CN117407678B - Hypersonic aircraft radiation detection and identification system and hypersonic aircraft radiation detection and identification method - Google Patents
Hypersonic aircraft radiation detection and identification system and hypersonic aircraft radiation detection and identification method Download PDFInfo
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Abstract
The invention provides a hypersonic aircraft radiation detection and identification system and method, which are characterized in that hypersonic unbalanced flow and radiation equation convection field information and radiation information are subjected to coupling solution, intermediate flow field information and intermediate radiation information obtained by hypersonic unbalanced flow and radiation equation calculation are reintroduced into hypersonic unbalanced flow and radiation equation to be subjected to iterative loop calculation until the intermediate flow field information meets convergence conditions, so that higher detection precision of radiation spectrum information of the hypersonic aircraft is realized.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a radiation detection and identification system and method of a hypersonic aircraft.
Background
The hypersonic aircraft is an aircraft which continuously flies at a speed of more than 5 times of sound and completes tasks such as specified hitting or investigation, and has the characteristics of high maneuverability, difficult trajectory prediction, high interception difficulty, rapid hitting of targets and the like. In the flight process, the flow field gas is subjected to strong compression due to severe aerodynamic effect and unbalanced effect, a temperature field exceeding 10000K is generated, at the moment, the internal degree of freedom of gas molecules in the high-temperature unbalanced flow field is excited, complex chemical processes such as dissociation, recombination and ionization occur, a thermal radiation spectrum which is obviously different from the atmospheric background is radiated, and the spectrum with obvious characteristics can be used as the basis for identifying and detecting hypersonic aircrafts.
The hypersonic aircraft has very high flying speed, so that the scattering cross section of the radar is very small, and the difficulty of detecting the target by using a radar detection means is very high. The hypersonic aircraft can generate extremely strong radiant heat and extremely obvious radiation spectrum in the flight process, and the heat radiation phenomenon and the radiation spectrum of the hypersonic aircraft provide an important supporting function for detecting the hypersonic aircraft by using the infrared detection system because the heat radiation generates infrared rays.
In the prior art, the research on the detection and identification of the radiant heat and the radiant spectrum of the hypersonic aircraft has the greatest influence on the research result of Johnston team of NASA in the U.S. (reference: johnston et al. Non-equilibrium stagnation-line radiative heating for Fire II [ J ]. Journal of Spacecraft and Rockets, 2008, 45 (6): 1185-1195.), the calculation of the radiant heat and the radiant spectrum information of a standard model Fire II (a standard geometric model of the hypersonic aircraft) is carried out in the research, the radiant heat prediction data of Fire II in the whole trajectory is given, and the research results of Johnston team are taken as the comparison standard in the industry. However, the Johnston team of NASA only discloses the research result, wherein a specific technical scheme is not known to the public, the prior art can only study by itself, and then the research result is compared with the Johnston team, but the existing research result has the problem of lower detection and identification accuracy compared with the Johnston team.
The hypersonic aircraft radiation detection and recognition model in the prior art is focused on a calculation method for a flow field, such as solving flow field parameters by using Euler equations in the prior art 1 (Sutton K. Air radiation revisited [ C/OL ]//19th Thermophysics Conference. Snow mass, CO, U.S. A.: american Institute of Aeronautics and Astronautics, 1984.); prior art 2 (Gupta R. Navier-Stokes and viscous shock-layer solutions for radiating hypersonic flows [ C/OL ]//22nd Thermophysics Conference. Honnolulu, HI, U.S. A.: american Institute of Aeronautics and Astronautics, 1987) uses the viscous shock layer equation to solve for flow field parameters. The biggest problem of the calculation methods is that the flow field information and the radiation information are calculated independently, and the radiation information is calculated after the final flow field information is calculated. However, in the actual situation, the flow field and the radiation are synchronously performed, and heat radiation exists in each layer of flow field, so that the calculation method of the existing model is seriously different from the actual situation, and the calculation method is also a main reason for low detection accuracy of the model.
Disclosure of Invention
The invention provides a hypersonic aircraft radiation detection and identification system and a hypersonic aircraft radiation detection and identification method, which aim at the problem of low detection precision caused by independently calculating flow field information and radiation information when the radiation spectrum information of the hypersonic aircraft is detected in the prior art, and the flow field information and the radiation information are subjected to coupling calculation, so that the detection and identification precision of the radiation spectrum information of the hypersonic aircraft is improved.
In order to solve the existing technical problems, the invention provides a hypersonic aircraft radiation detection and identification method, which comprises the following steps:
setting initial flow field information and initial radiation information as a first input;
carrying out calculation by taking the first input into hypersonic unbalanced flow and radiation equation, and outputting intermediate flow field information and intermediate radiation information;
when the convergence condition is met, the intermediate flow field information and the intermediate radiation information are used as second input and output; when the convergence condition is not met, taking the intermediate flow field information and the intermediate radiation information as a first input, carrying out calculation on hypersonic unbalanced flow and a radiation equation, iterating and outputting the first input;
and extracting and outputting the radiation spectrum information of the hypersonic aircraft according to the second input.
In practice, the above method provides a physical model of detection and identification for the trajectory prediction system of hypersonic aircraft, on the basis of which the optical detection device analyzes the hypersonic aircraft detected in order to predict its flight trajectory.
Further, the hypersonic unbalanced flow and radiation equation comprises a known parameter heat source item, the intermediate radiation information comprises radiation heat, the radiation heat in the intermediate radiation information is used as a heat source item to be input, and calculation of the hypersonic unbalanced flow and radiation equation is carried out, so that iteration of the first input is realized.
A second object of the present invention is to provide a hypersonic aircraft radiation detection and identification system employing any of the hypersonic aircraft radiation detection and identification methods described above, comprising:
the hypersonic unbalanced flow and radiation calculation module is used for calculating and iterating flow field information and radiation information; taking initial flow field information and initial radiation information as first input; and/or, calculating according to the first input, and outputting and iterating the intermediate flow field information and the intermediate radiation information of the first input;
the coupling module is used for continuously iterating the first input, judging whether the convergence condition is met, and taking the first input as the second input and outputting if the convergence condition is met; if the convergence condition is not met, continuing to iterate the first input;
the hypersonic unbalanced flow and radiation calculation module comprises a known parameter heat source item, the intermediate radiation information comprises radiation heat, the radiation heat in the intermediate radiation information is used as the heat source item to be input, hypersonic unbalanced flow and radiation calculation is carried out, and iteration of the first input is achieved.
The invention also discloses a server, which comprises a memory, a processor and a computer program stored in the memory and capable of running on the processor, and is characterized in that: the processor, when executing the computer program, implements the steps of the method as described above.
The present invention also discloses a computer-readable storage medium storing a computer program, characterized in that: the computer program, when being executed by a processor, implements the steps of the method as described above.
According to the invention, on the basis of considering an 11-component air model, by considering the coupling effect of hypersonic flow and a radiation source, the radiation item is considered to iterate in a hypersonic unbalanced flow and radiation calculation equation, so that the result of coupling calculation is closer to a real physical process. Specifically, the invention simulates the flow field and the flow field gas radiation spectrum information, comprehensively considersN、OBound-bound state, bound-free state, free-free state transition process of atomsIs the first of (1)Negative system, N 2 A first positive system and a second positive system,NOBeta, gamma and O of the molecule 2 Schumann-finger et al molecular bands. The detection method uses Fire II flight measurement data for verification, and provides a hypersonic aircraft radiation detection and identification method.
Compared with the prior art, the method has the advantages that the hypersonic unbalanced flow and radiation equation is used for carrying out coupling solution on the flow field information and the radiation information, the intermediate flow field information and the intermediate radiation information obtained by calculating the hypersonic unbalanced flow and radiation equation are reintroduced into the hypersonic unbalanced flow and radiation equation for iterative loop calculation until the intermediate flow field information meets the convergence condition, so that the higher detection precision of the radiation spectrum information of the hypersonic aircraft is realized, in practice, the method provides a physical model for detection and identification for a track prediction system of the hypersonic aircraft, and the optical detection equipment analyzes the hypersonic aircraft detected based on the physical model so as to predict the flight track of the hypersonic aircraft. The invention has the following specific beneficial effects:
(1) In the wave band of 3000-6000nm, the radiation intensity result of the invention is well matched with the Fire II flight test result, and the error of the radiation intensity result and the Fire II flight test result is less than 2%;
(2) The spectrum resolution of the invention can reach 0.0002nm, and compared with the spectrum resolution of 0.01nm in the prior art, the invention realizes higher-precision spectrum analysis;
(3) The radiation intensity of the invention is positioned between the upper limit and the lower limit of the error of the Fire II flight test result, and is close to the real physical radiation process;
(4) The error between the heat flow result and the Fire II flight test result is not more than 3%, and the method can be used for accurately identifying and detecting the flight track of the hypersonic aircraft;
(5) The invention discloses a domestic autonomous hypersonic aircraft radiation detection and identification system.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
Fig. 1 is a technical idea diagram of a radiation detection and identification method of a hypersonic aircraft provided in this embodiment;
FIG. 2 is a graph showing the comparison between the calculated radiation intensity of a Fire II aircraft in the 3000-6000nm band and the test result of Fire II;
FIG. 3 is a graph of the radiation intensity calculations provided in this example for a Fire II aircraft in the ultraviolet, visible, and infrared ranges;
FIG. 4 is a graph comparing calculated radiation intensity values for Fire II aircraft provided in this example with those of the prior art;
FIG. 5 is a graph showing the results of the Mach number visualization calculations provided in this embodiment with respect to the FireII aircraft symmetry plane;
fig. 6 is a graph showing the results of the wall heat flow visualization calculation provided in this embodiment with respect to the symmetry plane of the Fire ii aircraft.
Detailed Description
The invention will be further elucidated with reference to the examples and the accompanying drawing. It is to be understood that these examples are illustrative of the present invention and are not intended to limit the scope of the present invention. Variations and advantages that would occur to those skilled in the art are included within the invention without departing from the spirit and scope of the inventive concept, and the appended claims and their equivalents are intended to be covered thereby.
It will be understood that the terms "a" and "an" should be interpreted as referring to "at least one" or "one or more," i.e., in one embodiment, the number of elements may be one, while in another embodiment, the number of elements may be plural, and the term "a" should not be interpreted as limiting the number.
In the present invention, other names and terms are common names in the art, except for the names and terms that the applicant has explicitly defined.
As shown in fig. 1, the present embodiment provides a method for detecting and identifying radiation of a hypersonic aircraft, where the hypersonic aircraft takes Fire ii as an example, and the method includes:
s1: setting initial flow field information according to the flight working condition, generating initial radiation information by matching the initial flow field information with a database, and setting the initial flow field information and the initial radiation information as first input.
The flight conditions comprise the flight height, the flight Mach number and the flight attitude attack angle of the hypersonic aircraft; the initial flow field information is set manually according to the flight working condition, and comprises a gas component, a flow field gas component density, a flow field speed, a flow field pressure, energy of flow field unit mass and a flow field temperature.
The initial radiation information is to call a high-temperature gas composition database according to the gas composition and the temperature of the initial flow field information, and the corresponding radiation intensity, spectral line distribution and radiation heat are matched.
S2: according to the geometric configuration, calculation grid and flight working condition of the hypersonic aircraft, the hypersonic unbalanced flow and radiation equation calculation is carried out on the first input, and the intermediate flow field information and the intermediate radiation information are output.
The hypersonic unbalanced flow and radiation equation calculation method for outputting the intermediate flow field information comprises the following steps:
s211: an adaptive computational grid is generated from the geometry of the hypersonic vehicle.
Further, the self-adaptive grid adopts a hessian matrix with volume intersection based on three variables of speed vector size, temperature and density; the Heisen matrix considers the characteristics of a high-temperature strong shock wave flow field in hypersonic flow, so that the generation direction of the self-adaptive grid is encrypted and increased towards the directions of speed, temperature and density gradient; generating a self-adaptive grid of local encryption of the hypersonic aircraft by solving a Laplace equation in a measurement space; setting quality control parameters of the self-adaptive grid to be that the minimum grid angle is 15-30 degrees, and when the updating times of the self-adaptive grid reach a thresholdWhen the value is 10 times, the self-adaptive grid basically reaches a convergence state; if the flow field residual is greater than 10 -9 Then adjusting the calculation grid; the geometric configuration refers to the outline and dimensions of the hypersonic aircraft.
S212: according to the flight condition, constructing hypersonic unbalanced flow and radiation equations by comprehensively considering the mutual coupling effect among conservation physical quantities such as mass, momentum, energy and gas components, and the like, wherein the hypersonic unbalanced flow and radiation equations comprise:
（1）
in the method, in the process of the invention,ρis the density of the gas component of the flow field,tIs a time,xIs a coordinate,pIs the flow field pressure,uIs the flow field speed,EEnergy per unit mass,Y l As a gaseous componentlThe mass fraction of (C) and T are the temperature of the flow field,i,j=(1,2,3)a vector component representing the physical quantity,l=(1,2,...,N)the gas composition is represented by the formula,τ ij is the tensor of the viscous stress,represents the chemical reaction source item,/->Representing the heat source term(s),V l,i representing the rate of diffusion of the gaseous component,q i is the transport characteristic of heat flux representing energy in a flow field, comprises a Fourier heat diffusion term and energy transport caused by gas component diffusion,h l is a gaseous componentlThe corresponding enthalpy of the heat transfer is,λis a thermal diffusion coefficient, is calculated by Pr number, and reflects the ratio of momentum transport capacity to heat transport capacity; in the selection ofρ、ρu、ρE、ρY l The constant conservation physical quantity is used as an original variable and corresponds to the conservation laws of mass, momentum, energy and chemical components respectively.
Wherein the known parameter has timetCoordinates ofxTensor of viscous stressτ ij And a flight condition, the flight condition having a specific mass fractionY l Gas compositionlCorresponding enthalpyh l Coefficient of thermal diffusionλChemical reaction SourceHeat source item->Speed of diffusion of gas componentsV l,i Heat fluxq i 。
Wherein the viscous term comprises、/>Non-sticky items include->、/>、、/>The time advance item includes->。
The flight conditions include flight altitude, flight Mach number and flight attitude angle of attack. In this embodiment, the settings of the flight conditions include a database of flight mach numbers ma=20, a flight attitude attack angle of 20 ° and 11 gas components.
The database of 11 gas components can be obtained according to the flying height, and the various gas components in the atmosphere participate in the emission and absorption process, and the 11 gas components comprise gas components generated by the chemical reaction of two elements of N and O and trace gas components in the air, such asCO 2 、H 2 O、CO、CH 4 、CN、C 2 H 2 Etc. Of the calculation equations for the 11 gas components, only the equation for the 10 gas components is solved, and the 11 th gas component fraction is obtained by subtracting the sum of the other gas component fractions from 1.
S213: carrying out numerical solution on the hypersonic unbalanced flow and radiation equation on the self-adaptive calculation grid, calculating to obtain intermediate flow field information, wherein the output intermediate flow field information comprises gas components and gas component density of a flow fieldρFlow field velocityuFlow field pressurepEnergy per unit mass of flow fieldEFlow field temperatureT。
Further, the method for carrying out numerical solution on hypersonic unbalanced flow and radiation equation on the self-adaptive grid specifically comprises the following steps: for the non-sticky term of the equation (1), a Steger-waring flow vector splitting method is adopted, and a high-order MUSCL format is selected for dispersion; for the viscous term of the equation (1), dispersing by adopting a 2-order precision center difference format or a 2-order precision windward format to realize effective analysis of small-scale vortexes; for the time propulsive term of the equation (1), an explicit range-Kutta method of a three-order TVD format is adopted, and a smaller time step is selected, so that the iteration process is more stable; adding an artificial super-viscosity term to the viscosity term of equation (1), the artificial super-viscosity term being based on the turbulent viscosity coefficient associated with the adaptive meshMake the construction->Wherein the empirical constant C t Is taken to be 0.02-0.03, S Δ Is the viscous stress Zhang Liangxiang associated with the grid dimensions of the adaptive grid.
The hypersonic unbalanced flow and radiation equation calculation output intermediate radiation information method comprises the following steps:
s221: thermodynamic parameters such as temperature, gas components and radiation required by hypersonic unbalanced flow and radiation calculation are obtained according to the initial flow field information or the intermediate flow field informationElectron number density, etc., to calculate the absorption coefficient of each micelle of high-temperature unbalanced gas componentK η ，K η Expressed as:
in the method, in the process of the invention,ηis the wave number of the wave,absorption coefficients of flow field gas components in bound-bound (bound-free) and bound-free (bound-free) processes, respectively,/->Is the absorption coefficient of the molecular band during the transition,lrefers to the number of continuous irradiation of molecules;K η a plurality of gas micro-clusters are provided, each gas micro-cluster is provided with a corresponding gas micro-clusterK η 。
For the bind-bind process, the gas component is recovered from a low energy leveliTransition to a high energy leveljIn the process, the spectral radiation intensity of spontaneous transition of unit volume and unit solid angle in the specified sight directionEThe expression form is as follows:
in the method, in the process of the invention,is a spectral line type function, and meets the normalization condition,g j is the energy leveljIs used to determine the degree of degeneracy of (1),N j is at an energy leveljIs used for the electron number density of the (a),A ji the einstein coefficient is represented by a number of coefficients,ΔE ji is the slave energy leveljTo the energy leveliThe energy of the photons released by the transition;
wherein the wavelength of the emitted light is:
in the method, in the process of the invention,his the planck constant of the sample,cis the speed of light.
From this, the absorption coefficient of the binding-binding process is obtainedThe calculation formula of (2) is as follows:
in the method, in the process of the invention,N i is the first gas componentiThe electron number density of the energy level,N j is at an energy leveljIs used for the electron number density of the (a),g j is the energy leveljIs used to determine the degree of degeneracy of (1),A ji representing the einstein coefficient, lambda being the wavelength of the emitted light,his the planck constant of the sample,cis the speed of light, which is the speed of light,v ji is from a high energy leveljTo a low energy leveliIs used to determine the transition speed of the (c) in the transition,is a spectral line type function of the emitted light with the wavelength lambda and meets the normalization condition.
Absorption coefficient of the bound-free processThe calculation of (a) uses the Gaunt factorg bf (η)Form representation of the photoelectric absorption cross section of the modified gas component,/->The calculation formula of (2) is as follows:
in the method, in the process of the invention,is the photoelectric absorption of the bound-free state of the energy level iCross section of the tube>Is the classical photoelectric absorption cross section of Kramer,g bf (η)is a bound-free form gap factor.
The saidThe calculation formula of (2) is as follows:
in the method, in the process of the invention,η ij is the wavenumber of the center of the spectral line emitted during the transition between energy level i and energy level j,N i is the first gas componentiElectron number density of energy level, R 2 Is the square of the band system electron transition array element,q ij is the Frank-Condon factor,S ij is a line intensity factor which is a factor of the line intensity,F(η)is a line-type factor of the spectral line,ris the electron orbit radius.
S222: calculating radiation intensity through a radiation transmission equation, wherein the radiation transmission equation is as follows:
in the method, in the process of the invention,I η is a certain position in the flow fieldsThe intensity of the radiation in the direction of the beam,J η the spectral emission coefficients can be obtained by kirchhoff's law and based on local thermodynamic equilibrium assumptions.
Further, the method comprises the steps of. Cutting the flow field into a plurality of plate layers along a required line of sight by adopting a slicing method, assuming that thermodynamic parameters of the flow field in the plate layers are uniform, solving the radiation transmission equation by taking gas components and temperature information of grid points of corresponding self-adaptive grids in the plate layers as input conditions of hypersonic unbalanced flow and radiation calculation, and assuming thatxRepresenting the distance of the radiation vertically passing through 2 of the plate layers, the gas is obtained in the s directionUpxRadiation intensity at a locationI η The method comprises the following steps:
in the method, in the process of the invention,L v andL v2 representing the optical thickness at the reference position s and any position s2, which is the absorption coefficient of the micelle at the corresponding positionK η Is the inverse of the number of (a),B v indicating the intensity of the blackbody radiation,tis an integral imaginary variable which is used to calculate the integral,θis the radioscopic solid angle.
Thereby, the radiation intensity of the hypersonic aircraft surface high-temperature unbalanced gas is obtainedI η And spectral line distribution.
S223: the radiation intensity obtained by calculationI η And the recorded spectral line distribution and radiant heat are output as intermediate radiant information.
S3: when the convergence condition is met, the intermediate flow field information and the intermediate radiation information are used as second input and output; and when the convergence condition is not met, taking the intermediate flow field information and the intermediate radiation information as a first input, carrying out calculation on hypersonic unbalanced flow and radiation equation, iterating and outputting the first input.
The convergence condition is that the difference value of the hypersonic unbalanced flow and the intermediate flow field information (comprising the gas component density, the flow field speed, the flow field pressure and the energy of the flow field unit mass) which is output by two adjacent iterations of radiation calculation is smaller than a first threshold value; the first threshold is 10 -4 ~10 -5 。
Further, the heat source items comprise radiant heat and other heat sources, the heat source items are known parameters of hypersonic unbalanced flow and a radiation equation, intermediate radiation information is calculated and output according to the hypersonic unbalanced flow and the radiation equation, the intermediate radiation information comprises the radiant heat, the radiant heat in the intermediate radiation information is used as the heat source items, the known parameters of the hypersonic unbalanced flow and the radiation equation are updated, and calculation of the hypersonic unbalanced flow and the radiation equation is continued, so that iteration of the first input is achieved.
S4: extracting and outputting radiation spectrum information of radiation intensity distribution at different wavelengths of the hypersonic aircraft according to the second input; the radiation spectrum information comprises radiation intensity, spectrum resolution and heat flow result.
Further, the initial flow field information and the intermediate flow field information comprise gas components, gas component density of the flow field, flow field speed, flow field pressure, energy of unit mass of the flow field and flow field temperature; the initial radiation information and the intermediate radiation information comprise radiation intensity, spectral line distribution and radiation heat.
The hypersonic aircraft radiation detection and identification system and method are described in a specific embodiment, the calculation result of the embodiment is compared with the Fire II flight test result, and the embodiment analyzes the radiation spectrum information of Fire II under the given Ma20 condition.
As shown in FIG. 2, comparing the radiation intensity of the high-temperature unbalanced gas radiation simulation result calculated by the method with the radiation intensity of the Fire II flight test result, it can be seen that the radiation intensity result calculated by the method has higher coincidence degree with the radiation intensity of the Fire II flight test result in a wave band of 3000-6000nm, and the error of the two is less than 2%.
In this embodiment, the radiation spectrum information in the ultraviolet (200 nm-400 nm), visible (400 nm-760 nm) and infrared (2.7 um-4.3 um) ranges is studied, and as shown in fig. 3, the spectrum obtained by the method of the invention has extremely high resolution, reaching 0.0002nm, and higher-precision spectrum analysis is realized compared with the spectrum resolution of 0.01nm in the prior art.
In this example, the radiation intensity results of Fire ii aircrafts in the wavelength range of 2.2-4.1 ev (1 ev=1240 nm) are compared with those of the prior art, and as shown in fig. 4, the error between the calculated result obtained by the method of the present invention and the radiation intensity of Fire ii flight test results is significantly better than those of prior art document 1 (Sutton k. Air radiation revisited [ C/OL ]//19th Thermophysics Conference, snowmass, CO, U.S. a.: american Institute of Aeronautics and Astronautics, 1984.2012, published), document 2 (Gupta R. Navier-Stokes and viscous shock-layer solutions for radiating hypersonic flows [ C/OL ]//22nd Thermophysics Conference. Honoulu, HI, U.s.a.: american Institute of Aeronautics and Astronautics, 1987.2012, published) and document 3 (Johnston C O, HOLLIS B R, sutton k. Nonequilibrium Stagnation-Line Radiative Heating for Fire II [ J/OL ]. Journal of Spacecraft and Rockets, 2008, 45 (6): 5-1195). The results of these 3 prior art experiments were compared with those of the examples of the present invention. As shown in FIG. 4, compared with the prior art, the experimental result of the invention is more stably positioned between the upper limit and the lower limit of the error of the Fire II flight test result, especially the data of 1643s and 1645s are compared, the radiation intensity result of the prior art is respectively 45.5% and 47.4% higher than the upper limit of the error of the Fire II flight test result, and the calculation result of the invention is exactly positioned between the upper limit and the lower limit of the error of the Fire II flight test result, which indicates that the calculation result of the invention is more approximate to the real physical radiation process.
As shown in fig. 5, the mach number visualization distribution diagram of the present embodiment on the symmetry plane of the Fire ii aircraft; as shown in fig. 6, the wall heat flow visualization distribution diagram of the present embodiment on the symmetry plane of the Fire ii aircraft is shown. The invention calculates the heat flow result of the standing point, wherein the heat flow result comprises the standing point heat flow Qc=191W/cm contributed by heat conduction 2 Heat flow qrad=58W/cm generated by heat radiation 2 The relative error between the heat flow result and the Fire II flight test result is about 3%, and the heat flow result calculated by Johnston team (the standard pole research result in the prior art) is 30% different from the Fire II flight test result (the abstract part in reference 3), so that the hypersonic aircraft radiation detection and identification method is obviously superior to the Johnston team research method.
In summary, the hypersonic aircraft radiation detection and recognition system and method provided by the invention can realize higher detection precision of radiation spectrum information of the hypersonic aircraft by carrying out coupling solution on flow field information and radiation information through hypersonic unbalanced flow and radiation calculation, can provide a physical model for detection and recognition for a trajectory prediction system of the hypersonic aircraft, and can realize ultra-long-distance detection and recognition of hypersonic flight targets.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. It is therefore intended that the following claims be interpreted as including the preferred embodiments and all such alterations and modifications as fall within the scope of the invention.
The above detailed description is intended to illustrate the present invention by way of example only and not to limit the invention to the particular embodiments disclosed, but to limit the invention to the precise embodiments disclosed, and any modifications, equivalents, improvements, etc. that fall within the spirit and scope of the invention as defined by the appended claims.
Claims (8)
1. A hypersonic aircraft radiation detection and identification method can provide a detection and identification physical model for a hypersonic aircraft track prediction system; characterized in that the method comprises:
setting initial flow field information and initial radiation information as a first input;
carrying out calculation by taking the first input into hypersonic unbalanced flow and radiation equation, and outputting intermediate flow field information and intermediate radiation information;
when the convergence condition is met, the intermediate flow field information and the intermediate radiation information are used as second input and output; when the convergence condition is not met, taking the intermediate flow field information and the intermediate radiation information as a first input, carrying out calculation on hypersonic unbalanced flow and a radiation equation, iterating and outputting the first input;
extracting and outputting radiation spectrum information of the hypersonic aircraft according to the second input;
the hypersonic unbalanced flow and radiation equation calculation output intermediate flow field information method comprises the following steps:
generating an adaptive computational grid according to the geometric configuration of the hypersonic aircraft;
according to the flight working conditions, constructing the hypersonic unbalanced flow and radiation equation, and carrying out hypersonic unbalanced flow and radiation calculation;
carrying out numerical solution on the hypersonic unbalanced flow and radiation equation on the self-adaptive calculation grid to obtain intermediate flow field information;
the hypersonic unbalanced flow and radiation calculation output intermediate radiation information method comprises the following steps:
according to the initial flow field information or the intermediate flow field information, the absorption coefficient of the high-temperature unbalanced gas component of each micelle is calculated;
calculating the radiation intensity;
outputting the calculated radiation intensity and the recorded spectral line distribution and the radiation heat as intermediate radiation information;
and the convergence condition is that the difference value between hypersonic unbalanced flow and intermediate flow field information output by two adjacent iterations of a radiation equation is smaller than a first threshold value.
2. The method according to claim 1, wherein the hypersonic unbalanced flow and radiation equation comprises a heat source term with known parameters, the intermediate radiation information comprises radiation heat, the radiation heat in the intermediate radiation information is used as the heat source term to be input, and the hypersonic unbalanced flow and radiation equation is calculated to realize iteration of the first input.
3. The method of claim 1, wherein the difference in intermediate flow field information comprises differences in adjacent two iterations of output of parameters of flow field gas composition density, flow field velocity, flow field pressure, energy per unit mass of flow field.
4. The method of claim 1, wherein the first threshold is 10 -4 ~10 -5 。
5. The method of claim 1, wherein the hypersonic unbalanced flow and radiation equation comprises:
in the method, in the process of the invention,ρis the density of the gas component of the flow field,tIs a time,xIs a coordinate,pIs the flow field pressure,uIs the flow field speed,EEnergy per unit mass,Y l As a gaseous componentlThe mass fraction of (C) and T are the temperature of the flow field,i,j=(1,2,3)a vector component representing the physical quantity,l=(1,2,...,N)the gas composition is represented by the formula,τ ij is the viscous stress tensor, +.>Represents the chemical reaction source item,/->Representing the heat source term(s),V l,i representing the rate of diffusion of the gaseous component,q i is the transport property of heat flux representing energy in the flow field,h l is a gaseous componentlThe corresponding enthalpy of the heat transfer is,λis the coefficient of thermal diffusion and,ρ、ρu、ρE、ρY l the constant conservation physical quantity is used as an original variable and corresponds to the conservation laws of mass, momentum, energy and chemical components respectively.
6. Hypersonic aircraft radiation detection and identification system employing the method as claimed in any one of claims 1 to 5, characterized in that it comprises:
the hypersonic unbalanced flow and radiation calculation module is used for calculating and iterating flow field information and radiation information; taking initial flow field information and initial radiation information as first input; and/or, calculating according to the first input, and outputting and iterating the intermediate flow field information and the intermediate radiation information of the first input;
the coupling module is used for continuously iterating the first input, judging whether the convergence condition is met, and taking the first input as the second input and outputting if the convergence condition is met; if the convergence condition is not met, continuing to iterate the first input;
the hypersonic unbalanced flow and radiation calculation module comprises a known parameter heat source item, the intermediate radiation information comprises radiation heat, the radiation heat in the intermediate radiation information is used as the heat source item to be input, hypersonic unbalanced flow and radiation calculation is carried out, and iteration of the first input is achieved.
7. A server comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized by: the processor, when executing the computer program, implements the steps of the method according to any one of claims 1-5.
8. A computer-readable storage medium storing a computer program, characterized in that: the computer program implementing the steps of the method according to any of claims 1-5 when executed by a processor.
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