The STSS Demo satellites are scheduled for launch on 2009 Sep 24, between 12:00 UTC and 13:00 UTC, from Cape Canaveral, aboard a Delta 2 rocket. Here are approximate elements, based on launch at window-open. The parking orbit is valid until T+42m30s: Parking orbit 185 X 1537 km 1 77001U 09267.50731830 .00000000 00000-0 00000-0 0 09 2 77001 54.6000 85.4138 0933762 36.2000 18.3000 14.09479000 08 Payload 1 1346 X 1352 km 1 77004U 09267.53320604 .00000000 00000-0 00000-0 0 08 2 77004 58.0000 84.9539 0003600 216.2526 335.5000 12.77975000 08 Payload 2 1339 X 1350 km 1 77005U 09267.53835649 .00000000 00000-0 00000-0 0 09 2 77005 58.0000 84.9400 0007193 216.2579 359.0000 12.79123000 03 Payload numbers are in order of separation from the 2nd stage. RAANs are accurate to 1 deg, at best. Argument of perigee of the payload orbits is a guess. They are intended to orbit in formation, separated by a central angle of 35 deg, or about 11 min of time. My guess of std magnitude is 6 to 7 (1000 km, 90 deg phase angle). So far, I have been unable to make a satisfactory estimate of the 2nd stage's final orbit, and am unlikely to make further efforts pre-launch. Considering the brief duration of the depletion burn, my guess is that relative the orbit of Payload 2, the 2nd stage's perigee may be reduced by hundreds of km, and its inclination changed by one or two degrees. Southern hemisphere observers near 30 S, would have all night visibility of the above orbits. Ted Molczan ------------------------------------------------------------------------- Subscribe/Unsubscribe info, Frequently Asked Questions, SeeSat-L archive: http://www.satobs.org/seesat/seesatindex.html
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