CN110765674B - Pneumatic optical effect calculation method and system - Google Patents
Pneumatic optical effect calculation method and system Download PDFInfo
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Abstract
The invention discloses a pneumatic optical effect calculation method and a system, comprising the following steps: analyzing temperature field data, pressure field data and density field data of external gas of the aircraft by adopting fluid mechanics analysis software; calculating to obtain refractive index field data outside the aircraft according to the temperature field data, the pressure field data and the density field data of the external gas and the influence relationship of the external gas on the refractive index; extracting the equal-refractive-index surface through the refractive-index field data and the set selection interval of the equal-refractive-index surface to obtain discrete equal-refractive-index surface data; fitting the data of the equal refractive index surfaces in a polynomial fitting mode to obtain a continuous function equation of the equal refractive index surfaces, wherein the refractive indexes between the adjacent equal refractive index surfaces are replaced by the same equivalent refractive index value; and inputting a continuous function equation of the equal refractive index surfaces and the equivalent refractive index value between the adjacent equal refractive index surfaces into optical design software, tracking light rays through the optical design software, and evaluating light beam deflection caused by the pneumatic optical effect.
Description
Technical Field
The invention belongs to the field of pneumatic optics, can be applied to the problem of imaging quality reduction of a guided weapon seeker caused by pneumatic optical imaging offset, and particularly relates to a pneumatic optical effect computing system and method.
Background
When the aircraft flies at high speed in the atmosphere, the optical hood of the imaging detection system and external air flow have violent interaction to form complex flow field structures such as shock waves, expansion waves, strong turbulence boundary layers and the like. The airborne optical/imaging system of the aircraft, whether it is the active optical system of the light beam emission, such as the airborne laser, it aims or focuses on the goal with the light beam of high energy, achieve the goal of destroying or even killing the goal; or a passive system that receives the beam, such as an infrared guidance system, that detects the infrared radiation spot of the target to meet the requirements for tracking a particular target. Operation is adversely affected by this flow field. In an active system, the flow field attenuates and deviates the energy of a projected light beam from an irradiation target, in a passive system, an image received by an optical system is deviated, blurred and jittered, and the influence or action of the gas flow field on optical propagation and an optical imaging system is called a pneumatic optical effect.
Because parameters such as density, temperature and the like of airflow in the flow field change all the time, the parameters have great influence on an optical imaging detection system of the aircraft, so that key parameters such as imaging quality and accurate positioning can be directly influenced, and the acquisition of the aircraft on a target object can also be influenced. The pneumatic optical effect is that the gas density is distributed in an irregular and non-uniform flow field, the distribution of the gas refractive index is influenced, the transmission tracking process of light rays in the flow field is further influenced, and the optical distortion of optical imaging is caused.
The ray tracing method is a commonly used method for calculating beam deflection, and obtains a transmission path of a ray by tracing refraction occurring when the ray passes through an interface of two materials having different refractive indexes. When the calculation of the aerodynamic optical effect is carried out, a calculation grid for ray tracing is generally defined in advance, and the idea of discretization calculation is adopted, so that the refractive index of air in each small grid is used as the same refractive index value niAnd i is a small lattice number. The calculation of the whole light ray tracing needs to be carried out in the grid, the edge of the grid is the initial line of the light ray tracing, after the calculation of the light ray tracing is started, the calculation is gradually recurred from the edge of the grid until the light ray is transmitted to the lower edge of the grid, namely the sensor inside the optical window. The refractive indexes of two adjacent small lattices may be different from each other, and when light rays are transmitted from one small lattice to enter the other small lattice, the light rays are refracted on the interface.
The grid discrete mode is adopted for calculation, the edge lines of the grid units are difficult to coincide with the equal refractive index lines, so that the refractive index inside the grid is greatly changed, when the size of the grid unit is larger, a large error exists, the error is accumulated once when light passes through one grid, and the final calculation result has obvious errors; the result is corrected by adopting the grid encryption method, but the grid encryption generates a large amount of data and calculation, the calculation time is increased, and the error accumulation times are also increased.
By adopting a grid discrete mode, when light rays enter the grid intersection point position, the light ray deflection calculation of the intersection point position is complex and difficult to calculate.
By adopting a grid discrete mode, a program for calculating the light ray deflection needs to be manually written, the existing mature commercial software cannot be used, and the calculation efficiency, the calculation maturity and the calculation precision are difficult to guarantee.
The grid discrete mode is adopted, which is equivalent to three-dimensional discrete of the whole field space, and the calculation amount is large.
Considering that the gradient distribution of the full-field refractive index is not uniform, the calculation amount is wasted at the position with small gradient by the mode of equidistant space grid division, and the calculation at the position with large gradient is not accurate.
Disclosure of Invention
The invention provides a system and a method for calculating an aerodynamic optical effect, which aim at the problems and the defects in the prior art, solve the problem that the aerodynamic optical effect is not calculated by a relatively accurate numerical value at present, solve the problems of error accumulation and large calculation amount caused by grid dispersion, solve the problem that intersection point incident light rays are difficult to calculate due to grid dispersion, solve the problem of large calculation amount caused by three-dimensional dispersion in a full-field space, and solve the problem that an equidistant division mode is not suitable for a non-uniform gradient distribution refractive index field.
The invention solves the technical problems through the following technical scheme:
the invention provides a pneumatic optical effect calculation method which is characterized by comprising the following steps:
s1, analyzing outflow field information of the aircraft flying in the atmosphere by adopting fluid mechanics analysis software, wherein the outflow field information comprises temperature field data, pressure field data and density field data of external air;
s2, calculating to obtain refractive index field data outside the aircraft according to the temperature field data, the pressure field data and the density field data of the outside air and the influence relationship of the outside air on the refractive index;
s3, extracting the equal refractive index surface through the refractive index field data and the set selection interval of the equal refractive index surface to obtain discrete equal refractive index surface data;
s4, fitting the equal refractive index surface data in a polynomial fitting mode to obtain a continuous function equation of the equal refractive index surfaces, wherein the refractive indexes between the adjacent equal refractive index surfaces are replaced by the same equivalent refractive index value;
and S5, inputting the continuous function equation of the equal refractive index surfaces and the equivalent refractive index value between the adjacent equal refractive index surfaces into optical design software, and performing ray tracing through the optical design software to evaluate the beam deflection caused by the pneumatic optical effect.
Preferably, in step S4, the equivalent refractive index value between adjacent equal refractive index surfaces is selected as the average value of the refractive indices of the adjacent equal refractive index surfaces.
Preferably, in step S4, the polynomial fitting formula is:
where x, y, z are spatial position coordinates, c is vertex curvature, and k-e2Is a constant of the curve, e2As eccentricity, B1、B2As a coefficient of tilt, AiIs a polynomial coefficient, and the coefficient is,
preferably, in step S5, the optical design software performs optical path simulation by using an optical tracking method.
Preferably, in step S1, the fluid mechanics analysis software employs CFD software.
The invention also provides a pneumatic optical effect calculation system which is characterized by comprising an analysis module, a calculation module, an extraction module, a fitting module and an evaluation module;
the analysis module is used for analyzing the outflow field information of the aircraft flying in the atmosphere by adopting fluid mechanics analysis software, wherein the outflow field information comprises temperature field data, pressure field data and density field data of external gas;
the calculation module is used for calculating to obtain refractive index field data outside the aircraft according to the temperature field data, the pressure field data and the density field data of the external gas and the influence relationship of the external gas on the refractive index;
the extraction module is used for extracting the equal refractive index surface through the refractive index field data and the set selection interval of the equal refractive index surface so as to obtain discrete equal refractive index surface data;
the fitting module is used for fitting the equal refractive index surface data in a polynomial fitting mode to obtain a continuous function equation of the equal refractive index surfaces, and the refractive indexes between the adjacent equal refractive index surfaces are replaced by the same equivalent refractive index value;
the evaluation module is used for inputting a continuous function equation of the equal refractive index surface and an equivalent refractive index value between adjacent equal refractive index surfaces into optical design software, and the optical design software is used for tracking light rays and evaluating light beam deflection caused by the pneumatic optical effect.
Preferably, the equivalent refractive index values between adjacent iso-refractive index surfaces are selected from the average of the refractive indices of the adjacent iso-refractive index surfaces.
Preferably, the polynomial fitting formula is:
where x, y, z are spatial position coordinates, c is vertex curvature, and k-e2Is a constant of the curve, e2As eccentricity, B1、B2As a coefficient of tilt, AiIs a polynomial coefficient, and the coefficient is,
preferably, the optical design software performs optical path simulation by using an optical tracking method.
Preferably, the fluid mechanics analysis software employs CFD software.
On the basis of the common knowledge in the field, the above preferred conditions can be combined randomly to obtain the preferred embodiments of the invention.
The positive progress effects of the invention are as follows:
the invention adopts the mode of surface dispersion of equal refractive index, so that the change of the internal refractive index of each discrete unit is not large, and a large amount of encryption work is not needed, thereby greatly reducing the calculation scale; the method has the advantages that the method has a mode of dispersing the refractive index surfaces, and does not have grid intersection points, so that the problem that light rays are incident on the grid intersection points does not need to be considered; the method adopts a mode of dispersing the equal refractive index surface, the structure shape after dispersion is similar to the input format of optical design analysis software, and commercial optical design analysis software can be called to perform the final step of optical evaluation after processing.
Drawings
Fig. 1 is a cross-sectional view of density field distribution data according to a preferred embodiment of the present invention.
FIG. 2 is a schematic diagram of discrete iso-refractive surfaces in accordance with a preferred embodiment of the present invention.
FIG. 3 is a flow chart of a method for calculating the aerodynamic optical effect according to a preferred embodiment of the present invention.
FIG. 4 is a block diagram of a pneumatic optical effect computing system according to a preferred embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
As shown in fig. 3, the present embodiment provides a method for calculating an aerodynamic optical effect, which includes the following steps:
Fig. 1 is a cross-sectional view of density field distribution data, the middle ellipsoid is an aircraft optical window, such as a missile with visible light guidance or infrared guidance, there is an optical window at the front end of the bullet nose, and the optoelectronic device in the optical window can observe the external image through the optical window. The outside of the optical window is the atmosphere because the outside gas is compressed during high-speed flight of the aircraft, resulting in a change in the refractive index profile, and the grey value of each point in the picture is used instead of the density value.
And 102, calculating to obtain refractive index field data outside the aircraft according to the temperature field data, the pressure field data and the density field data of the outside air and the influence relationship of the outside air on the refractive index.
And 103, extracting the equal-refractive-index surface according to the refractive-index field data and the set selection interval of the equal-refractive-index surface to obtain discrete equal-refractive-index surface data.
Fig. 2 is a graph in which discrete refractive index field data of fig. 1 is processed, iso-refractive index surfaces are extracted at set intervals of the iso-refractive index surfaces, and discrete iso-refractive index surface data is obtained, in which the refractive index difference between two adjacent iso-refractive index surfaces is a set value, and the air between two adjacent iso-refractive index surfaces is set to have the same refractive index. The continuous function equation of the iso-refractive index surface is fitted by the spatial position of each point of the iso-refractive index surface. Wherein n1, n2, n3, ni, nj, nk, etc. are refractive index values, and the middle ellipsoid in fig. 2 is the aircraft optical window.
And 104, fitting the equal refractive index surface data in a polynomial fitting mode to obtain a continuous function equation of the equal refractive index surfaces, wherein the refractive indexes between the adjacent equal refractive index surfaces are replaced by the same equivalent refractive index value, and the equivalent refractive index value between the adjacent equal refractive index surfaces is the average value of the refractive indexes of the adjacent equal refractive index surfaces.
The polynomial fitting formula is:
where x, y, z are spatial position coordinates, c is vertex curvature, and k-e2Is a constant of the curve, e2As eccentricity, B1、B2As a coefficient of tilt, AiIs a polynomial coefficient, and the coefficient is,
and 105, inputting a continuous function equation of the equal-refractive-index surfaces and the equivalent refractive index value between the adjacent equal-refractive-index surfaces into optical design software (for example, optical path simulation is carried out by adopting an optical tracking method, and CodeV, Zemax or similar optical design software is specifically adopted), carrying out ray tracking through the optical design software, and evaluating the beam deflection caused by the pneumatic optical effect.
As shown in fig. 4, the present embodiment further provides an aero-optical effect calculation system, which includes an analysis module 1, a calculation module 2, an extraction module 3, a fitting module 4, and an evaluation module 5.
The analysis module 1 is used for analyzing the outflow field information of an aircraft flying in the atmosphere by using fluid mechanics analysis software (such as CFD software), wherein the outflow field information comprises temperature field data, pressure field data and density field data of external gas.
The calculation module 2 is used for calculating and obtaining the refractive index field data outside the aircraft according to the temperature field data, the pressure field data and the density field data of the outside air and the influence relationship of the outside air on the refractive index.
The extraction module 3 is used for extracting the isorefractive index surface through the refractive index field data and the set selection interval of the isorefractive index surface so as to obtain discrete isorefractive index surface data.
The fitting module 4 is configured to fit the equal refractive index surface data in a polynomial fitting manner to obtain a continuous function equation of the equal refractive index surfaces, the refractive indexes between adjacent equal refractive index surfaces are replaced by the same equivalent refractive index value, and the equivalent refractive index value between adjacent equal refractive index surfaces is the average refractive index value of the adjacent equal refractive index surfaces.
The polynomial fitting formula is:
where x, y, z are spatial position coordinates, c is vertex curvature, and k-e2Is a constant of the curve, e2As eccentricity, B1、B2As a coefficient of tilt, AiIs a polynomial coefficient, and the coefficient is,
the evaluation module 5 is configured to input a continuous function equation of the equal refractive index surface and an equivalent refractive index value between adjacent equal refractive index surfaces into optical design software (for example, optical path simulation is performed by using an optical tracking method, specifically, CodeV, Zemax or similar optical design software is used), perform ray tracking by using the optical design software, and evaluate beam deflection caused by the pneumatic optical effect.
The analysis process for realizing the pneumatic optical imaging deflection is introduced, a means for solving the pneumatic optical effect is provided, and a mode of isorefraction surface dispersion is adopted, as shown in fig. 2, the problems of low calculation efficiency, large calculation error and difficult light deviation evaluation caused by grid dispersion can be solved; and fitting the discrete iso-refractive index surface data into a continuous iso-refractive index equation representation by adopting a polynomial fitting mode, so that an interface with optical design software can be opened, and the final-step evaluation can be carried out by means of the optical design software.
The invention provides a high-precision pneumatic optical effect calculation method, which solves the problem that the prior art can not calculate accurately; the isorefractive index surface is extracted in an isorefractive index dispersion mode, namely, one-dimensional dispersion is carried out on a spatial field, and compared with the traditional three-dimensional grid dispersion mode, the method has the advantages that the calculation amount is reduced, and the calculation efficiency is improved; by setting the selection interval of the equal refractive index surfaces (for example, one equal refractive index surface is selected for each 0.01 refractive index), the obtained equal refractive index surfaces are sparse at the position with smaller gradient, dense at the position with larger gradient, and can automatically adapt to the gradient distribution of the refractive index field, thereby ensuring the calculation precision.
The polynomial fitting formula provided by the invention is added with B1x+B2The y term is added, namely the inclination term is added, the equal refractive index surface inclination angle caused by the attack angle of a high-speed aircraft such as a missile during flying is fully considered, the equal refractive index fitting process can be simplified, the fitting efficiency is improved, and the fitting accuracy is improved.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.
Claims (8)
1. A pneumatic optical effect calculation method is characterized by comprising the following steps:
s1, analyzing outflow field information of the aircraft flying in the atmosphere by adopting fluid mechanics analysis software, wherein the outflow field information comprises temperature field data, pressure field data and density field data of external air;
s2, calculating to obtain refractive index field data outside the aircraft according to the temperature field data, the pressure field data and the density field data of the outside air and the influence relationship of the outside air on the refractive index;
s3, extracting the equal refractive index surface through the refractive index field data and the set selection interval of the equal refractive index surface to obtain discrete equal refractive index surface data;
s4, fitting the equal refractive index surface data in a polynomial fitting mode to obtain a continuous function equation of the equal refractive index surfaces, wherein the refractive indexes between the adjacent equal refractive index surfaces are replaced by the same equivalent refractive index value;
s5, inputting a continuous function equation of the equal refractive index surfaces and an equivalent refractive index value between adjacent equal refractive index surfaces into optical design software, tracking light rays through the optical design software, and evaluating light beam deflection caused by the pneumatic optical effect;
in step S4, the polynomial fitting equation is:
where x, y, z are spatial position coordinates, c is vertex curvature, and k-e2Is a constant of the curve, e2As eccentricity, B1、B2As a coefficient of tilt, AiIs a polynomial coefficient, and the coefficient is,
2. the method of claim 1, wherein in step S4, the average value of the refractive indices of the adjacent iso-refractive index surfaces is selected as the equivalent refractive index value between the adjacent iso-refractive index surfaces.
3. The method for calculating an aerodynamic optical effect according to claim 1, wherein in step S5, the optical design software performs optical path simulation using an optical tracing method.
4. The method of calculating aerodynamic optical effects of claim 1, wherein in step S1, the fluid mechanics analysis software employs CFD software.
5. The pneumatic optical effect calculation system is characterized by comprising an analysis module, a calculation module, an extraction module, a fitting module and an evaluation module;
the analysis module is used for analyzing the outflow field information of the aircraft flying in the atmosphere by adopting fluid mechanics analysis software, wherein the outflow field information comprises temperature field data, pressure field data and density field data of external gas;
the calculation module is used for calculating to obtain refractive index field data outside the aircraft according to the temperature field data, the pressure field data and the density field data of the external gas and the influence relationship of the external gas on the refractive index;
the extraction module is used for extracting the equal refractive index surface through the refractive index field data and the set selection interval of the equal refractive index surface so as to obtain discrete equal refractive index surface data;
the fitting module is used for fitting the equal refractive index surface data in a polynomial fitting mode to obtain a continuous function equation of the equal refractive index surfaces, and the refractive indexes between the adjacent equal refractive index surfaces are replaced by the same equivalent refractive index value;
the evaluation module is used for inputting a continuous function equation of the equal refractive index surface and an equivalent refractive index value between adjacent equal refractive index surfaces into optical design software, tracking light rays through the optical design software and evaluating light beam deflection caused by a pneumatic optical effect;
the polynomial fitting formula is:
where x, y, z are spatial position coordinates, c is vertex curvature, and k-e2Is a constant of the curve, e2As eccentricity, B1、B2As a coefficient of tilt, AiIs a polynomial coefficient, and the coefficient is,
6. an aero-optical effect calculation system according to claim 5 wherein the equivalent refractive index values between adjacent iso-refractive surfaces are selected to be the average of the refractive indices of the adjacent iso-refractive surfaces.
7. The pneumatic optical effect computing system according to claim 5, wherein the optical design software performs optical path simulation using optical tracing.
8. The aero-optical effect calculation system according to claim 5 wherein the fluid dynamics analysis software employs CFD software.
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| CN112484783B (en) * | 2020-12-04 | 2022-03-29 | 中国航空工业集团公司北京长城计量测试技术研究所 | Optical-based gas pressure and temperature high-precision synchronous measurement method |
| CN115452326B (en) * | 2022-09-02 | 2023-08-15 | 上海索辰信息科技股份有限公司 | Thermo-optical effect analysis method based on disordered refractive index |
| CN115510694B (en) * | 2022-11-23 | 2023-02-21 | 中国航天三江集团有限公司 | Turbulent flow boundary layer aerodynamic optical effect inhibition method based on injection jet flow |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107832532A (en) * | 2017-11-14 | 2018-03-23 | 哈尔滨工业大学 | A kind of Pneumatic light transmission effects are to high-speed aircraft image quality numerical computation method |
| CN109740288A (en) * | 2019-01-24 | 2019-05-10 | 北京航空航天大学 | A method of the aero-optical effect of simulation High Speed Flow Field culminant star optical transport |
| CN110108271A (en) * | 2019-04-11 | 2019-08-09 | 北京航空航天大学 | Starlight deviation compensation method caused by a kind of aero-optical effect |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107832532A (en) * | 2017-11-14 | 2018-03-23 | 哈尔滨工业大学 | A kind of Pneumatic light transmission effects are to high-speed aircraft image quality numerical computation method |
| CN109740288A (en) * | 2019-01-24 | 2019-05-10 | 北京航空航天大学 | A method of the aero-optical effect of simulation High Speed Flow Field culminant star optical transport |
| CN110108271A (en) * | 2019-04-11 | 2019-08-09 | 北京航空航天大学 | Starlight deviation compensation method caused by a kind of aero-optical effect |
Non-Patent Citations (1)
| Title |
|---|
| 小入射角条件下气动光学成像偏移;张士杰等;《光学学报》;20121031;第32卷(第10期);第1001002-2页右栏第1段，第1001002-2至1001002-6页第2-4节及图1-5 * |
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