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  The SCaN Testbed will consist of reconfigurable and reprogrammable SDR (Software Defined Radio) transceivers/transponders operating at S-band, Ka-band, and L-band, along with the required RF/antenna systems necessary for communications. Designed to operate for a minimum of two years, the three SDRs will provide S-band duplex RF (Radio Frequency) links directly with the ground, [also referred to as the Near Earth Network (NEN)], S-band duplex RF links with the TDRSS (Tracking and Data Relay Satellite System), [also referred to as the Space Network (SN)], Ka-band duplex with TDRSS, and L-band receive-only with the GPSS (Global Positioning Satellite System). The SCaN Testbed will be in low earth orbit and has multiple antennas providing connectivity to a series of NASA Space Network (SN) TDRSS satellites in geosynchronous orbits and NASA Near Earth Network (NEN) stations. The major components of the SCaN Testbed are shown above The SCaN Testbed uses a frequency assignment between IS...

 transit finder:  Fri 2022-09-09, 20:25:31.45  •  Moon transit ISS angular size: 34.72″; distance: 795.83 km Angular separation: 0.0′; azimuth: 122.5°; altitude: 28.7° Center line distance: 0.03 km; visibility path width: 16.02 km Transit duration: 1.03 s; transit chord length: 32.9′ R.A.: 22h 36m; Dec: -14° 44′; parallactic angle: 46.2° ISS velocity: 31.9 ′/s (angular); 7.39 km/s (transverse) ISS velocity: 0.41 km/s (radial); 7.40 km/s (total); Direction of motion relative to zenith: 84.9° Moon angular size: 32.9′; 56.8 times larger than the ISS Moon illumination: 98.7%; angular separation from Sun: 167.1° Sun altitude: -26.4°; the ISS will be in shadow   heavens above : the transit time is just ~1 second ( but still longer than transit in Nagoya on 23 Aug), and highly uncertain  Iss track using python pyephem, but space view Orbital using python numpy , cattech lab, github Three body periodic orbit sjtu , github , shijun liao

  transit finder(there is a bug in the time shown, which is calculated from your location, which is shown as UT+8 in this case. It should be UT+9, ie 12:06 JT)     data from JPL Horizons: the data is based on apparent RA and Dec of ISS and moon. The chart shows the delta of these 2 objects. The data is closest to zero is around 62nd data, which is 2:58 UTC, or 11:58 Japan Time(UT+9)         Taizo

This transit prediction has been removed from ISS transit, possibly due to recent change of ISS orbit transit finder: ISS Sat 2022-09-10, 19:31:59.69  •  Moon transit ISS angular size: 18.52″; distance: 1491.61 km Angular separation: 2.7′; azimuth: 103.9°; altitude: 10.0° Center line distance: 5.20 km; visibility path width: 63.86 km Transit duration: 1.97 s; transit chord length: 32.0′ R.A.: 23h 28m; Dec: -08° 46′; parallactic angle: 52.1° ISS velocity: 16.2 ′/s (angular); 7.05 km/s (transverse) ISS velocity: 2.30 km/s (radial); 7.42 km/s (total); Direction of motion relative to zenith: 85.2° Moon angular size: 32.4′; 105.1 times larger than the ISS Moon illumination: 99.8%; angular separation from Sun: 174.8° Sun altitude: -14.6°; the ISS will be in shadow     heavens above  ISS will pass low above horizon from south to north west, below 10 degrees altitude

To locate when ISS passes above you, use these   Transit-finder   Heavens above N2yo  Celestrak SubGP is very accurate, and provides TLE in 6 hour segments, and you can use simulator to visualise ISS ID: 25544  CSS TianHe Norad ID: 48274 Beebottle using celestrak data and python ESA should be most accurate, but only shows + or - 1.5 hours. so BE prepared to re-position the latest path ( takes a few seconds to refresh) spotthestation for Hong Kong trajectory data Kibo  forecast for Japan area only  Chinese Space Station, Tiangong  3 Aug 09:04 CSS Sun transit over Hong Kong, quite BIG difference in predictions, so don't have high hope on this rare event Orekit and forum talking about ISS pass in perl Sourceforge  by Ed Morana

  The Crew Dragon also had a few jobs of its own to complete. Crew and capsule would spend about two hours performing 3 different burns of the sixteen Draco thrusters outfitted all around the Crew Dragon’s outer shell. The first phasing burn was needed to insert it into the correct orbit, followed a little while later by a boost burn to raise the capsule’s orbit even more. And lastly, a close coelliptic burn to flatten out the orbit around the Earth making it more elliptical, rather than circular matching that of the ISS. These three burns were completed while the crew was awake performing any necessary tasks. Two more burns remained to be completed, but those would need to occur much closure to docking with the ISS, one while the crew slept and one just before autonomous docking procedures were set to begin. Flyby: "The way the two vehicles navigate together is relative, where you get pieces of information from both vehicles and you do the calculation and then they know exactly w...