Current STS-72 TLEs, KEPs and State Vector <Set 19, Rev 047> **

David Cottle (dcottle@ozemail.com.au)
Sun, 14 Jan 1996 02:26:03 -0800

>Date: Sun, 14 Jan 1996 02:24:39 -0800
>To: 2 STS TLE 2
>From: David Cottle <dcottle@ozemail.com.au>
>Subject: Current STS-72 TLEs, KEPs and State Vector <Set 19, Rev 047> **
>
>STS-72      
>1 23762U 96001A   96014.33381082  .00002418  00000-0  83517-5 0   191
>2 23762  28.4519  72.7963 0006487 287.6912 129.1231 15.88221575   479
>
>Launch time for STS-72: 11 JAN 96 @ 09:41:00.086 UTC
>
>Earth-Fixed Greenwich State Vector :
>
>Vector format = 7
>Satellite Name:         STS-72 
>Catalog Number:         23762  96001A    
>Epoch Date/Time:        96014.33381082200
>                        01/14/1996  08:00:41.255 UTC
>ECI X:                   -3618.3684593028 km
>    Y:                   4946.90724867347 km
>    Z:                   2663.82900000000 km
>    Xdot:                -5.4624934019719 km/s
>    Ydot:                -5.0793666310309 km/s
>    Zdot:                2.01495199999999 km/s
>ndot/2 (drag):              0.00002417777 rev/day^2
>nddt/6:                       0.00000E+00 rev/day^3
>Bstar:                        8.35169E-06 1/Earth Radii
>Elset #:                               19
>Rev @ Epoch:               47.15777094239
>
>
>Keplerian Elements (Amsat format):
>
>Satellite: STS-72      
>Catalog number: 23762
>Epoch time:      96014.33381082
>Element set:      19
>Inclination:       28.4519 deg
>RA of node:        72.7963 deg
>Eccentricity:    0.0006487
>Arg of perigee:   287.6912 deg
>Mean anomaly:     129.1231 deg
>Mean motion:   15.88221575 rev/day
>Decay rate:    2.41778e-05 rev/day^2
>Epoch rev:              47
>Check sum:             322
>
>Drag Factor is 0.1
>
>SPACE SHUTTLE ORBITAL DATA:
>
>These 2-line elements have been generated using Ken Ernandes' program
>VEC2TLE using real time state vector data supplied by DOD C-Band Radar
>Network courtesy Dave Simonson. Note that the epoch of the 2-line
>elements is the same as the state vector time.
>
>Occasionally these elements are derived from the Goddard Space Flight Center
>(GSFC) NASA Orbital Information Group (OIG), using Curtis Haases' program
>VEC2VIF that formats the OIG vectors for use by VEC2TLE.
>
>The source of the data can be confirmed by the data format of the vector ;
>EFG, ft, ft/s      = DOD C-Band Radar Network
>ECI, km, km/s      = NASA OIG RAID RBBS
>ECI M50, ft, ft/s  = Rockwell Mission Support Room
>
>Drag and B-Star parameters are internally calculated by VEC2TLE using
>the drag factor. Rev numbers use NASA orbit numbering convention.
>
>                                Dave Cottle
>
>
>NOTE - Thanks to John Marxmiller, I found my dual 100 MHz pentium machine
is making mistakes. I verified set 18, and this machine verifies it fine,
but my second pentium shows the TLE is incorrect. I noticed the mean motion
was out, but this machine verified it fine compared to previous sets. I
found one of the CPU fans had stopped working and made the error.
>
>My appologies to all, hardware mistakes was not anticipated..
>
>                Dave Cottle.
>
>
>

--------------
		David Cottle
		IDB Communications.
		Sydney, Australia.
--------------
David Cottle -	Email Primary : dcottle@ozemail.com.au
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.