Hi All, Thanks Bjorn for the search elements - Ill have a go tonight. At the moment its not too bad-- some light cirrus that may disappear or get worse! but at least Im ready to do a long session tonight - will have a search for USA56 rocket which seems lost as well as your two element sets. The weather for the rest of the week isnt too good so its more or less "now or never" so as long as I can see stars Ill try... Cheers Greg ----- Original Message ----- From: "Björn Gimle" <b_gimle@algonet.se> To: "Ted Molczan" <molczan@rogers.com>; "SeeSat-L" <SeeSat-L@satobs.org>; "Greg Roberts" <grr@iafrica.com> Sent: Tuesday, November 19, 2002 9:10 PM Subject: Re: USA 116 search elements > 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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