Current STS-72 TLEs, KEPs and State Vector <Set 11, Rev 026>

David Cottle (dcottle@ozemail.com.au)
Fri, 12 Jan 1996 18:08:42 -0800

STS-72      
1 23762U 96001A   96013.00311271  .00000193  00000-0  55875-5 0   113
2 23762  28.4530  82.3303 0005282 184.2285 295.3797 15.34557436   263

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:        96013.00311270800
                        01/13/1996  00:04:28.937 UTC
ECI X:                   -5629.1891242369 km
    Y:                   -2645.8014182271 km
    Z:                   2829.78699999999 km
    Xdot:                2.40086025876774 km/s
    Ydot:                -7.0296605359735 km/s
    Zdot:                -1.7990399999999 km/s
ndot/2 (drag):              0.00000193446 rev/day^2
nddt/6:                       0.00000E+00 rev/day^3
Bstar:                        5.58746E-06 1/Earth Radii
Elset #:                               11
Rev @ Epoch:               26.33228671535


Keplerian Elements (Amsat format):

Satellite: STS-72      
Catalog number: 23762
Epoch time:      96013.00311271
Element set:      11
Inclination:       28.4530 deg
RA of node:        82.3303 deg
Eccentricity:    0.0005282
Arg of perigee:   184.2285 deg
Mean anomaly:     295.3797 deg
Mean motion:   15.34557436 rev/day
Decay rate:    1.93446e-06 rev/day^2
Epoch rev:              26
Check sum:             283

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


--------------
		David Cottle
		IDB Communications.
		Sydney, Australia.
--------------
David Cottle -	Email Primary : dcottle@ozemail.com.au
		Email Backup  : 100354.450@compuserve.com
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