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.
KEYWORDS: Cooling systems, HVAC controls, Control systems, Astronomy, Cameras, Charge-coupled devices, CCD cameras, Control systems design, Satellites, Imaging systems
The dark current noise existing in the CCD of the astronomical observation camera has a serious influence on its working performance, reducing the working temperature of CCD can suppress the influence of dark current effectively. By analyzing the relationship between the CCD chip and the dark current noise, the optimum working temperature of the red band CCD focal plane is identified as -75℃. According to the refrigeration temperature, a cooling control system for focal plane based on a thermoelectric cooler (TEC) was designed. It is required that the system can achieve high precision temperature control for the target. In the cooling control system, the 80C32 microcontroller was used as its systematic core processor. The advanced PID control algorithm is adopted to control the temperature of the top end of TEC. The bottom end of the TEC setting a constant value according to the target temperature used to assist the upper TEC to control the temperature. The experimental results show that the cooling system satisfies the requirements of the focal plane for the astronomical observation camera, it can reach the working temperature of -75℃ and the accuracy of ±2℃.
One space-based astronomy telescope will observe astronomy objects whose brightness should be lower than 23th magnitude. To ensure the telescope performance, very low system noise requirements need extreme low CCD operating temperature (lower than -65°C). Because the satellite will be launched in a low earth orbit, inevitable space external heat fluxes will result in a high radiator sink temperature (higher than -65°C). Only passive measures can’t meet the focal plane cooling specification and active cooling technologies must be utilized. Based on detailed analysis on thermal environment of the telescope and thermal characteristics of focal plane assembly (FPA), active cooling system which is based on thermo-electric cooler (TEC) and heat rejection system (HRS) which is based on flexible heat pipe and radiator have been designed. Power consumption of TECs is dependent on the heat pumped requirements and its hot side temperature. Heat rejection capability of HRS is mainly dependent on the radiator size and temperature. To compromise TEC power consumption and the radiator size requirement, thermal design of FPA must be optimized. Parasitic heat loads on the detector is minimized to reduce the heat pumped demands of TECs and its power consumption. Thermal resistance of heat rejection system is minimized to reject the heat dissipation of TECs from the hot side to the radiator efficiently. The size and surface coating of radiator are optimized to compromise heat reject ion requirements and system constraints. Based on above work, transient thermal analysis of FPA is performed. FPA prototype model has been developed and thermal vacuum/balance test has been accomplished. From the test, temperature of key parts and working parameters of TECs in extreme cases have been acquired. Test results show that CCD can be controlled below -65°C and all parts worked well during the test. All of these verified the thermal design of FPA and some lessons will be presented in this paper.
Mechanical stability is a significant segment for an on-axis space telescope to assure its assembly accuracy as well as the image quality in the rigorous space environment, supporting structure between the primary mirror and the secondary mirror as a main structure of the on-axis space telescope must be designed reasonably to meet the mission requirements of the space telescope. Meanwhile, in view of the limitation of the satellite launching cost, it is necessary to reduce the weight and power compensation during the supporting structure design based on the satisfaction of telescope performance. Two types of supporting structure for a space telescope are designed, one is three-tripod structure which has three tripods located on the optical bench to support the secondary mirror assemblies and keep the distance between the primary mirror and the secondary mirror, the other is barrel supporting structure which includes a tube and a secondary mirror support with four spider struts. To compare the mechanical performance and launching cost of the two kinds of supporting structure, both structural and thermal analysis model are established. The analysis results indicates that the three-tripod support is lighter, has better mechanical performance and needs less power compensation than the barrel support.
An attitude-varied space camera changes attitude continually when it is working, its attitude changes with large angle in short time leads to the significant change of heat flux; Moreover, the complicated inner heat sources, other payloads and the satellite platform will also bring thermal coupling effects to the space camera. According to a space camera which is located on a two dimensional rotating platform, detailed thermal design is accomplished by means of thermal isolation, thermal transmission and temperature compensation, etc. Then the ultimate simulation cases of both high temperature and low temperature are chosen considering the obscuration of the satellite platform and other payloads, and also the heat flux analysis of light entrance and radiator surface of the camera. NEVEDA and SindaG are used to establish the simulation model of the camera and the analysis is carried out. The results indicate that, under both passive and active thermal control, the temperature of optical components is 20±1°C,both their radial and axial temperature gradient are less than 0.3°C, while the temperature of the main structural components is 20±2°C, and the temperature fluctuation of the focal plane assemblies is 3.0-9.5°C The simulation shows that the thermal control system can meet the need of the mission, and the thermal design is efficient and reasonable.
Image intensifiers are always used to amplify low light level (LLL) images in a wide wavelength range to observable
levels. As a leader in image intensifiers for industrial and scientific applications, intensified CCD (ICCD) is an
innovative product which is a hybrid of image intensifier and CCD. Over the past few decades ICCDs have been
increasingly developed and widely used in a variety of fields such as LLL television system and medical diagnostics. In
this paper, we present the application of ICCD in the field of LLL remote sensing. General LLL imaging devices are
introduced briefly, and their advantages and disadvantages are compared. ICCD technology which includes fundamental,
configuration and development, is expatiated on. The major parameters which incarnate the performance of the LLL
remote sensing ICCD camera are analyzed in detail, such as signal noise ratio (SNR), dynamic range, spatial resolution,
etc. An ICCD camera is designed, and an imaging experiment is made to validate the imaging ability of it in LLL
condition. The experiment results are discussed and summarized. At last, the most important issues to the application of
ICCD in LLL remote sensing are generalized in detail.
A space telescope containing two CCD cameras is being built for scientific observation. The CCD detectors need to
operate at a temperature below -65°C in order to avoid unacceptable dark current. This cooling is achieved through
detailed thermal design which minimizes the parasitic load to 2K×4K array with 13.5 micron pixels and cools this
detector with a combination of thermo electric cooler(TEC).
This paper will describe detailed thermal design necessary to maintain the CCD at its cold operating temperature while
providing the means to reject the heat generated by the TECs. It will focus on optimized techniques developed to manage
parasitic loads including material selection, surface finishes and thermal insulation. The paper will also address analytical
techniques developed to characterize TEC performance. Finally, analysis results have been shown the temperature of key
parts.
One of the most significant requirements driving CCD assemblies design is the operating temperature. In order to avoid
unaccepted dark current, CCD need operate between 7°C and 15°C and temperature gradient across the focal plane
should be not greater than 1.0°C. These requirements must be achieved by combining active and passive measures. This
paper focuses on the precise thermal control design, analysis and test. Because CCD assemblies include focal electronics
and movable precise focalizing parts, thermal control must utilize the integrated method to achieve compatible design.
Largely using standard and well-proven technologies, this paper also points out some special techniques used. Based on
finite difference method and transient energy equations, thermal model of CCD assemblies were built utilizing thermal
software and solved for extreme cases. To validate the design, thermal balance test has been done. Analysis and test
results have shown that CCD temperature can be controlled between 7.2°C and 13.5°C and temperature gradient was less
than 0.5°C. These jobs could give some guidance and reference for the precise thermal control of CCD assembly of other
space optical remote-sensor.
A multi-discipline comprehensive archaeological study is being carried out to the well-known Chinese Emperor Qin Shi Huang's Mausoleum. In this paper, the research de- velopment and application of photogrammetry and remote sensing techniques will be des- cribed. In the project, the data and images were acquired by using the techniques of close-range photography,low-altitude photography and aerial remote sensing ( black-and-white and color infrared photography, thermal in frared scanning ). Several large scale present maps and orthophoto maps have been made as well as elevation drawings of different kinds of typical terra-cotta warriors, horses and weapons. In the area of known historical monuments, the inter pretation of remote sensing imagery made the de- tection be accurate upto 85%, while in the unknown area, it helped to make new archaeo- logical finds and to determine the range of flowing slopes. The operation procedures and methods for application of remote sensing technique in field archaeological work are stu- died and investigated.
Access to the requested content is limited to institutions that have purchased or subscribe to SPIE eBooks.
You are receiving this notice because your organization may not have SPIE eBooks access.*
*Shibboleth/Open Athens users─please
sign in
to access your institution's subscriptions.
To obtain this item, you may purchase the complete book in print or electronic format on
SPIE.org.
INSTITUTIONAL Select your institution to access the SPIE Digital Library.
PERSONAL Sign in with your SPIE account to access your personal subscriptions or to use specific features such as save to my library, sign up for alerts, save searches, etc.