Solar radiation will be scattered by atmospheric molecules and aerosol particles when it transfers through the Earth atmosphere. The scattered radiance with different polarization state can be used to characterize atmospheric components. Based on the BHU-ATM presented in our previous work, an atmospheric radiative transfer model considering the polarization effects is developed in this paper, in which the parameter discretization method is used. To this end, the radiative transfer equation is adapted into the Stokes vector form, while the impacts of atmospheric molecules and aerosols on the polarization state of the scattered radiance are represented by means of the scattering phase matrix. The Curtis-Godson approximation and the two-stream approximation are used to obtain the analytical solution of the adapted radiative transfer equation. As the precise calculation of the scattering phase matrix varying with the scattering angle and the radiant wavelength is inefficient for the calculation of spectral path radiance, a novel aspect of this work is the efficient computation of the scattering phase matrix through a two-dimensional interpolation method, significantly reducing computational complexity while maintaining accuracy across a broad range of angles and wavelengths. The simulation results of the atmospheric transmittance, the spectral radiance and the degree of polarization (DOP) for an arbitrarily selected transfer path are given. As it can be seen, in the spectrum from the visible through the near infrared (VNIR), the polarization modeling showed a maximum transmittance difference of 0.0007 and a spectral radiance difference of 0.3W/m2/μm/sr. The DOP varied significantly, with a difference of up to 0.12 between urban and ocean aerosols. The developed polarization model can improve aerosol component identification in satellite-based remote sensing applications, aiding in more accurate air quality monitoring and enhancing climate models that account for aerosol scattering effects.
Improving the centroid and grayscale extraction accuracy of point targets is of great significance to the long distance detection system. There is a drop in centroid accuracy due to pixel sampling. For point targets, due to the small number of target pixels, the positioning accuracy is generally sub-pixel, and the use of optical dispersion to increase the number of target point pixels will reduce the signal-to-noise ratio of the point target, thereby reducing the detection distance of the system. In addition, there is a gap between the pixels of the infrared detector, and the grayscale response of the detector cannot reflect the real radiation intensity of the target. This paper simulates the point spread function based on the Gaussian function .The four parameters(the center coordinate, the width and the peak value) of the Gaussian function are estimated by a proposed optimization algorithm based on the obtained grayscale information of the point target. The results show that the grayscale extraction error is reduced from 35% of the grayscale summation algorithm to less than 10%, and the centroid error is also improved compared with the traditional centroid calculation algorithm.
KEYWORDS: Solar radiation, Solar radiation models, Heat flux, Sun, Spherical lenses, Reflection, Radiation effects, Data modeling, Optical simulations, Black bodies
The target will be affected by the solar radiation, the earth radiation and the earth's reflected solar radiation during the flight. Due to the closeness of the earth to the target, the spatial position of the target has a great influence on the received radiative heat flux. At present, in many studies on the radiation characteristics of the target, researchers regard the earth as a black body with uniform temperature for equivalent replacement, which will cause certain errors in the calculation results. Therefore, based on the radiation transfer theory and spherical model, this paper analyzes the spatial position relationship between the target and the earth and the sun under different attitudes, calculates the angular coefficient relationship between solar radiation, earth radiation and the earth's reflected solar radiation, and build a simulation model of heat flux received by space target. The simulation results show that for the shadow environment, the target is only affected by the radiation of the earth. The model constructed in this paper can achieve refined modeling of the earth with higher accuracy than traditional methods. For environments with solar radiation, although the introduction of the sun compresses the effect of Earth's radiation, the effect of Earth's albedo needs to be considered in Earth modeling because the target receives a large amount of Earth-reflected solar radiation.
The range analysis of the infrared detection system is the first task in the design of the detection system. The traditional range model based on the signal-to-noise ratio is only suitable for a uniform background. For complex backgrounds, the fluctuation of background clutter is the main factor restricting the detection distance, and the results based on the signal-to-noise ratio model may deviate greatly from the actual situation. Based on the characteristics of the re-entry process, this paper analyzes the dynamic process, and establishes an infrared detection distance analysis model based on the signal-to-clutter ratio. The radiation flux between the background and the target is calculated, and the infrared detection band selection is simulated. On this basis, the analysis and calculation of the infrared detection distance under different cloud conditions are carried out, and the similarities and differences between the signal-to-noise ratio model and the signal-to-clutter ratio model are compared, which can provide references for the design of infrared detection systems in practical applications.
To achieve an accurate evaluation of the effect of laser interference, this paper studies on the image simulation model of laser interference infrared detectors. According to different interference densities, the characteristics of the laser interference detector spots are investigated. First, based on the laser interference transmission link, a simulation model of the gray response of the detector image and the laser interference power is established. Then, a set of NEFD measurement methods for infrared detector response models are established based on the response characteristics of the detector. Finally, according to the different NEFD values at the entrance pupil optical system, theoretically simulation is carried on the relationship between the laser interference effect and the power density irradiated to the entrance pupil surface of the optical system. The results show that when the irradiance density at the entrance of the pupil optical system exceeds 1*106 of the NEFD value, the point target can be effectively interfered. Further, when the irradiance density at the entrance of the pupil optical system exceeds 1*107 of the NEFD value, the area target can be effectively interfered. The proposed model is verified by the ground test as the ground test results have the same trend and magnitude as the simulation results.
The solar stray light will seriously affect the imaging quality of the infrared detection system. The traditional point source transmittance (PSF) index is difficult to evaluate the image degradation of the detection system due to stray light. In this paper, a stray light simulation is performed firstly for a given infrared detection system, and the irradiance distribution of solar stray light on the surface of the detector with different incident angles are obtained. Then a simulation model of the detection system is established based on the physical conversion process of the infrared detection system. By combining this simulation model with the light distribution, the spatial noise of the detection system with solar stray light can be calculated quantitatively, and the image degradation due to solar stray light can be quantitatively evaluated.
Rocket engine is a complex and accident-frequently-occurring system. Its fault location and cause analysis is challenge. This paper analyze a rocket launching fault based on the video captured by a visible light camera on the rocket during the flight. The primary mission is to judge whether the suspected "flame" is caused by the combustion luminescence or the reflection of sunlight by the fluids. A qualitative and semi-quantitative analysis is carried out from the perspective of intensity and color. The possibility of self-luminescence is analyzed, and the spectrum from visible to near infrared of hydrogen and oxygen combustion is measured on the ground. The atomic radiation spectra of Na, Ka and other related metal elements are detected. The combustion brightness and atmospheric scattering brightness are compared. Combining with other prior information of the engine, it is considered that the brightness of the re-burning of hydrogen and oxygen should be lower than the atmospheric scattering brightness. The real color of the suspected "flame" area in the image is analyzed by using the characteristics of the white balance processing algorithm. By comparing with other similar gray scale and similar color images, it is inferred that the real color is white, and the yellowish of the “flame” is caused by compensation of the blue background by the automatic white balance of the camera. Based on the above analysis, it is inferred that the "flame" is caused by the reflection of sunlight by liquid particles, not by combustion, and the region should be located at the bottom of the rocket.
In view of the lack of precision and small dynamic range in one or two-point temperature nonuniformity correction method which is applied in the Space Infrared Image, this paper will introduce the technique of discrete wavelet transform which is applied to the non-uniformity correction. In addition, it is used the real-time infrared image processing method of removing blind pixels, invalid pixels and additive noise with using ground calibration parameters and deep space images. It is designed the infrared image processing method applied to the flight that the multiplicative noise in infrared image is turned into additive noise using the logarithm aimed at the characteristic of noise distribution.
The mechanism of the image degradation due to the opaque metallic wire grid is analyzed and a degradation mode is built based on the theory of Fourier optics. The effect of different opaque wire grid on the image quality is simulated. We define the manner of using wire grid that will meet system requirements for both optical and shielding efficiency. A gray non-uniformity correction model based on two-point correction method is built, and the way to estimate the degradation function and the restoration process are proposed. Both the experimental results and simulation show that the non-uniformity of the image after correction is less than 1/10 of that of before correction and the relative error between the original image and restored image is 0.56%.
Blackbody is a crucial device for performance test and radiometric calibration of infrared system. This paper put forward a low-temperature surface blackbody with variable temperature. It works under vacuum and low temperature environment, and can realize the variable temperature control within the range from 130K to 450K by the dual control of liquid nitrogen and electric heating. This paper gave a detailed introduction to the system composition and structure of surface blackbody, introduced the design processes of radiator, temperature controller, temperature control system and other important parts, and analyzed the temperature field distribution of blackbody radiator through finite element software. And test method was used to test performance of the surface blackbody. The results show that the blackbody has good temperature uniformity and temperature stability performance, and is able to provide a benchmark for low temperature test of infrared system.
There is a clear need for miniaturized, lightweight, accurate and inexpensive star tracker for spacecraft with large anglar rate. To face these new constraints, the Beijing Institute of Space Long March Vehicle has designed, built and flown a low cost miniaturized star tracker that provides autonomous (“Lost in Space”) inertial attitude determination, 2 Hz 3-axis star tracking, and digital imaging with embedded compression. Detector with high sensitivity is adopted to meet the dynamic and miniature requirement. A Sun and Moon avoiding method based on the calculation of Sun and Moon’s vector by astronomical theory is proposed. The produced prototype weight 0.84kg, and can be used for a spacecraft with 6°/s anglar rate. The average angle measure error is less than 43 arc second. The ground verification and application of the star tracker during the pick-up flight test showed that the capability of the product meet the requirement.
KEYWORDS: Holography, Data storage, Signal to noise ratio, 3D image reconstruction, Multiplexing, Spatial light modulators, Modulation, Holograms, Volume holography, Sensors
An optical model to describe the reconstructed image of the collinear holographic data storage system is presented. The 2-D shape of the recording spot in the medium is simulated. The system structure parameters that influence the signal-to-noise ratio (SNR) of the reconstructed image are investigated in order to choose proper optical components to improve data storage density of the system. The role of the random binary phase mask (RBPM) utilized in the multilayer collinear holographic system is investigated. It is proved that the inter-layer crosstalk can be effectively suppressed by using different RBPMs. Different layers of data pages can be recorded with the SNR increased by a factor of six at least and the shift selectivity along z-axis can also be improved significantly.
KEYWORDS: 3D image reconstruction, Image restoration, Data modeling, Image quality, Holographic data storage systems, Optics manufacturing, Holography, Optical testing, Current controlled current source, Data storage
An image reconstruction model for the collinear holographic data storage (CHDS) system is proposed and analyzed. The analytical solution for the reconstructed image by the CHDS system is derived based on the first Born approximation and scalar diffraction theory. This expression shows the CHDS system is not a linear space-invariant system. A page-oriented simulation method is desired for a rigorous analysis. By applying the fast Fourier transform method, a page-oriented simulation method for the CHDS system is presented. The influence of the reference pattern and the media thickness on the quality of the image reconstructed from the holograph is investigated. The fill factor of the reference pattern is the key parameter for the quality of the reconstructed image.
A transmission type of collinear holographic data storage system (CHDS) based on photorefractive LiNbO3 crystal is constructed. The polarization states of the coherent beams in the crystal are optimized for a larger dynamic range based on the coupled mode theory and the linearized band transport model of photorefractive effect. The optimization predicts that the photorefractive crystal will have a larger dynamic range by use of extraordinary light than using ordinary light for CHDS system when the grating wave vector is parallel to the c-axis of the crystal. It also predicts that the dynamic range for CHDS can be larger than that for traditional 90 degree holographic recording geometry. In the experimental results, data pages are recorded with the shifting multiplexing method in the LiNbO3 crystal by using the extraordinary light.
KEYWORDS: Holography, Diffraction, Sensors, Point spread functions, Holograms, Spatial light modulators, Optical simulations, Data storage, Modulation, Holographic data storage systems
The wavelength and defocus margins for collinear holographic data storage system are theoretically analyzed based on
the first Born approximation and the scalar diffraction theory. Explicit expressions for the decay of diffracted signal in
the center of the detector plane with the shift of the reading wavelength and with the defocus of the disc are presented.
The expressions predict that the defocus margin is independent of the media thickness while a thicker disc leads to a
narrower wavelength margin. Simulation results show that the wavelength margin of collinear holographic scheme is
larger than that of the conventional 2-axis holographic scheme. The influences of the properties of reference pattern on
both margins are also discussed.
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