This PDF file contains the front matter associated with SPIE Proceedings Volume 9280, including the Title Page, Copyright information, Table of Contents, Introduction (if any), and Conference Committee listing.

The support structure of large aperture mirror of space remote sensor is the key of the space remote sensor development. In this paper, the size of the large aperture mirror is Φ700mm,which is supported in the back of mirror with 3 points ,the composite structure of ball joint and flexible groove is adopted in support structure which can guarantee the mirror surface satisfy the requirement of optical design under the coupled load of gravity and heat. At the same time, the mirror subassembly should have a high enough stiffness through the reasonable lightweight to ensure the camera in transportation and launch process can withstand severe vibration condition. In order to validate the rationality of the design,the finite element analysis is done to the mirror subassembly,which indicates that the shape error variation of mirror RMS is better than λ/50 and PV is better than λ/10 in the coupling load of gravity and heat,and the first natural frequency of the mirror subassembly is higher than the design requirements. Dynamics calculation results of mirror subassembly consistent with mechanics experiment results；the surface precision of the mirror subassembly obtained from the ZYGO interferometer consistent with the results of finite element analysis and meets the design requirements.

With the uprating requirements of space remote sensing, the aperture of the optical remote sensor is getting larger and larger. The influences of both the support of optical elements and gravity deformation on the optical system are difficult to conquer. Therefore, it is necessary to compensate the descending optical performance which is caused by the surface error of primary mirror by means of adjusting the position parameters of the optical elements on-orbit. A large aperture coaxial three-mirror optical system is introduced in the paper. Matlab and MetroPro are used to simulate the surface error of the primary mirror. The surface error of the primary mirror is compensated by adjusting the position freedoms of the secondary mirror. The results show that the adjustment of the position freedoms of the secondary mirror can compensate both the coma and some astigmatism of the primary mirror, but not the spherical aberration.

Space telescope locking and releasing system is one of the most important part in aerospace. It can provide the part in the spacecraft from being under attack. In this letter, the developing status and primary characteristics of several locking and releasing system in recent years were summarized. The main locking and releasing system can be part with pyrotechnic device and un-pyrotechnic device. The paper introduces the system and the way that the device released by compared the pyrotechnic and the un-pyrotechnic device. In the way of comparing the different device, the letter made the point that each of these device had its advantages that should been developed, and the disadvantages that should been improved. These analyses will provide references for the design of the locking and releasing system in the future of telescope research.

Silicon carbide is being the main ceramics material to make aspherical optical reflectors because of its good physical and chemical performance. But, because of the particularity of wheel structure, wheel wear form and wear loss is changing with time going, which limits the wheel wear researchment. In order to make a better research to wheel grinding, the author experimented many researches on diamond grinding blocks in grinding of SiC in the surface grinding machine, finding the relationship between diamond grinding block wear form and wear loss and grinding force, surface quality and surface precision of workpiece, including the principle of diamond grinding block wear form and wear loss changing with time going, the influencing law of surface quality and surface accuracy because of wheel wear. By changing some grinding parameters in the grinding experiments, the author gets the order of the influencing factors of grinding parameters to wheel wear by orthogonal test.

Thirty Meter Telescope’s Tertiary Mirror Cell Assembly (TMTM3-CA) will be manufactured in Changchun Institute of Optics, Fine Mechanics and Physics (CIOMP). To reduce the risk of fabricating TMTM3, a prototype made of Zerodur with a d/t ratio of 72 is planned to be polished. Here the focus is on the design scheme of the prototype’s optical manufacturing support system. Firstly the number of support points was estimated, then structural design scheme for equal-force polishing support system are drawn, and finally layout optimization of support points was carried out. As its high performance and efficiency, the work will be beneficial to manufacturing large thin mirrors.

The segmentation of the primary mirror is the only promising solution for building the next generation of ground telescopes. However, manufacturing segmented mirrors presents its own challenges. The edge mis-figure impacts directly on the telescope’s scientific output. The ‘Edge effect’ significantly dominates the polishing precision. Therefore, the edge control is regarded as one of the most difficult technical issues in the segment production that needs to be addressed urgently. This paper reports an active edge control technique for the mirror segments fabrication using the Precession's polishing technique. The strategy in this technique requires that the large spot be selected on the bulk area for fast polishing, and the small spot is used for edge figuring. This can be performed by tool lift and optimizing the dell time to compensate for non-uniform material removal at the edge zone. This requires accurate and stable edge tool influence functions. To obtain the full tool influence function at the edge, we have demonstrated in previous work a novel hybrid-measurement method which uses both simultaneous phase interferometry and profilometry. In this paper, the edge effect under ‘Bonnet tool’ polishing is investigated. The pressure distribution is analyzed by means of finite element analysis (FEA). According to the ‘Preston’ equation, the shape of the edge tool influence functions is predicted. With this help, the multiple process parameters at the edge zone are optimized. This is demonstrated on a 200mm crosscorners hexagonal part with a result of PV less than 200nm for entire surface.

The M3M (Mirror 3 Mirror) of TMT (Thirty Meter Telescope) project is a3.5m×2.5m solid flat elliptical mirror. CIOMP is responsible for the fabrication of the M3M. A primary study on the fabrication and metrology is done in the past 2 years, and this paper introduces our work on the project. The fabrication strategy is based on large orbital tools and a plan combining with multiple measure methods is developed based on the requirement of M3M. A concept of dualsupporting system is also studied in the program to reduce the effect of gravity deformation.

Sintered silicon carbide (SSiC) is becoming one of the most important materials for the optical mirrors due to its excellent specific stiffness (E/ρ) and demission stability (λ/α). However, it is difficult to fabricate the monolithic structure SSiC optical mirror with demission of larger than Φ1.5m because of process limitation. Joining of SSiC segments (brazing) provide a good solution to prepare large size mirror optics. However, compared with the uniform properties of the monolithic structure SSiC optical mirror, the brazed mirror is composed of two materials (SSiC segments and brazing material), so the performance of optical grinding and reliability of brazed optical mirrors become the focus. In this paper, the Φ300mm and Φ600mm brazed optical mirrors was used to evaluate the reliability of different conditions. Three kinds of environmental simulation tests, including thermal stability, thermal circle and random vibration were carried out. The evaluation results show that the temperature and vibration has no obvious effects on the surface figure (RMS) of the brazed optical mirrors.

In SGIII lasers there are large number of transport mirrors in target beam enclosures. Surface contaminations could easily introduce optical damage, and increase laser energy loss under high laser influence conditions. It is significant for lasers to control contamination and maintain cleanliness. In SGIII prototype, the target beam enclosures are test to be seriously contaminated after about two years of routine operations. Volume cleanliness in mirror boxes are monitored through 24 hours before, during and after a shot. Ingredients of particle and organics are tested. Reconstructions are performed on the mirror boxes to remove debris and keep cleanliness for upward facing surface of mirrors effectively. In SGIII facility some contaminations are found in beam enclosures and on the mirrors after several months of test running. Contaminations sources are analyzed to further know about the contamination mechanisms. Some engineering countermeasures are introduced for controlling contamination and keeping cleanliness for optics.

A range gated laser imaging system has been designed and developed for high precision three-dimensional imaging. The system uses a Nd:YAG electro-optical Q-switched 532nm laser as transmitter, a double microchannel plate as gated sensor, and all the components are controlled by a trigger control unit with accuracy of subnanosecond. An experimental scheme is also designed to achieve high precision imaging; a sequence of 2D “slice” images are acquired in the experiment, and these images provide the basic data for 3D reconstruction. Basing on the centroid algorithm, we have developed the 3D reconstruction algorithm, and use it to reconstruct a 3D image of target from the experimental data. We compare the 3D image with the system performance model, and the results are corresponding.

During the alt-azimuth telescope tracking, due to the frame structure of tracking support and relative movement of each mirror in Coude optical path, image plane is rotating. To eliminate the effects of image rotation for imaging and subsequent image processing, dove prism or K mirror are generally used. A set of K mirror system designed for 2m telescope. Affected by various errors in the alignment process, the rotating axis K, the optical axis of the K mirror, and the optical axis of the telescope’s optical system can’t be fully coincide. This causes the track optical axis drawn on the image is not a point, but a Pascal’s limacon. The impact caused by the various sources of error were analyzed in this paper and simulation results have important guiding significance for the alignment error distribution.

The success of the large telescope is largely linked to the excellent performance and reliability of the primary mirror. In order to maintain the quality of its reflective surface at the high expectations of astronomers, the primary mirror after almost two or three years of astronomical observations, needs to be removed and reinstalled for its cleaning and re-coating operation. There are a series of procedures such as the primary mirror cell dissembling from telescope, mirror handling, transportation, reintegration, alignment and so on. This paper will describe the experiences of disassembling and reintegration of large telescope primary mirror, taking a two meter grade primary mirror for example. As with all advanced and complex opto-mechanical systems, there has been the usual problems and trouble shooting.

To determine parameters of the Segmented Mirror Telescope is quite essential for the design, manufacture, testing and construct of the telescope system, especially the F-number parameters and curvature radius of the primary mirror, as well as the asphericity. A model of Sub-segmented mirror was established in this paper, based on which, using the feature points combined with lagrange condition extreme, the asphericity calculation of the asymmetrical hexagon off-axis parabolic mirror in different central points is solved. The 8m and 11m segmented mirror telescope were taken for example in the calculation, and got the relation curve between F-number of primary mirror and Asphericity of segmented mirror, respectively. This work is useful for the design, manufacturing and testing of the large diameter Segmented Mirror Telescope.

With the aim to decrease the gravitational distortion and stress for the large aperture optics, a novel mounting configuration was proposed, analyzed and optimized. The effects of the design factors of external load, supporting surface topography and supporting width were studied by using the Finite Element Method (FEM), the changing trends of the distortion and stress with these varying factors were obtained, respectively. More over, orthogonal tests of the influence of these factors were carried out, consequently, the regression analysis of the test results were processed, and the mathematical models for comprehensively considering the coupling effects of these factors were received. Further more, the optimization of the mounting configuration, based on the mathematical models and additionally considered the engineering specifications, was performed, and the optimal configuration was figured out. The numerical results showed the feasibility of the mounting configuration in the aspects of decreasing the gravitational distortion and stress.

Diffractive optical element (DOE) shows high diffraction efficiency and good dispersion performance, which makes the optical system becoming light-weight and more miniature. In this paper, the design, processing, testing, compensation of DOE are discussed, especially the analyzing of compensation technology which based on the analyzing the DOE measurement date from Taylor Hobson PGI 1250. In this method, the relationship between shadowing effect with diamond tool and processing accuracy are analyzed. According to verification processing on the Taylor Hobson NANOFORM 250 lathe, the results indicate that the PV reaches 0.539 micron, the surface roughness reaches 4nm, the step position error is smaller than λ /10 and the step height error is less than 0.23 micron after compensation processing one time.

From October 2010 to December 2012, the systematic study of the protected aluminum coating which is thermally evaporated downwards for large primary mirror had been developed. By adjusting the structure, it makes the physical nonuniformity of the bare aluminum films in the diameter of 1.8m drop to 4.18%, and the average reflectivity meets 95.09% in the band 400nm-2500nm. The optimized parameters suggest that the SiO_x (1<x<2) protective film with the oxygen flow of 50sccm has excellent environmental stability, and the average reflectivity of the protected aluminum coating reduces just less than 5%. Further, the SiO_xN_y protective film which is formed with 25sccm nitrogen flow not only has the environmental adaptability as the SiO_x film but also resists to the salt spray corrosion. But the average reflectivity of the SiO_xN_y protected aluminum coating decreases about 2%, reach 88.6%, in the band 400nm-2500nm.

With the aperture of large ground-based telescopes increasing, thermal issues appear more evidently. As a relatively large thermal expansion coefficient SiC (about 2.5x10^-6 /K), it makes large aperture SiC lightweight primary mirror more sensitive to temperature gradient. Firstly, discuss thermal issue of the mirror seeing induced by the temperature difference between the mirror surface and ambient theoretically. Then analyze the mirror surface deformation under seven different steady-state temperature fields with a unit temperature load. A uniform axial gradient can cause a mirror surface deflection RMS which can reach 438.4 nm. According to the simulation results, it shows that the primary is most sensitive to a uniform axial gradient and least to uniform change. Lastly, the parameter of thermal control is determined through the above analysis with the error budget to get a better image quality.

In order to analyze the tracking performance and design the controllers for TMT-M3 control system in the design stage. This paper presents the development of the analytical model of the gear driven large telescope using the lumped mass modeling method. The analytical model includes the telescope structure, its drives, the velocity loop and position loop. First, the modal model of a flexible structure is analyzed based on the finite-element data. And the modal model is transferred into the state-space model, in continuous-time. Next, the drive model is derived, and combined into the velocity loop and position loop. Finally, the impact of the error sources on the control loop properties is simulated. According to the simulation accuracy of the analytical modeling, the analytical model can be used in implementation, such as the model-based controllers.

Taking a 1m aperture photoelectric theodolite as study object, its key components including four-way, turntable and base are structural optimized so as to improve structural rigidity while reducing structural mass. First, various components’ working characteristics and relationships with the other parts are studied, based on these, reasonable finite element model of these components are established, then each component’s optimal material topology are obtained by continuum topology optimization. According to structural topology, lightweight truss structure models are constructed and the models’ key parameters are optimized in size. Finally, the structures optimized are verified by finite element analysis. Analysis prove that comparing to traditional structure, lightweight structures of theodolite’s three key components can reduce mass up to 1095.2kg, and increase ratio of stiffness to mass. Meanwhile, for other indexes such as maximum stress, static deformation and first-order natural frequency, lightweight structures also have better performance than traditional structure. After alignment, angular shaking error of theodolite’s horizontal axis is tested by autocollimator, the results are: maximum error is υ =1.82″, mean square error is σ =0.62″. Further, angular shaking error of theodolite’s vertical axis is tested by 0.2″ gradienter, the results are: maximum error is υ =1.97″, mean square error is σ =0.706″. The results of all these analysis and tests fully prove that the optimized lightweight key components of this 1m aperture theodolite are reasonable and effective to satisfy this instrument’s requirements.

TMT Tertiary Mirror System (M3S) is required to be able to track and point. It should rotate with the observing object. In this article, the schemes of Tertiary Mirror supporting assembly and position assembly are introduced. Then, the static and dynamic performance of Tertiary Mirror System has been analyzed. It is shown that, the maximum deflection is 1.024 mm, the maximum stress is 138.91MPa when gravity is affecting. The security of M3S can be assured when telescope is working at all required positions. The first nature frequency is 15.39Hz, the requirement 15 Hz has been satisfied. In addition, the response to earthquake has been estimated primarily. Results shows that when earthquake with mean return time 200 year happens in three directions simultaneous, or earthquake with mean return time 1000 years happens, the lateral support will be destroyed. Protection measures should be considered. Conclusions in this article are useful guides for the M3S design.

The tertiary mirror positioned assembly (M3PA) of the thirty meters telescope (TMT) is the largest tertiary mirror pointing system in the world. The tracking and pointing performance of M3PA is better than any other telescopes which have been built, and the working condition is even worse, so the designers face an enormous challenge. The tracking system includes the bottom rotator shaft and the tilt shaft. The study of this paper focuses on the tilt shaft. There are mainly three forms. The first form is one end fixed with the other unrestrained in axial direction. The second form uses two pairs of angular contact ball bearing. The last form lays two tape roller bearings. All of them can meet the requirements when the M3PA is vertical. But the first one becomes invalid when the M3PA is horizontal. We pay our attention on the study for the second arrangement method.. This bearing arrangement can produce a good stiffness, and increase the first modal frequency to 15.1Hz. In addition, some analysis were down to study the load applied on the balls. The results show that the maximum load is up to 5000N with the stress of 2300MPa.

Benefiting from low cost, light weight and reduced volume in launch, deployable optical telescopes will be extensively applied in microsatellites. As a result of manufactured tolerance and external disturbance, the secondary mirror can’t arrive at designed position precisely after a deployable telescope is unfolded. We investigate an adjustment system with six degrees of freedom based on hexapod structure to solve this problem. There are mainly four parts in this paper. Firstly, the adjustment methods of deployable telescopes for microsatellites are introduced. Generally several kinds of optical components can be adjusted to align a deployed telescope: primary mirror, tip/tilt mirror and secondary mirror. Due to its high sensitivity and convenience, the secondary mirror is chosen to collimate the optical system of the telescope. Secondly, an adjustment system with hexapod structure is designed for a secondary mirror with 85 mm diameter. After comparing the characteristics of step motors, piezo actuators and voice coil motors (VCMs), VCMs are selected as the linear actuators. By using optical gratings as displacement sensors in the system, we can make closed-loop control come true. The hexapod structure mainly consists of 6 VCMs, 6 optical gratings and 6 oblique legs with flexible hinges. The secondary mirror adjustment system is 83 mm in diameter and 55 mm high. It has tip/tilt rotational ranges of ±2.205° with resolution of better than ±0.007°, and translational ranges of ±1.545 mm with resolution of better than ±0.966 μm. Thirdly, the maximum stress and the maximum deformation in the adjustment system are computed with finite element method. At last, the kinematics problems of the adjustment system are discussed.

Stitching Fresnel lens are designed for the application in the micro-focus X-ray, but splicing errors between sub-apertures will affect optical performance of the entire mirror. The offset error tolerance of different degrees of freedom between the sub-apertures are analyzed theoretically according to the wave-front aberration theory and with the Rayleigh criterion as evaluation criteria, and then validate the correctness of the theory using simulation software of ZEMAX. The results show that Z-axis piston error tolerance and translation error tolerance of XY axis increases with the increasing F-number of stitching Fresnel lens, and tilt error tolerance of XY axis decreases with increasing diameter. The results provide a theoretical basis and guidance for the design, detection and alignment of stitching Fresnel lens.

When the swing arm profilometer(SAP) measuring the mirror, the effective arm length of SAP which haves an obvious influence on the measurement results of the mirror surface shape needs to be measured accurately. It requires the measurement uncertainty of the effective arm length to reach 10μm in order to meet the measurement requirements, in this paper, we present a kind of technology based on laser tracker to measure the effective arm length of SAP. When the swing arm rotates around the shaft axis of swing arm rotary stage, the probe and two laser tracker balls form three sections of circular arc around the shaft axis of swing arm rotary stage in space. Laser tracker tracks and measures the circular arcs of two laser tracker balls, the center coordinates of the circular plane of circular arc can be calculated by data processing. The linear equation that passes through the two center coordinates is the equation of the shaft axis of rotary stage, the vertical distance from the probe to the shaft axis of rotary stage which can be calculated refer to the equation from the point to the line is the effective arm length. After Matlab simulation, this measurement method can meet the measurement accuracy.

The existence of self-generated thermal radiation in infrared optical systems exhibits a great impact to the extraction of target signal and further degrades the signal-to-noise ratio (SNR), thus making the self-generated thermal radiation one of the important factors affecting the detective property. In this paper, a refraction-reflection optical system has been taken as an example and the three-dimensional simulation model has been built up using the ASAP optical analysis software. On this basis, the influence of the surface roughness, the level of the optics contaminated by the particles with the uniform and non-uniform distributions, the treatment of the mechanical surface (such as blacking, polishing, roughening) on the self-generated thermal radiation have been focused on discussion. Moreover, the thermal radiation of the system has been evaluated by the effective emissivity. The results indicate that the effective emissivity varies with different surface treatment. The self-generated thermal radiation is more and more serious with the increasing of the effective emissivity, resulting in great difficulty in obtaining and analyzing the target signal. It follows that the surface treatment of components exhibits a significant effect on the stray radiation performance in infrared optical systems. Consequently, appropriate treatments should be taken to diminish the self-generated thermal radiation in order to meet the requirements of the stray radiation performance in practical applications.

The particle contamination on the optical components would degrade the detection performance of the infrared optical systems and even make the detection task failure for the case of the optical components seriously contamitated. With the use of ASAP optical analysis software, a typical infrared optical-mechanical three-dimensional stimulation model has been built up. The particle distributions on the surface of the optical components have been studied and the particle distribution model has also been given. Furthermore, the influence of particle contamination on the stray light radiation characteristic of the infrared optical system has been analyzed in detail. The result shows that contamination particles randomly undergo collisions and small particles are loosely attached to each other at their first contact location and finally deposited as random single-particle aggregation and cluster-cluster aggregation, resulting in an obviously affect on the stray radiation performance of the infrared optical system. Furthermore, the change of the deposition positions of the contaminants aggregation also has a certain influence on the stray light radiation characteristics. In practical applications, it seems particularly important to control strictly over the contamination of optical surface during the operation of the infrared optical system.

The development of infrared optical materials is always closely related to the research and exploration of material science. The infrared optical domes bears shock and produces stress when the infrared optical domes mounted on the missile moving at a high speed is shocked by high temperature. According to aerodynamics theory and thermo shock theory, the surge current will be transferred to optical parts through holding up layer and warms the surface of optical parts when infrared optical parts are shocked by high temperature. A compress stress is formed on the hot external surface of optical parts forms and a tension stress is formed on the internal surface or optical parts under the circumstance of the edge of optical parts being fixed. The windows of optical parts become curvature radius of lens with the function of pressure difference which can cause aberration change. The brittle fracture of material will be caused if peak stress is beyond the strength which is permitted for infrared materials. Therefore, limits to design of windows thickness is proposed in this paper.

In order to accurately test shape quality of the large diameter aspherical mirror, a kind of binary optical element called Computer generated holograms (CGHs) are widely used .The primary role of the CGHs is to generate any desired wavefronts to realize phase compensation. In this paper, the CGH design principle and design process are reviewed at first. Then an optical testing system for testing the aspheric mirror includes a computer generated hologram (CGH) and an imaging element (IE) is disposed. And an optical testing system only concludes a CGH is proposed too. The CGH is designed for measurement of an aspheric mirror (diameter=404mm, F-number=2). Interferometric simulation test results of the aspheric mirror show that the whole test system obtains the demanded high accuracy. When combined the CGH with an imaging element in the Aspheric Compensator, the smallest feature in the CGH should be decreased. The CGH can also be used to test freeform surface with high precision, it is of great significance to the development of the freeform surface.

Lightweight mirrors have been used widely in ground-based imaging systems and astronomical telescopes, because of their light weight and good stiffness. However, space telescope mirrors cannot maintain their initial surface shape due to the effects such as gravity release, thermal changes in the space and so on. To deal with the problem, a new type of lightweight, active primary mirrors which are rib-stiffened and contain surface-parallel actuators embedded in the recess of the ribs, are designed for potentially using in space-based imaging systems. They enable larger primary aperture to improve resolution and sensitivity and are capable of on-orbit surface shape correction, which can control the shape of the mirrors to optical tolerances. According to the previous optimized parameters a prototype of lightweight, active mirrors is fabricated and tested. The influence functions of the fabricated prototype are measured by using a Veeco interferometer and the correctability for the Zernike aberrations is simulated. The results show that it has a good fitting ability for low order Zernike aberrations.

Quartz Crystal Microbalance (QCM) coated with polyetherimide (PEI) by spin coating method was applied for carbon dioxide (CO₂) gas detection at room temperature in this study. The experiments were performed in dry and humid air atmospheres, and the results revealed that the prepared CO2 sensor in moisture circumstance exhibited a larger sensing response than that at dry condition. An enhanced sensing response took place for CO₂ detection with the existence of water molecules. The effect of different humidity on QCM sensor performances was investigated as well in this paper. A curve, which displayed a proportional relationship between sensing response and water vapor concentration, was obtained. Moreover, the relevant sensing mechanisms were investigated.

Adhesive bonding technology has been widely applied in the field of space remote sensing. In order to make the adhesive bonds connecting the mirror and the fixed structures in a satellite launch or operation of dynamic environment without damage, the finite element model of the tilt mirror is essential to be established for dynamic analysis, as well as the experimental verification . There are detailed model and the equivalent stiffness model on the adhesive bonds. The modal, frequency response，random vibration and shock response are analyzed through the detailed model of the bonds. The stress of the three point mirror bonds is compared with the six point support mirror. The mechanics experiment is carried out based on the dynamics analysis. The results of calculation demonstrates that the impact of frequency response and random vibration on adhesive bonds is relatively little, while the impact of the shock response is large. The experimental verification shows that the stress of bonds with three points support mirror under shock response exceeds the shear strength, which leads to the separation of the mirror and the fixed structure and the improved six point support mirror is satisfied to the requirements. The dynamics analysis on adhesive bonds of tilt mirror makes sense for designing, assembling and mechanics experiment.

Active support system is a low-frequency wavefront error correction system, which is often used to correct the mirror deformation resulting from gravity, temperature, wind load, manufacture, installation and other factors. In addition, the active support technology can improve the efficiency of grinding and polishing by adjusting the surface shape in the process of manufacturing large mirrors. This article describes the design of an active support control system for a thin 1.2m primary mirror. The support system consists of 37 axial pneumatic actuators. And in order to change the shape of thin primary mirror we need to precisely control the 37 pneumatic actuators. These 37 pneumatic actuators are divided into six regions. Each region is designed with a control circuit board to realize force closed-loop control for the pneumatic actuators, and all control panels are connected to the PC by CAN bus. The control panels have to support: receive commands from the host PC; control the actuators; periodically return result of control. The whole control system is composed by hardware and control algorithm and communication program.

The truss structure had the merits of simple configuration, reliable, flexible assembly, specific stiffness and strong design ability. It was widely used in the support structure of Space camera and large telescope at home and abroad. The article described and analyzed truss structures of ground-based telescopes, space-based telescopes and Space camera. Conclusions that some reference should be followed in the truss design process were given. Simultaneously it also introduced the basic knowledge of truss design optimization, including the optimization ideas of truss structure and optimization algorithm of truss structure, which laid a good foundation for optimal design of truss in future.

The computer controlled active lap (CCAL) is used to grind a 1.8m honeycomb primary mirror. One problem which is not totally solved by CCAL is the edge effect, also exists in many other fabricating methods. To reduce the CCAL edge effect, the pressure distribution on the contact face between lap and mirror is analyzed by finite element method (FEM). A new method is proposed to calculate the pressure curve from FEM results. A simplified model is used to approximate the pressure curve along the mirror radius when active lap covers the mirror center hole. The const-linear (C-L) model is used to describe the pressure curve when active lap overhang at the mirror out edge. The contact status between lap and mirror is also considered in this paper, and its influence is taken into the material removal rate calculation. The API's T3 laser tracker is used to measure the mirror surface shape and to check the correctness of the theoretical model. The results that we have got by now and the problems that still exist are reported in this paper.

That minimizing the mass of space optical remote sensor at the same time guaranteeing of structural rigidity and surface shape accuracy, became a new critical research topic. This paper achieves detailed design of meniscus rectangular lens body structure by taking the choice of materials, design of supporting structure and lightweight form of mirror into account. And we established lightweight concrete of the mirror under self-weight by the method of topological optimization design. For the optimization, we used a 3-D model of the rectangular mirror and calculated based on that making minimum weight of the mirror as an objective function constrained by the displacement of the mirror surface. Finally finite element analysis method was adopted to get the optimization results analyzed and compared with the traditional triangular lightweight model. Analysis results prove that: the new mirror is superior to the traditional model in surface accuracy and structural rigidity, PV value, RMS value and the lightweight rate. With enough high dynamic-static stiffness and thermal stability, this kind of mirror can meet the demand under the self-weight and the random vibration environment respectively. So this article puts forward a new idea in the lightweight design of rectangular mirror.

In space reflective optical system, the back-point support is one of the widely used support means. For back-point support method, the support points position are important for the deformation of the reflective surface, find the best support points position of the mirror is particularly important. A new technique of mass allocation was discovered by using the theory of circular plate in this paper, and then the mass allocation method was used to look for the locations of the back support points on a single ring for a circular mirror having a central hole (primary mirror of Cassegrain telescope）. Then the Ansys software was used to calculate the deformation of the reflective surface when the mirror supported under different radius. It was validated that the mirror surface deformation is minimized due to gravity when supported in these positions which confirmed by mass allocation. It was proved that mass allocation is a simple and effective way to find the optimum support location of back-point support.

The performance of Adaptive Optics (AO) real-time controller based on Central Processing Unit (CPU) has significantly progressed due to the introduction of the high speed frame-grabber and a 4-cores CPU, which make it possible to process at frequency over 2000 Hz for 4-meter-class telescope and to integrate the real-time task and the user interface program in this compact device. The detailed architecture of this computation system is demonstrated in this paper, and the performance and suitability of this architecture is also discussed by measuring the latency of the controller processing via an adaptive optics emulator system with 16 times 16 and 32 times 32 sub-aperture, and the overall typical processing time is 61 us and 322 us respectively. Test result turns out that it is well suited for the next generation 4-meter-class adaptive optics system and it is possible to process at frequency over 2000 Hz for a 3000-element AO system in 10- meter-class telescope with one board of art-of-the-state computer and a frame-grabber. Comparison with GPU and FPGA based architecture is also discussed in this paper.

Using the diamond turning lathe and mono crystalline diamond tool, the aluminum alloy of 2A12 was cut under different cutting parameters including cutting speed, feed rate and depth of cut and the mirror surfaces were made. The surface roughness, micro hardness and residual stress of the mirror surface were tested by the surface profiler, the universal hardness tester and X-stress Robot. The influences of the cutting parameters on the mirror quality were studied. The research results have theoretical and practical significance to the selection of the optimal cutting parameters in ultraprecision diamond turning.

With the development of the fabricating and testing technology, the large optical system is widely used in more and more fields, the diameters of the convex aspheric mirrors are also becoming larger, generally the test of the large convex aspheres is much more difficult. It is always urgent to research and develop new fabricating and testing technology of the large convex aspheric components. In this paper we make a comparison of the advantages and disadvantages of the current test methods, at this basis another test method for the large convex aspheres–aspheric test plate method is given. The principle and test setup are explained detailedly. Using ZEMAX software we design and simulate the test plates and the wavefront error is better than 1/50 λ(PV).

The object of study is the electric control box of a certain type of space remote sensor. In view of the existing shortcomings of the original electric control box, the electric control box is designed reasonably. In the result, the design of electronic control box supported by the cylindrical multi-point is proposed, which can solve the series of problem of the original program, such as the large volume, heavy weight, large signal interference. The camera control box is made of magnesium alloy which has light weight and high strength; by the structure design of stacked, the electronics system is classified integration; through the local shielding program, the problem of anti radiation and interference of electronics system is solved; by using the multi supporting structure scheme , the structural rigidity of the electric control box is improved, the modal by 57Hz increased to more than 120Hz, which meet the 100Hz technology of the design specifications; the box body is adopted by nickel for protection, which eliminating the possibility of air and humid environment on the corrosion of magnesium alloy. At present, the electric control box designed has been completed the

For the purpose of monitoring the attitude of aircraft, an angular measurement system using a MEMS heat convection accelerometer is presented in this study. A double layers conditioning circuit that center around the single chip processor is designed and built. Professional display software with the RS232 standard is used to communicate between the sensor and the computer. Calibration experiments were carried out to characterize the measuring system with the range of - 90°to +90°. The curves keep good linearity with the practical angle. The maximum deviation occurs at the 90°where the value is 2.8°.The maximum error is 1.6% and the repeatability is measured to be 2.1%. Experiments proved that the developed measurement system is capable of measuring attitude angle.

We present a method to measure the radius of curvature of a concave conic asphere. By analysis the central area of the asphere, we can measure the radius of an arbitrary point in the central area instead of the vertex of asphere. In the procedure, we firstly adjust the interferometer until the interferogram of the central area approach nulls, then put the laser tracker ball at the beam focus of the interferometer and move the tracker ball to touch the central area of the aspherical surface to get the two positions. With these measurement data, we can calculate the radius of curvature of the aspherical vertex and its uncertainty.

Thermal properties and dispersive capacity of diffractive optical elements were expounded in this paper, and the conclusion that optothermal expansion coefficient of diffractive optical element is independent of refractive index of the material was derived. The design method to athermalize the hybrid infrared optical system was studied, a new hybrid system with diffractive surface was structured on the foundation of refractive/reflective optical system using optical design software ZEMAX, and the surface was simulated by MATLAB. The image quality was improved obviously compared with the one without diffractive surface. The system worked at 3.7~4.8μm band with its’ effective focal length of 70mm, field of view of 2° and possessed better athermal performance in the temperature range -40°~+60°. The image quality achieved diffractive limit, besides, a compact structure, small volume and light weight were other advantages of the hybrid system.

In structured light vision measurement system, the ideal image of structured light strip, in addition to black background , contains only the gray information of the position of the stripe. However, the actual image contains image noise, complex background and so on, which does not belong to the stripe, and it will cause interference to useful information. To extract the stripe center of mental surface accurately, a new processing method was presented. Through adaptive median filtering, the noise can be preliminary removed, and the noise which introduced by CCD camera and measured environment can be further removed with difference image method. To highlight fine details and enhance the blurred regions between the stripe and noise, the sharping algorithm is used which combine the best features of Laplacian operator and Sobel operator. Morphological opening operation and closing operation are used to compensate the loss of information.Experimental results show that this method is effective in the image processing, not only to restrain the information but also heighten contrast. It is beneficial for the following processing.

MEMS deformable mirrors (DM) have many merits of low drive voltage, high response speed, small power consumption, low cost and small size. Its surface shape and displacement versus applied voltage are significant factors of MEMS DM. Phase-shifting interferometer (PSI) has many advantages such as non-contact, quickness and high precision. A phase-only liquid crystal spatial light modulator (LC-SLM), as a linear phase-shifter in PSI, is linear calibrated for its phase-shift characteristics. The PSI is set up to measure the static characteristic of MEMS DM. Five-step phase-shifting method is used to calculate the phase distribution from interference fringes, and Global phase unwrapping algorithm to solve the holes, noise and breakpoint of interfere images. Compared to the measurement results using Zygo instrument, these two experimental results are very close. The experiment results show, this measuring system is very reliable, convenient and cheap. Moreover, this test system need not stitch some fringe images to get the whole surface shape of the mirror like the Zygo instrument.