The deployed S/C length is 25.78 m. The CCD Camera consists of the following elements: scan mechanism assembly, optics and detector assembly, and camera electronics. On-orbit mass is 911 kg. The INSAT-2 program at ISRO was underway in 1983 to develop an indigenous multi-purpose GEO spacecraft that relied heavily on the previous Ford Aerospace design. The INSAT-2 series flies a data collection system (DCS) with a data relay transponder (DRT) for environmental data collection from DCPs (Data Collection Platforms) the ground segment. • North & south equipment panels are of size 2300 mm x 1930 mm. • Two flaps offsetting seasonal variations in solar pressure; it is operated by a shaped memory alloy spring VHRR/2 consists of the following major subsystems: scan mechanism assembly, radiant cooler, Optics assembly, and camera electronics. The S/C is three-axis stabilized (momentum-biased) and uses a box-shaped structure based around a central cylinder of 0.89 m diameter with asymmetrical five-panel solar wings (23 m span). This permits independent performance optimization of the TIR and IR (water vapor) bands in the radiant cooler/detector system.
Further Indo-US workshops were held to identify fields of cooperation: They are attached to the main cylinder using shear frames VHRR is an improved version over that of the INSAT-1 series.
You are welcome to send updates and corrections to webmaster@lyngsat.com Logotypes provided by LyngSat Logo Orbit maneuvers are supported by an integral apogee boost motor, there are also 16 attitude control thrusters. The scanner electronics, the DC/DC converter regulators, patch temperature controller and the analog telemetry processor are part of the electronics package-2. This mission was named MetSat-1 and was launched on Sept. 12, 2002. • Camera electronics: The subsystem provides: a) clock and bias inputs to the detectors, b) processes and digitizes the detector outputs., c) formats the video signal along with auxiliary information, d) monitors the instrument; e) interfaces with other subsystems, and f) controls the SWIR detector temperature through a feedback loop. Launch: June 3, 1997, Ariane 44L, at 93.5º E, Satellite TV charts all over the world from Asia, Europe, Atlantic and America.
VHRR was designed and built at ISRO. • Two independent power buses with cross-strap capability, each bus regulated to 42+0.5 V by sequential switching The meteorological instrument on the INSAT-2E spacecraft features an additional band in the water vapor absorption spectrum of 6.8 µm. The characteristics of the DCPs are: A separate 0.9 m diameter Earth view antenna on-board the S/C is providing transmission services for the meteorological data. 4100H would be cool (new "landpoint").Very cool reception of 83E for your location Kveys! The IR detector assembly consists of two HgCdTe photoconductive detectors mounted in the passive radiant cooler. Both meteorological payloads have a common up convertor and a redundant transmitter for a downlink through a 4.5 GHz carrier.
• Near omni radio visibility during transfer orbit phase • The S/C main body is a cuboid of dimension: 1930 mm x 1770 mm x 2375 mm. The INSAT-2 meteorological sensor VHRR has a 2 km resolution in VIS and 8 km resolution in the IR spectral ranges. • Provision of variable execution pulse width command feature
The water vapor band is used for estimating water-vapor-tracer winds at the mid-troposphere, identifying subsidence/convection zones, and indirectly estimating the atmospheric correction to SST (Sea Surface Temperature) for the TIR channel. The north-facing Earth sensor is used during transfer orbit to maintain Earth lock. General description of the INSAT-2E satellite bus system. • Optics and detector assembly: The assembly consists of the scan mirror, telescope, dichroic beam splitters, fold mirror, lens doublet and bandpass filters. 3976H ZEE Sangam more than 12 db on mornings.... as I mentioned above 4040H first time here.
Under another collaborative program with EUMETSAT, an agreement has been signed for reception of METEOSAT data at IMD, New Delhi. All rights reserved. An image of 20º x 20º (TFOV) is generated within 33 minutes, covering the full disk of the Earth. The 0.4º south stepping of the mirror after each east-west scan provides the generation of successive image strips. 6250 km x 300 km per scan line (max. I am new. The INSAT-2 series was conceived with five spacecraft INSAT-2A through -2E, with the first two, INSAT-2A and INSAT-2B, planned to be realized as multipurpose satellites on the lines of the INSAT-1 system. 2 258: Tam IN: Coverage: 2-SEP-2008 3.934, 12, V Subhavaartha TV DVB 13021 3/4 2 273 1 2 274 IN: Coverage: 2-SEP-2008 3.934, 12, V Star Jalsha VIACCESS, MPEG-4 13021 3/4 4 501 1 2 502: Ben IN: Coverage: 23-DEC-2008 3.934, 12, V Star Pravah VIACCESS, MPEG-4 13021 3/4 5 504 1 2 …
The data of the CCD Camera in PCM NRZ-L format is QPSK modulated, the data rate is 1.3 Mbit/s. I would like to know if I may be able to receive signals from the Insat 2E satellite located at 83 degrees east.