I made an orbit for USA 116 assuming +15 m/s at perigee 02319.8447 If it maneouvred a day before as I supposed, it would be 9-10 minutes late etc. Add to that about one minute/day elapsed since the maneouvre because of uncertainty of its size. USA 116 Search - after +15 m/s reboost. 897 x 403 1 70001U 02319.84470000 .00004926 00000-0 25658-3 0 10 2 70001 97.9270 75.9623 0351388 189.6065 0.3060 14.73535231 428 With the same assumptions for USA 161 USA 161 Search - after +15 m/s reboost. 895 x 405 1 26934U 01044A 02319.84000000 .00008000 00000-0 33807-3 0 16 2 26934 97.9060 70.1931 0348630 220.8245 0.5293 14.73535513 7996 USA 129 would be passing about 160 minutes before USA 161, decreasing by 1 min/day. Since it is currently near perigee at shadow entry lat. 50 S, I will probably not compute elsets until 161 (and/or 116) is found again. (Actually I will have a few points above 10 degrees from horizon before Greg will - if I only get some clear skies) ----- Original Message ----- From: "Ted Molczan" <molczan@rogers.com> To: "SeeSat-L" <SeeSat-L@satobs.org> Sent: Thursday, November 14, 2002 10:11 PM Subject: USA 116 search elements > Using Greg Roberts' 2nd through 5th recovery points of object 95066A / 23728, I obtained the following: > > 1 70000U 02316.97439815 .00004900 00000-0 25658-3 0 00 > 2 70000 97.9270 73.1037 0313600 198.4561 160.5554 14.82147778 06 > > WRMS error = 0.017 deg > > I have issued the elements without the identifiers because I suspect they could differ significantly from the actual orbit. > > I derived the elements as follows: > > - inclination fixed at the value of the epoch day 02266 elements > > - rate of decay is apparent mean rate since the epoch of the epoch day 02266 elements > > - mean motion estimated from the apparent mean rate of decay > > - eccentricity estimated on the basis of maintaining the perigee distance of the epoch day 02266 elements > > - argument of perigee estimated by precessing epoch day 02266 elements to the epoch of the new elements > > - RAAN and mean anomaly computed by differential correction, holding all other elements constant > > Ted Molczan > > > ----------------------------------------------------------------- > Unsubscribe from SeeSat-L by sending a message with 'unsubscribe' > in the SUBJECT to SeeSat-L-request@lists.satellite.eu.org > http://www.satellite.eu.org/seesat/seesatindex.html > > ----------------------------------------------------------------- Unsubscribe from SeeSat-L by sending a message with 'unsubscribe' in the SUBJECT to SeeSat-L-request@lists.satellite.eu.org http://www.satellite.eu.org/seesat/seesatindex.html
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