CN110598344A - Full-link dynamic image quality numerical simulation system and method for optical system of space camera - Google Patents
Full-link dynamic image quality numerical simulation system and method for optical system of space camera Download PDFInfo
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Abstract
A full-link dynamic image quality numerical simulation system and method for an optical system of an aerospace camera relate to the technical field of photoelectric imaging and solve the problem that image quality restriction factors of the existing on-orbit camera are complex and difficult to evaluate singly, and comprise an optical simulation module, a structure simulation module, a thermal simulation module and a dynamic simulation module; the thermal simulation module is used for simulating the temperature field distribution of the camera system in the working environment and calculating the structural deformation of the camera assembly caused by the environmental change; the structure simulation module is used for simulating the structural deformation caused by the change of the rail gravity of the camera system; the dynamic simulation module is used for calculating the structural deformation of the camera at each moment under the working states of system structural vibration and posture correction motion; and the optical simulation module simulates the processing surface shape and the final image quality calculation of each component of the optical system according to the results obtained by the thermal simulation module, the structural simulation module and the dynamic simulation module. The invention further improves the analysis accuracy, shortens the system development period and effectively reduces the manufacturing cost.
Description
Technical Field
The invention relates to the technical field of photoelectric imaging, in particular to a full-link dynamic image quality numerical simulation system and method for an optical system of an aerospace camera.
Background
Space cameras have been widely used in the fields of astronomical observation, weather forecasting, military reconnaissance, and the like. With the continuous upgrading of the use requirements, the requirements of customers on the imaging view field and the resolution capability of the space camera are continuously improved, and a research party is also required to shorten the development period as much as possible while ensuring the quality of equipment. The aerospace camera full-link numerical simulation method is used for calculating the imaging quality of the camera based on an on-orbit imaging physical mechanism and can be used for analyzing the influence of each imaging link on the imaging quality. Firstly, integrating modules at each end in a link; then, calculating the image quality of the full-link optical system by adopting a simulation method; and analyzing the influence of various factors such as the electric heat of the optical machine and the like on the imaging quality of the camera according to the calculation result. Compared with experimental preparation test analysis, accurate simulation can effectively shorten the development period of the on-orbit camera and greatly reduce the manufacturing cost. Generally, the on-orbit camera is affected by module vibration and a self-adjusting mechanism, and works in a micro-vibration environment state, so that the imaging quality of the on-orbit camera needs to be evaluated by calculating dynamic image quality.
Disclosure of Invention
The invention provides a full-link dynamic image quality numerical simulation system and a full-link dynamic image quality numerical simulation method for an optical system of an aerospace camera, aiming at solving the problem that the restriction factors of the image quality of the existing in-orbit camera are complex and difficult to evaluate singly.
The full-link dynamic image quality numerical simulation system of the optical system of the space camera comprises an optical simulation module, a structure simulation module, a thermal simulation module and a dynamic simulation module;
the thermal simulation module is used for simulating the temperature field distribution of the camera system in the working environment and calculating the structural deformation of the camera assembly caused by the environmental change;
the structure simulation module is used for simulating the structural deformation caused by the change of the rail gravity of the camera system;
the dynamic simulation module is used for calculating the structural deformation of the camera at each moment under the working states of system structural vibration and posture correction motion;
and the optical simulation module simulates the processing surface shape and the final image quality calculation of each component of the optical system according to the results obtained by the thermal simulation module, the structural simulation module and the dynamic simulation module.
The full-link dynamic image quality numerical simulation method of the optical system of the space camera is realized by the following steps:
designing an initial system structure of a camera according to user index requirements, and optimizing optical parameters by adopting an optical simulation module to complete initial optical design;
dividing each error model in the working state of the space camera into a static error and a dynamic error; the static errors comprise initial design errors, mirror surface processing and manufacturing surface shape errors, on-orbit gravity environment change errors, installation and adjustment errors and thermal environment change errors; loading the thermal environment change error as a static error to a simulation system;
establishing interfaces among the optical simulation module, the structural simulation module and the thermal simulation module to realize data interconnection; loading structural deformation caused by thermal environment change and gravity environment change into an optical simulation module, setting the processing surface shape of each component, and calculating to obtain the diffusion function value of each field static point of the simulation system;
adding the dynamic error into the simulation system, namely loading the surface shape and the structural deformation of each component into a dynamic simulation module along with the time change relationship, and calculating to obtain the diffusion function value of each field dynamic point of the simulation system;
fifthly, adjusting design parameters of all modules of the full link system, analyzing the influence of the design parameters on the imaging quality of the on-orbit camera, and judging key parameters influencing the image quality;
step six, if the image quality simulation analysis result meets the user index requirement, considering the design parameters to be reasonable; if the analysis result exceeds the user index requirement, adjusting key parameters influencing the image quality and optimizing the system to enable the imaging quality of the system to meet the user requirement; and finally obtaining an output image simulation calculation result of the in-orbit space camera.
The invention has the beneficial effects that: the method for simulating the full-link dynamic image quality value of the aerospace camera optical system based on the on-orbit imaging physical mechanism provides theoretical support for analyzing the imaging index of the system, analyzes key factors influencing and inhibiting the imaging quality of the on-orbit camera according to a calculation result, and optimizes the design parameters of corresponding modules to further improve the dynamic imaging quality; meanwhile, theoretical support is provided for system optimization and upgrade, and compared with single component improvement, the analysis mode for optimizing the system structure is more efficient and reliable.
The invention adopts a full-link dynamic image quality simulation analysis method to realize the comprehensive evaluation of the image quality of the system after the integration of multiple factors such as optical-mechanical-electrical heating and the like, is convenient to analyze and search key design parameters influencing the image quality, and avoids the difficulty that the image quality restriction factors of an on-orbit camera are complex and difficult to evaluate singly.
Secondly, the method of the invention can optimize and improve the system structure according to the full link dynamic image quality simulation analysis result. The design parameters are improved and the system module is replaced on the premise of ensuring the imaging quality of the system, so that different application requirements of a client on the on-orbit camera are met. On the premise of ensuring the imaging quality of the system, the system structure is optimized, and the improvement and the upgrade of the on-orbit camera are realized.
Compared with the traditional full-physical hardware simulation method, the method provided by the invention has the advantages that the system image quality is analyzed by means of simulation software, the analysis accuracy is further improved, the system development period is shortened, the manufacturing cost is effectively reduced, and the camera imaging level is improved.
Drawings
FIG. 1 is a schematic block diagram of a full-link dynamic image quality numerical simulation system of an optical system of an aerospace camera according to the invention;
FIG. 2 is a flow chart of a full-link dynamic image quality value simulation method of an optical system of an aerospace camera according to the invention;
FIG. 3 is an initial design result of a full-link dynamic image quality numerical simulation system of an optical system of an aerospace camera according to the invention;
FIG. 4 is a diagram of the effect of gravity environment change surface shape error in the full-link dynamic image quality numerical simulation system of the optical system of the space camera according to the present invention;
FIG. 5 is a diagram of the effect of thermal environment change surface shape errors in the full-link dynamic image quality numerical simulation system of the optical system of the space camera according to the present invention;
FIG. 6 is a processing surface shape error effect diagram in the full-link dynamic image quality numerical simulation system of the optical system of the space camera according to the present invention;
FIG. 7 is a perspective view of a normalized intensity distribution of a static point spread function;
FIG. 8 is a top view of a static point spread function normalized intensity distribution;
FIG. 9 is a perspective view of a dynamic point spread function normalized intensity distribution;
FIG. 10 is a top view of a dynamic point spread function normalized intensity distribution;
FIG. 11 is a simulation input diagram of the full-link dynamic image quality numerical simulation system of the optical system of the space camera according to the present invention;
FIG. 12 is a simulation output diagram of the full-link dynamic image quality numerical simulation system of the optical system of the aerospace camera according to the invention;
FIG. 13 is an output diagram of the full-link dynamic image quality numerical simulation system of the optical system of the space camera for reducing the error of the processing surface shape according to the present invention;
FIG. 14 is a diagram of the output of the full-link dynamic image quality numerical simulation system of the optical system of the space camera for reducing the vibration error of the system structure.
Detailed Description
In a first specific embodiment, the present embodiment is described with reference to fig. 1, in which a full-link dynamic image quality value simulation system of an optical system of an aerospace camera includes four parts, namely a thermal simulation module, a structural simulation module, a dynamic simulation module, and an optical simulation module; the thermal simulation module is used for simulating the temperature field distribution of the camera system in the working environment and calculating the structural deformation of the camera assembly caused by the environmental change; the structure simulation module is used for simulating the structural deformation caused by the change of the rail gravity of the camera system; the dynamic simulation module is used for calculating the structural deformation of the camera at each moment under the working states of system structural vibration and posture correction motion;
and substituting the calculation results of the thermal simulation module, the structural simulation module and the dynamic simulation module into the optical simulation module to solve the system dynamic image quality.
In a second embodiment, the present embodiment is described with reference to fig. 2 to 14, and the present embodiment is a simulation method of a full-link dynamic image quality numerical simulation system of an optical system of an aerospace camera according to the first embodiment, and the method is implemented by the following steps:
(1) and designing an initial system structure of the camera according to the user index requirements, and optimizing optical parameters in an optical system module to complete initial optical design. Taking an off-axis three-mirror system as an example, as shown in fig. 3, far parallel light rays pass through a primary mirror, a secondary mirror and a tertiary mirror and then are imaged on a detection image surface;
(2) and dividing each error model in the working state of the on-orbit camera into a static error and a dynamic error. Taking the primary mirror as an example, the static errors mainly include five items, namely an initial design error, a mirror surface processing and manufacturing surface shape error, an on-orbit gravity environment change error, a setup error and a thermal environment change error, as shown in fig. 4-6; due to the fact that the distribution of the temperature field of the orbit camera is stable in a short period, the thermal environment change error is loaded to the simulation system as a static error.
(3) And establishing interfaces among the optical simulation module, the structural simulation module and the thermal simulation module to realize data interconnection. Adding the static error into the simulation system, namely loading the structural deformation caused by the change of the thermal and gravitational environments into the optical simulation module, setting the processing surface shape of each component, and calculating to obtain the diffusion function value of each field static point of the simulation system, as shown in FIGS. 7-8;
(4) adding the dynamic error model into the simulation system, namely loading the time-varying relation between the surface shape and the structural deformation of each component of the system into a dynamic simulation module, and calculating to obtain the diffusion function value of each dynamic point of each field of view of the system, as shown in FIGS. 9-10;
(5) and adjusting various design parameters of the sub-modules of the full link system, analyzing the influence of the parameters on the imaging quality of the on-orbit camera, and judging key parameters influencing the image quality.
(6) Performing convolution operation on the input end image shown in fig. 11 and the dynamic point spread function of the optical system obtained through simulation calculation to finally obtain a simulation output image of the optical system, as shown in fig. 12; and optimizing the processing surface shape error and the system structure vibration error, and improving the image quality of the optical system of the on-orbit camera, as shown in fig. 13-14.
In a third specific embodiment, the present embodiment is an example of the method for simulating a full-link dynamic image quality value of an optical system of an aerospace camera according to the second specific embodiment: the method comprises the following specific steps:
step one, completing initial optical design;
according to the requirements of users on the use functions of the camera, the initial structure design of the system is completed, and parameter indexes such as optics, mechanics, electricity and the like are distributed; and then optimizing the initial optical system of the camera to enable various initial design parameters of the system to meet the index requirements. In the embodiment, an off-axis three-mirror system is taken as an example for explanation, and parallel light at infinity is imaged on a detection focal plane after passing through a primary mirror, a secondary mirror and a three-mirror of the system.
Step two, establishing an error model;
and analyzing and establishing various error models generated by the camera in the actual processing and manufacturing and using processes, and simulating the deviation of the actual parameters and the initial design values. According to the change condition of each error, the model is divided into static and dynamic states. The static errors mainly comprise initial design errors, mirror surface processing and manufacturing surface shape errors, on-orbit gravity environment change errors, installation and adjustment errors and thermal environment change errors; the dynamic errors mainly comprise system structure vibration errors and attitude correction motion errors. Each static error can be divided into a misalignment error and a surface error. The misalignment error represents the deviation between the actual position and the ideal position of each component caused by factors such as thermal environment change, gravity environment change, installation and adjustment; the surface shape error represents the deviation between the actual surface shape and the ideal surface shape of each reflector caused by thermal environment change, gravity environment change and actual processing factors of the component. The misalignment error is obtained by finite element simulation, and specific parameters comprise system component size, density, elastic modulus, thermal conductivity, working environment temperature and the like. The surface shape error caused by the thermal environment change and the gravity environment change can be obtained by finite element simulation, and the processing surface shape error is obtained by Matlab simulation. The specific calculation process is as follows:
the optical surface quality is generally analyzed by adopting a power spectral density function, and the frequency band distribution error of the optical surface is simulated by adopting a Gaussian distribution calculation method in the embodiment. The surface correlation function is related to the power spectral density fourier transform as follows:
wherein C (x, y) is a surface correlation function; PSD (K)x，Ky) Is a function of power spectral density. Taking the intermediate frequency error as an example, the PSD function is:
wherein lx、lyσ is the root mean square value for the correlation length in the x and y directions. The surface correlation function is solved to obtain the surface correlation function,
then, a machined surface shape containing the mid-frequency error is constructed. Firstly, constructing a Gaussian distribution random number matrix T (x, y) through a Matlab program; secondly, constructing a two-dimensional digital filter function F (x, y), convolving the filter function with a Gaussian distribution numerical matrix to obtain intermediate frequency error distribution meeting statistical characteristics,
wherein the filter function F (x, y) and the surface correlation function C (x, y) satisfy a Fourier transform relationship,
{F[F(x,y)]}2＝F[C(x,y)]
it is assumed here that the correlation lengths in the x and y directions are both lcAnd the function of the intermediate frequency filter is solved,
selecting sigma and l according to requirementscSimulated mid-frequency error profile.
Loading static errors; and adding the static error model into the system, and calculating and acquiring the diffusion function value of each field static point of the system.
Step four, loading dynamic errors; and adding the dynamic error model into the system, and calculating and acquiring a dynamic point diffusion function value of each field of view of the system at a single moment, namely acquiring a quasi-dynamic point diffusion function value of each field of view of the system.
The system structure vibration error and attitude correction motion error model is obtained by adopting finite element analysis calculation, and is obtained by calculating the position parameters of the on-orbit camera structure assembly at each moment and then performing dynamic accumulation.
Step five, linearly superposing diffusion function values of the quasi-dynamic points;
the on-orbit camera needs to complete the imaging function of an infinite point object, and the light intensity distribution function of the object can be regarded as linear superposition of a series of delta functions, and each delta function represents the light intensity distribution of one point object. If the output function of the delta functions generated by the system on the image plane is defined as a point spread function, namely, the light intensity distribution function of the image spot generated by the point object, the light intensity distribution function of the object image is the linear superposition of the point spread functions. Therefore, the full-field point spread function, i.e. the dynamic point spread function, in a period of time can be obtained by superposing the quasi-dynamic point spread functions at different times.
Analyzing key parameters influencing the image quality;
after a complete analysis model is established, the change condition of the dynamic image quality of the camera is analyzed by adjusting parameters of each model, and key factors influencing the image quality are searched. If the final simulation result of the dynamic image quality exceeds the user index requirement, the key system design parameters influencing the image quality are adjusted and the system is optimized, so that the imaging quality of the system meets the requirement.
Seventhly, acquiring an on-orbit aerospace output image simulation calculation result;
and convolving the obtained dynamic point spread function with the input image to obtain a final simulation output image. The known calculation formula:
I(x,y)＝I0(x,y)*hI(x,y)
wherein, I (x, y) and I0(x, y) represent the light intensity distributions of the image point and the object point, respectively; h isI(x, y) represents a dynamic point spread function.
Analyzing main factors influencing the image quality according to the calculation result; according to the calculation result, the main factors influencing the image quality in the example are two terms of the processing surface shape error and the system structure vibration error. Two errors are optimized respectively, and the image quality of the on-orbit camera is improved.
Claims (3)
1. The full-link dynamic image quality numerical simulation system of the optical system of the space camera comprises an optical simulation module, a structure simulation module, a thermal simulation module and a dynamic simulation module; the method is characterized in that:
the thermal simulation module is used for simulating the temperature field distribution of the camera system in the working environment and calculating the structural deformation of the camera assembly caused by the environmental change;
the structure simulation module is used for simulating the structural deformation caused by the change of the rail gravity of the camera system;
the dynamic simulation module is used for calculating the structural deformation of the camera at each moment under the working states of system structural vibration and posture correction motion;
and the optical simulation module simulates the processing surface shape and the final image quality calculation of each component of the optical system according to the results obtained by the thermal simulation module, the structural simulation module and the dynamic simulation module.
2. The simulation method of the full-link dynamic image quality numerical simulation analysis system of the aerospace camera optical system according to claim 1, wherein the simulation method comprises the following steps: the method is realized by the following steps:
designing an initial system structure of a camera according to user index requirements, and optimizing optical parameters by adopting an optical simulation module to complete initial optical design;
dividing each error model in the working state of the space camera into a static error and a dynamic error; the static errors comprise initial design errors, mirror surface processing and manufacturing surface shape errors, on-orbit gravity environment change errors, installation and adjustment errors and thermal environment change errors; loading the thermal environment change error as a static error to a simulation system;
establishing interfaces among the optical simulation module, the structural simulation module and the thermal simulation module to realize data interconnection; loading structural deformation caused by thermal environment change and gravity environment change into an optical simulation module, setting the processing surface shape of each component, and calculating to obtain the diffusion function value of each field static point of the simulation system;
adding the dynamic error into the simulation system, namely loading the surface shape and the structural deformation of each component into a dynamic simulation module along with the time change relationship, and calculating to obtain the diffusion function value of each field dynamic point of the simulation system;
fifthly, adjusting design parameters of all modules of the full link system, analyzing the influence of the design parameters on the imaging quality of the on-orbit camera, and judging key parameters influencing the image quality;
step six, if the image quality simulation analysis result meets the user index requirement, considering the design parameters to be reasonable; if the analysis result exceeds the user index requirement, adjusting key parameters influencing the image quality and optimizing the system to enable the imaging quality of the system to meet the user requirement; and finally obtaining an output image simulation calculation result of the in-orbit space camera.
3. The method for full-link dynamic image quality numerical simulation analysis of the aerospace camera optical system according to claim 2, wherein the key parameters affecting image quality include processing surface shape errors and system structure vibration errors.
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