urn:nasa:pds:context:instrument:ts.phb2 1.0 1.7.0.0 Product_Context 2016-10-01 1.0 extracted metadata from PDS3 catalog and modified to comply with PDS4 Information Model urn:nasa:pds:context:instrument_host:spacecraft.phb2::1.0 instrument_to_instrument_host Murray, B., Naraeva, M. K., Selivanov, A. S., Betts, B. H., Svitek, T., Kharlamov, V. D., Romanov, A. V., Santee, M. L., Gektin, Y. M., Fomin, D. A., Paige, D. A., Panfilov, A. S., Crisp, D., Head, J. W., Murchie, S. L. and Martin, T. Z., Preliminary Assessment of Termoskan Observations of Mars, Planetary and Space Sciences, volume 39, no. 1-2, 1991, pp 237-265. reference.MURRAYETAL1991 Selivanov, A.S., Naraeva, M.K., Panfilov, A.S., Gektin, Iu.M. and Kharlamov, V.D., Thermal Imaging of the Surface of Mars, Nature, vol. 341, October 19. 1989, p. 593-595. reference.SELIVANOVETAL1989 TERMOSKAN Radiometer not applicable not applicable Instrument Overview =================== This is a two-channel optical mechanical scanning radiometer termoskan designed for the scanning of Mars. The Termoskan radiometer operates in two spectral bands: 8.5-12 microns and 0.5- 0.95 microns. The line-by-line scanning is achieved by means of a mirror oscillating in a stepwise fashion, perpendicular to the spacecraft motion velocity; the frame scanning is accounted for by the motion of the spacecraft itself. The instantaneous field- of-view value in both channels is 0.9 arcmin, the scanning angle 6.1 degrees, and the scanning rate 1 line per second. It provides a resolution at nadir of 1.8x1.8 km and a swath length of 650 km from the circular observational orbit of 6,300 km. The area traversed in the direction of motion is a function of the length of the session. PDS1 Instrument Parameters ========================== PI_PDS_USER_ID = ASELIVANOV BUILD_DATE = 1988 INSTRUMENT_MASS = 28 INSTRUMENT_HEIGHT = 0.4 INSTRUMENT_LENGTH = 0.52 INSTRUMENT_WIDTH = 0.22 INSTRUMENT_MANUFACTURER_NAME = GLAVCOSMOS INSTRUMENT_SERIAL_NUMBER = 3 Scientific Objectives Summary ============================= The scientific objectives of this experiment were the following: o investigation of the daily and seasonal dynamics of the temperature condition on the surface. o measurement of the thermal inertia of martian soil. o detection of the humidified regions of surface and subsurface ice formations. o searching of the sources of internal heat. Instrument Calibration Description ================================== To provide the radiometric measurements during the scanning process, the instrument is calibrated relative to inner reference radiators and space. The fore optics are included in the calibration with the exception of the scanning mirror. Operational Considerations ========================== The scanning was conducted under conditions of uninterrupted astro-solar spatial attitude control of the spacecraft. Moreover, the axis-ifsight position in the center of Termoskan line is aligned with the solar-ray direction. During scanning, the distance from the spacecraft to the planet surface and the velocity of the subsatellite point were varied. As a result, changes in dimensions of the area traversed in the line direction and in line and frame resolution occurred. Visible Channel Detector ======================== DETECTOR_TYPE = SILICON PHOTODIODE DETECTOR_ASPECT_RATIO = 1.0 MINIMUM_WAVELENGTH = 0.5 MAXIMUM_WAVELENGTH = 1.0 NOMINAL_OPERATING_TEMPERATURE = 293 The contrast of the thermal images on the whole scanning route is higher than in the short-wave raange because of the lower dependence of the thermal contrasts on the Sun's position during scanning. A no-shadow condition in the visible spectrum gives rise to diminished contrast in channel 0.6-0.85 micron and allows the surface reflectance to be determined in that spectral range Thermal Channel Detector ======================== DETECTOR_TYPE = HG CD TE DETECTOR_ASPECT_RATIO = 1.0 MINIMUM_WAVELENGTH = 8.0 MAXIMUM_WAVELENGTH = 13.0 NOMINAL_OPERATING_TEMPERATURE = 180 The contrast of the thermal images on the whole scanning route is higher than in the short-wave raange because of the lower dependence of the thermal contrasts on the Sun's position during scanning. A no-shadow condition in the visible spectrum gives rise to diminished contrast in channel 0.6-0.85 micron and allows the surface reflectance to be determined in that spectral range. Instrument Mounting =================== The instrument was fixed to the spacecraft, pointing in the anti- solar direction. There was no scan platform. PDS1 Instrument Parameter Information ===================================== INSTRUMENT_PARAMETER_NAME = RADIANCE MINIMUM_INSTRUMENT_PARAMETER = N/A MAXIMUM_INSTRUMENT_PARAMETER = 15.0 NOISE_LEVEL = UNK INSTRUMENT_PARAMETER_UNIT = WATT/(METER*METER)/STERADIAN SAMPLING_PARAMETER_NAME = PIXEL MINIMUM_SAMPLING_PARAMETER = N/A MAXIMUM_SAMPLING_PARAMETER = 384 SAMPLING_PARAMETER_INTERVAL = 1 SAMPLING_PARAMETER_RESOLUTION = 1 SAMPLING_PARAMETER_UNIT = N/A PDS1 Instrument Mode Information ================================ INSTRUMENT_MODE_ID = OPERATING GAIN_MODE_ID = N/A DATA_PATH_TYPE = RECORDED DATA PLAYBACK INSTRUMENT_POWER_CONSUMPTION = 22 INSTRUMENT_MODE_DESC = N/A