Re: USA 116 search elements

From: Björn Gimle (b_gimle@algonet.se)
Date: Tue Nov 19 2002 - 14:10:13 EST

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    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
    >
    >
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