Currently, most space-borne optical cameras have fixed focal length and depth of focus. In this case, the range within which the target can be clearly imaged has been pre-determined before launch. However, the distance of the target to the optical camera might be unknown or change very fast and therefore focus adjustment has to be carried out to obtain clear images. However, no matter which refocusing technique is used, focus adjustment might lag behind the object distance variation and depth of focus extension is a better way. Wave-front coding can be used to extend the depth of focus of incoherent imaging system but the surface profile of the phase mask could not be changed dynamically, which is not flexible for application. In this manuscript, by combing the variable curvature mirror (VCM) and coded imaging technique together, a new depth of focus extension technique is proposed. According to our previous studies, the focal plane could be quickly adjusted by changing the curvature radius of VCM. Compared with the curvature variation speed, the exposure time of the camera is quite long. Therefore, by adjusting the focal plane very fast in a wide range during the exposure through VCM, an equivalent coded optical transfer function having no null frequency points within bandwidth is generated and the image captured is uniformly blurred. After that, with the help of digital restoration, the clear image could be obtained. Because the focal plane could be adjusted through variable curvature mirror in the range of millimeter, the proposed method could be used to obtain clear images with greatly extended depth of focus.
The detecting CCD of a space astronomical telescope needs to be cooled to -75℃ to suppress the dark current for faint target detecting in the universe, and coplanarly spliced with two fine guidance sensor(FGS) which needs to be cooled to -40°C for the stability as long time observation. Two one stage thermos-electric cooler(TEC) was connected to actively cool the detector to ensure the working temperature and the temperature control accuracy, the Structural of the actively cooling detector assembly and the focal plane component were presented and the power dissipation of the TEC was calculated. In order to ensure the coplanarity of the focal plane component on the working temperature, the finite element method was used to analyze the thermal distribution on the detector surface and the thermal deformation of the supporting structure of the FGS with different materials. The analysis results showed that the lowest cooling temperature of the detecting CCD is -75°C, the temperature control accuracy was better than 1°C, and the coplanar error of the detection CCD and the fine guidance sensors did not exceed 20μm. The thermal equilibrium test showed that the lowest cooling temperature was -74.9°C~-75.1°C for the detecting CCD, The temperature control accuracy was 0.1°C. The thermal optical test showed that the defocus of the FGS was 4μm after focusing, which verified the thermal and structural design performance of the focal plane component.
A Φ1400mm silicon carbide (SiC) mirror assembly was designed according to the requirement of the mass and the optical surface distortion. The parameters of the light-weighted open-back primary mirror were optimized by finite element analysis. Six flexure bipods were designed to support the mirror edge in 12 points evenly. 12 floating anti-gravity supports were used to Minimize the optical surface distortion caused by gravity effect to obtain the real optical surface during polishing. The mirror was precisely assembled with the bipods supports and the Carbon fiber reinforcement plastic (CFRP) chamber. The optical test with interferometer showed that the surface distortion was less than 0.03λ (λ=632nm) RMS with ±5°C temperature variation and 1g gravity condition, and the mass was 145kg, which coincided with the FEA results.
Many factors could lead to deviation of focal plane of a space-borne camera from its ideal position and thus on-orbit focusing are indispensable to capture satisfactory images of space targets. Among all typical focusing techniques, changing the position of focal plane directly through motor-driven worm and gear is the simplest one, but two drawbacks are obvious. First, mechanical movement is slow but the space targets usually move very fast. In this case, it is highly probable that focus adjusting is always lagging. Second, the targets especially the non-cooperative ones may appear anywhere and working distance of defocus compensation should be large enough which makes the focusing assembly much heavier. Factually, most large aperture space-borne cameras are all-reflective or all-reflective having lens correctors, therefore by changing the interval between the primary and secondary mirror or by changing intervals within lens correctors defocus could be compensated. Although the sensitiveness is improved, moving elements are still needed indicating underlying lagging. Therefore in this manuscript, a new focus adjusting method is proposed. By changing the secondary mirror into a variable curvature mirror (VCM), the defocus compensation could be realized by varying the curvature radius of VCM. One prototype space-borne optical camera whose focal length is 6000mm and aperture is 600mm is used to verify the method. Our research demonstrates that the VCM based focus adjusting is not only very sensitive but also suitable for very severe defocus. Specifically, only a slight saggitus variation of less than 4um could compensate amazing defocus of about 4mm while maintaining good linearity between the saggitus variation of VCM and defocus, which proves the potential of this focus adjusting method.
Nowadays, large aperture space-borne optical camera is one important payload used to capture optical images of space targets based on satellite platform, but many factors could prevent space-borne camera from obtaining satisfactory images. Firstly, vibration during launch, moisture absorption, deflation and violent temperature variation and so on could make the focal plane of space-borne camera deviate from its ideal position. Secondly, space targets are usually distant, moving quite fast and especially noncooperative targets may even appear in unknown distances. In this case, frequent, rapid and precise on-orbit focusing mechanism are indispensable to traditional imaging system, but wave-front coded imaging provides another choice. In wave-front coded imaging system, by introducing a suitably designed phase mask, the optical transfer function will become insensitive to defocus and the clear images similar to diffraction limited ones could be obtained through digital restoration. Therefore in this manuscript, the experimental research is carried out to investigate the effectiveness of wave-front coding technique in realizing high-resolution imaging without introducing any focusing mechanisms. By only adding a cubic phase mask to the exit pupil with diameter of approximately 80mm and keeping other optical-mechanical structures of a prototype large aperture camera with focal length of 6000mm and aperture of 600mm unchanged, the extension of depth of focus could be obtained. In the collimator based testing, the depth of focus of that prototype space-borne camera could be extended 8.5x approximately, which provides another way to realize high-resolution imaging of space targets while designing space-borne optical camera in future.
The Space-based multi-band astronomical Variable Objects Monitor (SVOM) project is a dedicated satellite developed at the cooperation of China and France, aim to make prompt multi-band observations of Gamma-Ray Bursts (GRBs), the afterglows and other high-energy transient astronomical events. The Visible Telescope (VT) is one of the four payloads onboard the SVOM. VT is designed to observe the afterglows of GRBs both in the visible and near infrared bands simultaneously. The telescope can reach a limiting magnitude of +22.5Mv and provide the redshift indicators for high-Z (z<4) GRBs. VT is also designed to measure the Relative Performance Errors (RPEs) for the satellite attitude and orbit control system (AOCS), aiming to improve the pointing stability of the platform during observation. VT adopts a Ritchey-Chrétien (RC) catadioptric optical configuration with a 440mm aperture and uses the dichroic prism before the focal plane to split the incident light into blue (visible) and red (near infrared) band. Two Fine Guidance Sensor (FGS) CCDs are mounted beside the main CCD on the blue band focal plane of VT and provide sub-arcsecond pixel resolution. Fiber reinforced plastic (CFRP) composites is selected as the material of VT’s main structure to ensure enough stiffness and strength during launch. The electrical video processing circuit is carefully designed to make the readout noise below 6e-/pix (rms) in 100s exposure time. Active and passive thermal control are used together to ensure the optical performance and thermoelectric cooler (TEC) is adopted to control the main CCDs working temperature below -65°C to reduce the noise. This paper provides a comprehensive overview of the scientific requirements and the key instrument design aspects of optics, main structure, electrics, thermal control, performance test and validation results of VT.
The surface contribution analysis method is to find the wavefront map at the local intermediate entrance and exit pupil reference spheres for each optical surface. Direct pictures of each surface aberration contribution are then given by fitting the wavefront errors with Fringe Zernike polynomials which can help optical designers to find the origins of the main aberrations at the final focal plane and make them choose the effective variables for optimization consciously, which is very helpful for designing the freeform optical system with hundrands of variables. This paper discusses the surface contribution analysis method. A Matlab routine is written to communicate with Code V and to give direct pictures of aberration contribution for each surface. A compact freeform optical system is designed to validate the surface contribution analysis design method which is proved to have good convergence and very directive for optical designers.
The status of ocean remote sensing is becoming more and more important. There are all kinds of resources in ocean and many ships on the sea. It is necessary for people to detect or observe these objects to know more about the natural resources and to ensure safety of ships. The paper concentrated on a compact design of a small space camera. An oscillating mirror was designed in the camera for a small volume. After that, structure analysis was done by traditional method and reduced method. The key step of reduced method was to get the reduced model. The analysis result showed that the reduced method could not only cut down the cost of computing, but also give a result with good accuracy. Besides, the analysis result indicated that the small space camera could undergo the strict load cases smoothly. The design in this paper may give some guidance to other designers and engineers when they are going to make a small space camera for ocean remote sensing.
A Φ450mm primary mirror subsystem of a space-based astronomy telescope was designed with mass, optical surface distortion and reflectivity requirement. The open-back primary mirror was made of pressure-less sintering silicon carbide, light-weighted at a ratio of approximately 70%. Three side supporting invar flexure bipods were designed to minimize the assembling stress and the thermal stress. The high reflection was obtained from the optical surface cementite. The mirror weighted 7kg and the reflectivity was 97% after optical polishing. The mirror subsystem was precisely assembled under the strict technical condition. The optical test with interferometer showed that the optical surface distortion is less than 1/40λ rms, which met the critical optical requirements for the primary mirror of the space-based astronomy telescope.
Based on the wavefront aberration theory and the coordinates transform, the free form optical induced aberration’s characteristic of optical system has been analyses in this paper. The optical wavefront error and the free form surface can be express as Fringe Zernike polynomial; the free form optical on the surface (Stop or Entrance pupil or Exit pupil) affects all the field angles equally. If the surface is not the pupil of optical system, the aberration observed is different from the free form itself because the footprint of the beam for an off-axis field point only covers part of the surface. For the Fringe Zernike surface figure on a surface not at pupil, it will transform into lower order Fringe Zernike aberration in the optical system, the relationship between different Fringe Zernike aberration and field is different, and the location zero for the lower aberration always reside at the center of the field of view.
Variable curvature mirror (VCM) is a long-history technique used to correct the defocus and spherical aberrations caused by thermal lens effect in solid-state laser. In recent years, the probability of VCM in realizing non-moving element optical zoom imaging has been paid much attention and how to generate a large enough saggitus variation while still maintaining good enough surface figure accuracy is the research hot topic. In this manuscript, two kinds of VCM has been studied and the advantages of pressurization actuation based VCM having variable mirror thickness has been confirmed. Compared with the traditional annular force actuation based VCM with constant mirror thickness, the pressurization actuation based one having variable mirror thickness is capable of providing a saggitus variation of larger than 35um and still maintaining its surface figure accuracy superior to 1/10λ(λ=632.8nm). Besides that, it is found that spherical aberration plays a main role in leading to the degradation of surface figure accuracy and the surface figure accuracy at extreme curvature could be improved to about 1/40λ(λ=632.8nm) by only removing spherical aberration. Therefore, when applying pressurization actuation based VCM to realize non-moving element optical zooming, the wavefront sensing and subsequent digital correction to eliminate the spherical aberration will become a necessary step.
Through introducing transformed pupil vector and shifted center of aberration fields vector into the nodal aberration expansions of an axially symmetric optical system, the aberration expression in third order of an off-axis optical system and misaligned off-axis optical system are detailed. Nodal aberration characteristics of misaligned off-axis optical system are revealed only by analyzing the pupil decentration vector, aberration fields shifted vector and the aberration coefficients of the axially symmetric optical system. Actually, it is well demonstrated that the 3rd spherical aberration, 3rd coma, 3rd astigmatism in a misalignment off-axis system are comparable to the aberrations in a misalignment axially symmetric system. Otherwise it will not only induced constant 3rd spherical aberration but also constant 3rd coma and 3rd astigmatism over the field of view, when aligned an off-axis optical system elements with error axial spacing.
Computer-generated hologram (CGH) is an effective way to compensate wavefront aberration in null test of aspheric
surfaces and freeform surfaces. Our strategies of CGH design for 600mm diameter SiC primary mirror surface figure
testing are presented, and an experiment demonstrating the compensation test results of CGH is reported. We design a
CGH including two sections on the same substrate in order to align the CGH to the incident wavefront: main section for
compensating wavefront in null test, alignment section for adjusting the relative position between CGH and
interferometer. In order to isolate different orders of diffraction, we used power carrier to make different orders of
diffraction come to focus at different position along the axis to avoid ghost reflections. We measured the 600mm
diameter SiC primary mirror using this CGH, and the surface test result is 0.033λ rms.
Based on optical zooming used to capture images with variable resolution and field of view (FOV), an all-reflective non-coaxial optical zooming system without moving elements is designed for space camera application. In this prototype design, a deformable mirror (DM) whose curvature radius can be changed is introduced. By carefully selecting the optical power of conventional reflective mirrors surrounding the DM, the overall focal length of the imaging system can be greatly changed with slight variation of curvature radius of DM. The focal length of the system can be changed from 48mm to 192mm and the system performance is approaching diffraction-limited with diverse criteria and the maximum stoke of DM is still within its physical limits at the same time. The experimental results prove the effectiveness of DM based optical zooming and will provide a new routine for new type of space camera design in the future.
According to technical requirements of satellite optical communication, a set of optical system of transmitter and receiver with a common optical antenna is designed at 850nm. We select a Cassegrain-type afocal off-axis system as the optical antenna structure. The entrance pupil diameter is 150 mm. The field of view of transmitter and receiver is ±100μrad and ±5mrad, respectively. This optical system has a simple and feasible configuration. The design results show that system performances are acceptable. The MTF is close to the diffraction limit. The energy concentration ratios are more than 90% at 30μm of diameter of circle. The RMS of wave front aberration is less than λ/20.
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