entry rectangular node as the quantity of the particle trajectory of initial grid.

M different-grain diameter particle trajectory is respectively particle diameter D in the step 403 _N1Particle trajectory, particle diameter be D _N2Particle trajectory ..., and particle diameter be D _NMParticle trajectory.

In the present embodiment, in the step 403 to (N _{Y goes into}-1) individual nozzle entry rectangular node as all particle trajectories of initial grid by way of guidance signal when influencing grid and determining, all particle trajectories by way of guidance signal influence grid and determine that method is all identical; For any particle trajectory by way of guidance signal when influencing grid and determining, axial coordinate and radial coordinate according to each tracing point in the current particle trajectory data of handling particle trajectory that read in the step 302, and constructed structured grid figure in the integrating step 204, find out current handle particle trajectory by way of guidance signal influence grid.

In the present embodiment, when carrying out the initial parameter setting in the step 403, also need adopt the described parameter input unit input test incident optical length L of visible light, wherein L=2 * y _m, y _mFor jet flow radical length and its for the engine jet pipe axis to the jet flow length of outer boundary radially; After obtaining the attenuation coefficient κ of visible light guidance signal on the incident direction in the step 406, described data processor also needs according to formula T=e ^{-κ * L}Calculate the test spectral transmittance T of visible light.

Step 404, particle trajectory gridded data calculate: adopt described data processor to M * (N _{Y goes into}-1) gridded data of individual particle trajectory calculates respectively, and the gridded data computing method of all particle trajectories are all identical; Wherein, to M * (N _{Y goes into}When-1) gridded data of arbitrary particle trajectory calculates in the individual particle trajectory, adopt described data processor calculate current calculate particle trajectory population density and the average particle diameter in guidance signal influences grid.

In the present embodiment, in the step 404 to M * (N _{Y goes into}When-1) gridded data of arbitrary particle trajectory calculated in the individual particle trajectory, process was as follows:

Step 4041, 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 calculating particle trajectory in all particle trajectory data that adopt described data processor from step 302, to read, 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 303, the current initial grid of nozzle entry that calculates particle trajectory is determined;

After treating that the current initial grid of nozzle entry that calculates 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 from the vapor phase product stream field data on summit one, find out the density of gas phase ρ on summit one _G1With gas phase axial velocity u _G1, and from the vapor phase product stream field data on summit two, find out the density of gas phase ρ on summit two _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 calculating particle trajectory, and summit two is the summit, lower left of the initial grid of nozzle entry of current calculating 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 calculating particle trajectory

In the formula, M is the different-grain diameter number of particles that the need that set in the step 301 are handled; f _PtogFor the flow rate of condensed phase and gas phase than and

N in the formula _xBy the equilibrium composition sum of all condensed phase products of producing after the test SOLID PROPELLANT COMBUSTION; Be the gas phase flow rate in the initial grid of nozzle entry of current processing particle trajectory, and ${\stackrel{\·}{m}}_g=\frac{{\stackrel{\·}{m}}_{g1}+{\stackrel{\·}{m}}_{g2}}{2},$ In the formula

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

Step 4042, population density are calculated: described data processor is according to formula

Calculate current calculate particle trajectory the population density in guidance signal influences grid; In the formula, dt by current calculating particle trajectory the residence time in guidance signal influences grid, and dt by current calculating particle trajectory the time step sum of all tracing points in guidance signal influences grid;

Mass particle flow rate by what calculate in the step 4041 in the initial grid of nozzle entry of current calculating particle trajectory;

Step 4043, average particle diameter calculate: described data processor is according to formula

Calculate current calculate particle trajectory the average particle diameter D in guidance signal influences grid _pIn the formula, k3 is positive integer, and k3=1,2 ..., K, wherein K by current calculating particle trajectory the tracing point total quantity in guidance signal influences grid, and D _Pk3Particle diameter for k3 tracing point place in K the tracing point.

In the present embodiment, in the step 4043 to current calculate particle trajectory the average particle diameter D in guidance signal influences grid _pBefore calculating, earlier according to current calculate particle trajectory influence up-and-down boundary radial coordinate and border, the left and right sides axial coordinate of grid by way of guidance signal, and find out axial coordinate and the radial coordinate of each tracing point in the current particle trajectory data of calculating particle trajectory in the integrating step 4041, to current calculate particle trajectory tracing point total quantity K in guidance signal influences grid and axial coordinate and the radial coordinate of K tracing point determine respectively; Simultaneously, find out institute's memory contents in the file that particle diameter in the current particle trajectory data of calculating particle trajectory changes with track in the integrating step 4041, the particle diameter of each tracing point in K the tracing point is determined.

Actual to current calculate particle trajectory the tracing point total quantity K in guidance signal influences grid when determining, travel through the current tracing point that calculates on the particle trajectory, and find out axial coordinate influence between border, the left and right sides axial coordinate of grid and the tracing point of radial coordinate between current the up-and-down boundary radial coordinate that influences grid by way of guidance signal by way of guidance signal.K tracing point with the current particle trajectory that calculates in guidance signal influences grid be divided into a plurality of orbit segments, and the time step sum of a plurality of described orbit segments (being the time step sum of K tracing point) just is dt.

Step 405, each particle trajectory attenuation coefficient convert: adopt described data processor to M * (N _{Y goes into}-1) attenuation coefficient of individual particle trajectory converts respectively, and the attenuation coefficient conversion method of all particle trajectories is all identical; Wherein, to M * (N _{Y goes into}When-1) attenuation coefficient of arbitrary particle trajectory converted in the individual particle trajectory, described data processor was according to formula κ ₀=π r ²* Q * n _pConvert κ in the formula ₀Be the attenuation coefficient of current institute conversion particle trajectory,

D be the current institute conversion particle trajectory that calculates in the step 404 the average particle diameter in guidance signal influences grid, n _pFor the current institute conversion particle trajectory that calculates in the step 404 the population density in guidance signal influences grid; Q be extinction efficiency and

In the formula

a _nAnd b _nRadius is the Mie scattering coefficient of the spheroidal particle of r when being λ for incident wavelength, Re (a _n+ b _n) expression gets a _n+ b _nReal part, n is positive integer.

In the present embodiment, radius was the Mie scattering coefficient a of the spheroidal particle of r when incident wavelength was λ _nAnd b _nWhen determining, determine with reference to following four documents.Wherein, document one is W.J.Lentz.Generating Bessel functions in mie scattering calculations using continued fractions[J] .Applied Optics, 1976,4(3).Document two is W.J.Wiscombe.Improved mie scattering algorithms[J] .Applied Optics, 1980,10(6).Document three is Y.Xu.Electromagnetic scattering by and aggregate of spheres[J] .Applied Optics, 1985,8(3).Document four is W.Yang.Improved recursive algorithm for light scattering by a multilayered sphere[J] .Applied Optics, 2003,11(5).

Simultaneously, also can roll out " solid propellant rocket exhaust plume is to the computing method of infrared guidance signal attenuation " literary composition of version with reference to " solid-rocket technology " the 30th phase the 5th in 2007, author: Zhang Shuo, Wang Ningfei, Zhang Ping.

Visible light guidance signal attenuation coefficient calculates on step 406, the incident direction: adopt described data processor with the M * (N that calculates in the step 405 _{Y goes into}-1) after the stack of the attenuation coefficient of individual particle trajectory, obtains the attenuation coefficient κ of visible light guidance signal on the incident direction.

In the present embodiment, obtain the attenuation coefficient κ of visible light guidance signal on the incident direction in the step 406 after, described data processor also needs according to formula κ _t=c * κ revises the attenuation coefficient κ that obtains, and wherein c is correction factor and c=1.05～1.15.

During actual the use, can be according to concrete needs, the value size of c is adjusted accordingly.In the present embodiment, c=1.1.

In the present embodiment, institute's test solid propellant is aluminized propellant in the step 1; The products of combustion that produces after the SOLID PROPELLANT COMBUSTION of testing comprise two types of gas-phase product and condensed phase products; Carry out plume in the step 1 when calculating, need input earlier the products of combustion equilibrium composition after the SOLID PROPELLANT COMBUSTION of testing; The products of combustion balance of importing comprises equilibrium composition and the Al of M gas-phase product ₂O ₃The equilibrium composition of particle; Wherein, M by after the test SOLID PROPELLANT COMBUSTION the quantity of generation gas-phase combustion product; The Al that sets ₂O ₃The equilibrium composition of particle by the equilibrium composition sum of all condensed phase products of producing after the test SOLID PROPELLANT COMBUSTION; M described in step 404, step 405 and the step 406 * (N _{Y goes into}-1) individual particle trajectory is Al ₂O ₃The track of particle; Before in the step 405 attenuation coefficient of arbitrary particle trajectory being converted, import Al by described parameter input unit earlier ₂O ₃The complex index of refraction of particle.

In the actual use, to Al ₂O ₃When the complex index of refraction of particle is determined, with reference to the obtainable relevant Al of those skilled in the art ₂O ₃The list of references of particle complex index of refraction is set.

In the present embodiment, with reference to Harbin Institute of Technology's PhD dissertation " experimental study of alundum (Al particle complex index of refraction " in 2008, author: Qi Hong was to Al ₂O ₃The complex index of refraction of particle is set.

In the present embodiment, before in the step 405 attenuation coefficient of arbitrary particle trajectory being converted, described data processor also needs according to formula

Calculate current calculate particle trajectory the medial temperature T in guidance signal influences grid _p, the Al that imports ₂O ₃The complex index of refraction of particle is Al ₂O ₃Particle is in temperature T _pThe time complex index of refraction, T _Pk3Particle temperature (from * _ temp.fvp file, reading) for k3 tracing point place in the tracing point of K in the step 4043.

In the present embodiment, carry out in the step 1 also need carrying out the energy response calculation of parameter before the plume calculating, its computation process is as follows:

Step I, initial parameter are set and storage:

At first, by the component information of the described parameter input unit input preparation test solid propellant component utilized quantity H of institute and each component, 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 ..., H, H are the quantity that the used component of solid propellant is tested in preparation; Wherein, 0＜m _i＜100, m ₁+ m ₂+ ... + m _H=100, N 〉=2;

Afterwards, by described parameter input unit in the products of combustion database of setting up in advance, select all products of combustion of producing after the SOLID PROPELLANT COMBUSTION of testing; 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 the test SOLID PROPELLANT COMBUSTION after the quantity m of the products of combustion that produces and the quantity M of gas-phase product set;

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

Step III, equilibrium composition are calculated: the minimum free energy mathematical model of setting up in the described data processor invocation step II, and the initial parameter that sets in the integrating step I, calculate the products of combustion equilibrium composition after the SOLID PROPELLANT COMBUSTION of testing, and the products of combustion equilibrium composition that calculates comprise the equilibrium composition of m products of combustion producing after the SOLID PROPELLANT COMBUSTION of testing;

Step IV, adiabatic combustion temperature are calculated: the chamber temperature computation model of setting up in the described data processor invocation step II, calculate the adiabatic combustion temperature when being in chemistry balance state after the SOLID PROPELLANT COMBUSTION of testing.

When carrying out plume calculating in the step 1, binding energy flow characteristic calculation of parameter result sets the firing chamber running parameter.

In the present embodiment, when equilibrium composition was set to products of combustion, the products of combustion equilibrium composition that sets calculated the chemical equilibrium composition of products of combustion for according to gibbs minimum free energy principle.

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 II is

(1), in the formula (1): j is positive integer, and j=1,2 ..., B, B 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 satisfying one group of ns value under formula (1) condition and is made 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 (2), 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 _S2T2+ α _S3T ²3)+α _S4T ³4+ α _S5T ⁴5+ α _S6T ⁵6), 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 III, 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 I _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

(1) calculates 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 IV, the products of combustion equilibrium composition after the designed SOLID PROPELLANT COMBUSTION that calculates in the described data processor integrating step III, and according to formula

(2), 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 I _iConsistent.

In addition, carry out in the step 1 also needing to import by described parameter input unit earlier the finite rate Chemical Reaction Model of products of combustion before the plume calculating.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 2 for details:

The chemical dynamic model reaction mechanism tables of data of table 29 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
				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 3 for details:

The chemical dynamic model reaction mechanism tables of data of table 312 component 17 reactions

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 (10)

1. a solid propellant smog influences visible light guidance signal virtual test method, it is characterized in that this method may further comprise the steps:

Step 1, plume are calculated and the data storage: adopt data processor to call FULENT software institute's test solid propellant is carried out exporting and be stored to plume result of calculation in the data storage cell that joins with described data processor automatically after plume calculates; 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 2, the gridding of gas-phase product plume data structure are handled, and its processing procedure is as follows:

Step 201, jet flow zone vapor phase product stream field data reads: adopt in the gas-phase product plume result of calculation that described data processor exports from step 1, read the vapor phase product stream field data of all non-structured grid nodes in the jet flow zone; Described jet flow zone is the rectangular area at used engine jet pipe outlet rear when plume calculates in the step 1;

Non-structured grid point extracts on step 202, the axial coordinate axle: adopt the non-structured grid node of described data processor all in the zone of jet flow described in the step 201, extraction is positioned at all the non-structured grid points on the axial coordinate axle, and the non-structured grid point total quantity of extracting in this step 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, is positioned at the radial coordinate y of the non-structured grid point on the axial coordinate axle _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 203, the radial coordinate axle: adopt the non-structured grid node of described data processor all in the zone of jet flow described in the step 201, extraction is positioned at all the non-structured grid points on the radial coordinate axle, and the non-structured grid point total quantity of extracting 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 204, 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 205, 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 204 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 201 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 3, 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 204 to carry out the structured grid processing respectively, and process is as follows:

Step 301, 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;

Step 302, 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 1, to export; Wherein, the condensed phase product plume result of calculation that reads comprises that particle diameter is with the file of track variation and the time step file of particle trajectory;

Step 303, 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 in the gas-phase product plume result of calculation that adopts described data processor to export from step 1; Afterwards, adopt and extract all non-structured grid nodes that are positioned on the straight line x=-Δ d the non-structured grid node of described data processor all in the engine jet pipe zone of reading, 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 is that described engine jet pipe entrance is to the distance between the nozzle exit; The rectangular node that is positioned at described engine jet pipe porch in the step 204 among the constructed structured grid figure is the nozzle entry rectangular node, and described nozzle entry rectangular node quantity 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 4, visible light guidance signal influence virtual test, and its test process is as follows:

Step 401, initial parameter are set: adopt described parameter input unit input test wavelength of visible light λ;

Step 402, guidance signal incident direction are determined: adopt described parameter input unit that the incoming position of visible light is set earlier, again according to the incident direction x=x of the incoming position that sets to visible light _{Go into}Determine, and adopt described data processor to find out to be positioned at straight line x=x _{Go into}On all rectangular nodes; Wherein, x _{Go into}For setting the spacing between the outlet of incoming position and described engine jet pipe; Be positioned at straight line x=x _{Go into}On all rectangular nodes be guidance signal and influence grid;

Step 403, particle trajectory influence grid by way of guidance signal and determine: adopt described data processor to (the N described in the step 303 _{Y goes into}-1) individual nozzle entry rectangular node as all particle trajectories of initial grid by way of guidance signal influence grid and determine; Wherein, with (N _{Y goes into}-1) any nozzle entry rectangular node includes M different-grain diameter particle trajectory as the particle trajectory track of initial grid in the individual nozzle entry rectangular node, with (N _{Y goes into}-1) individual nozzle entry rectangular node is M * (N as all particle trajectory quantity of initial grid _{Y goes into}-1) individual;

Step 404, particle trajectory gridded data calculate: adopt described data processor to M * (N _{Y goes into}-1) gridded data of individual particle trajectory calculates respectively, and the gridded data computing method of all particle trajectories are all identical; Wherein, to M * (N _{Y goes into}When-1) gridded data of arbitrary particle trajectory calculates in the individual particle trajectory, adopt described data processor calculate current calculate particle trajectory population density and the average particle diameter in guidance signal influences grid;

Step 405, each particle trajectory attenuation coefficient convert: adopt described data processor to M * (N _{Y goes into}-1) attenuation coefficient of individual particle trajectory converts respectively, and the attenuation coefficient conversion method of all particle trajectories is all identical; Wherein, to M * (N _{Y goes into}When-1) attenuation coefficient of arbitrary particle trajectory converted in the individual particle trajectory, described data processor was according to formula κ ₀=π r ²* Q * n _pConvert κ in the formula ₀Be the attenuation coefficient of current institute conversion particle trajectory,

D be the current institute conversion particle trajectory that calculates in the step 404 the average particle diameter in guidance signal influences grid, n _pFor the current institute conversion particle trajectory that calculates in the step 404 the population density in guidance signal influences grid; Q be extinction efficiency and

In the formula

a _nAnd b _nRadius is the Mie scattering coefficient of the spheroidal particle of r when being λ for incident wavelength, Re (a _n+ b _n) expression gets a _n+ b _nReal part, n is positive integer;

Visible light guidance signal attenuation coefficient calculates on step 406, the incident direction: adopt described data processor with the M * (N that calculates in the step 405 _{Y goes into}-1) after the stack of the attenuation coefficient of individual particle trajectory, obtains the attenuation coefficient κ of visible light guidance signal on the incident direction.

2. influence visible light guidance signal virtual test method according to the described a kind of solid propellant smog of claim 1, it is characterized in that: when carrying out the initial parameter setting in the step 403, also need adopt the described parameter input unit input test incident optical length L of visible light, wherein L=2 * y _m, y _mFor jet flow radical length and its for the engine jet pipe axis to the jet flow length of outer boundary radially; After obtaining the attenuation coefficient κ of visible light guidance signal on the incident direction in the step 406, described data processor also needs according to formula T=e ^{-κ * L}Calculate the test spectral transmittance T of visible light.

3. influence visible light guidance signal virtual test method according to claim 1 or 2 described a kind of solid propellant smog, it is characterized in that: in the step 404 to M * (N _{Y goes into}When-1) gridded data of arbitrary particle trajectory calculated in the individual particle trajectory, process was as follows:

Step 4041, 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 calculating particle trajectory in all particle trajectory data that adopt described data processor from step 302, to read, 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 303, the current initial grid of nozzle entry that calculates particle trajectory is determined;

After treating that the current initial grid of nozzle entry that calculates 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 from the vapor phase product stream field data on summit one, find out the density of gas phase ρ on summit one _G1With gas phase axial velocity u _G1, and from the vapor phase product stream field data on summit two, find out the density of gas phase ρ on summit two _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 calculating particle trajectory, and summit two is the summit, lower left of the initial grid of nozzle entry of current calculating 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 calculating particle trajectory

In the formula, M is the different-grain diameter number of particles that the need that set in the step 301 are handled; f _PtogFor the flow rate of condensed phase and gas phase than and

N in the formula _xBy the equilibrium composition sum of all condensed phase products of producing after the test SOLID PROPELLANT COMBUSTION;

Be the gas phase flow rate in the initial grid of nozzle entry of current processing particle trajectory, and ${\stackrel{\·}{m}}_g=\frac{{\stackrel{\·}{m}}_{g1}+{\stackrel{\·}{m}}_{g2}}{2},$ In the formula S wherein _GridArea by the initial grid of nozzle entry of current processing particle trajectory;

Step 4042, population density are calculated: described data processor is according to formula

Calculate current calculate particle trajectory the population density in guidance signal influences grid; In the formula, dt by current calculating particle trajectory the residence time in guidance signal influences grid, and dt by current calculating particle trajectory the time step sum of all tracing points in guidance signal influences grid;

Mass particle flow rate by what calculate in the step 4041 in the initial grid of nozzle entry of current calculating particle trajectory;

Step 4043, average particle diameter calculate: described data processor is according to formula

Calculate current calculate particle trajectory the average particle diameter D in guidance signal influences grid _pIn the formula, k3 is positive integer, and k3=1,2 ..., K, wherein K by current calculating particle trajectory the tracing point total quantity in guidance signal influences grid, and D _Pk3Particle diameter for k3 tracing point place in K the tracing point.

4. influence visible light guidance signal virtual test method according to the described a kind of solid propellant smog of claim 3, it is characterized in that: in the step 4043 to current calculate particle trajectory the average particle diameter D in guidance signal influences grid _pBefore calculating, earlier according to current calculate particle trajectory influence up-and-down boundary radial coordinate and border, the left and right sides axial coordinate of grid by way of guidance signal, and find out axial coordinate and the radial coordinate of each tracing point in the current particle trajectory data of calculating particle trajectory in the integrating step 4041, to current calculate particle trajectory tracing point total quantity K in guidance signal influences grid and axial coordinate and the radial coordinate of K tracing point determine respectively; Simultaneously, find out institute's memory contents in the file that particle diameter in the current particle trajectory data of calculating particle trajectory changes with track in the integrating step 4041, the particle diameter of each tracing point in K the tracing point is determined.

5. influence visible light guidance signal virtual test method according to claim 1 or 2 described a kind of solid propellant smog, it is characterized in that: after obtaining the attenuation coefficient κ of visible light guidance signal on the incident direction in the step 406, described data processor also needs according to formula κ _t=c * κ revises the attenuation coefficient κ that obtains, and wherein c is correction factor and c=1.05～1.15.

6. influence visible light guidance signal virtual test method according to claim 1 or 2 described a kind of solid propellant smog, it is characterized in that: when carrying out plume calculating in the step 1, described data processor is set up the two-dimentional axisymmetric model that the inside and outside plume of described engine jet pipe is carried out numerical evaluation earlier according to predefined jet pipe geometric parameter and jet flow computational fields scope; Afterwards, described data processor calls the CFD front processor, generate the plume computational fields grid chart of institute's test solid propellant, and described CFD front processor is GAMBIT software; Then, described data processor calls FULENT software, and in conjunction with the jet pipe geometric parameter, jet flow computational fields scope and the firing chamber running parameter that design in advance, institute's test solid propellant is carried out plume calculate, and output plume result of calculation; In the step 1 institute's test solid propellant is carried out plume when calculating, the governing equation of the condensed phase product that adopts is Lagrangian particle model trajectory.

7. influence visible light guidance signal virtual test method according to claim 1 or 2 described a kind of solid propellant smog, it is characterized in that: institute's test solid propellant is aluminized propellant in the step 1; The products of combustion that produces after the SOLID PROPELLANT COMBUSTION of testing comprise two types of gas-phase product and condensed phase products; Carry out plume in the step 1 when calculating, need input earlier the products of combustion equilibrium composition after the SOLID PROPELLANT COMBUSTION of testing; The products of combustion balance of importing comprises equilibrium composition and the Al of M gas-phase product ₂O ₃The equilibrium composition of particle; Wherein, M by after the test SOLID PROPELLANT COMBUSTION the quantity of generation gas-phase combustion product; The Al that sets ₂O ₃The equilibrium composition of particle by the equilibrium composition sum of all condensed phase products of producing after the test SOLID PROPELLANT COMBUSTION; M described in step 404, step 405 and the step 406 * (N _{Y goes into}-1) individual particle trajectory is Al ₂O ₃The track of particle; Before in the step 405 attenuation coefficient of arbitrary particle trajectory being converted, import Al by described parameter input unit earlier ₂O ₃The complex index of refraction of particle.

8. influence visible light guidance signal virtual test method according to the described a kind of solid propellant smog of claim 7, it is characterized in that: M=8 in the step 301, 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 _nFor by the predefined Al of described parameter input unit ₂O ₃The mean grain size of particle.

9. influence visible light guidance signal virtual test method according to claim 1 or 2 described a kind of solid propellant smog, it is characterized in that: carry out in the step 1 also need carrying out the energy response calculation of parameter before the plume calculating, its computation process is as follows:

Step I, initial parameter are set and storage:

At first, by the component information of the described parameter input unit input preparation test solid propellant component utilized quantity H of institute and each component, 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 ..., H, H are the quantity that the used component of solid propellant is tested in preparation; Wherein, 0＜m _i＜100, m ₁+ m ₂+ ... + m _H=100, N 〉=2;

Afterwards, by described parameter input unit in the products of combustion database of setting up in advance, select all products of combustion of producing after the SOLID PROPELLANT COMBUSTION of testing; 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 the test SOLID PROPELLANT COMBUSTION after the quantity m of the products of combustion that produces and the quantity M of gas-phase product set;

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

Step III, equilibrium composition are calculated: the minimum free energy mathematical model of setting up in the described data processor invocation step II, and the initial parameter that sets in the integrating step I, calculate the products of combustion equilibrium composition after the SOLID PROPELLANT COMBUSTION of testing, and the products of combustion equilibrium composition that calculates comprise the equilibrium composition of m products of combustion producing after the SOLID PROPELLANT COMBUSTION of testing;

Step IV, adiabatic combustion temperature are calculated: the chamber temperature computation model of setting up in the described data processor invocation step II, calculate the adiabatic combustion temperature when being in chemistry balance state after the SOLID PROPELLANT COMBUSTION of testing.

10. influence visible light guidance signal virtual test method according to claim 1 or 2 described a kind of solid propellant smog, it is characterized in that: when in the step 201 the vapor phase product stream field data of all non-structured grid nodes in the jet flow zone of institute's test solid propellant being read, at first set up F dynamically one-dimension array, F=F1+F2 wherein, F1=7 wherein, F2 by after the test 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, a F2 gas-phase product; Wherein, N is the quantity of all non-structured grid nodes in the jet flow zone; Gas-phase product plume result of calculation described in the step 201 is the result of calculation that is stored in after plume calculating is finished in the step 1 in * _ tec.dat file; Automatically * _ diam.fvp file of preserving after the file that particle diameter changes with track in the step 302 is finished for FULENT software calculates, * _ time.fvp file that the time step file of particle trajectory is preserved after finishing for FULENT software calculates automatically.

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