Current STS-72 TLEs, KEPs and State Vector <Set 12, Rev 028>

David Cottle (dcottle@ozemail.com.au)
Fri, 12 Jan 1996 23:30:59 -0800

STS-72      
1 23762U 96001A   96013.16891124  .00000171  00000-0  54025-5 0   123
2 23762  28.4484  81.1932 0002476 126.8131 190.1700 15.31735718   286

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:        96013.16891123800
                        01/13/1996  04:03:13.930 UTC
ECI X:                   4831.60074889540 km
    Y:                   4316.02692599884 km
    Z:                   -2227.2699999999 km
    Xdot:                -4.0460301424399 km/s
    Ydot:                5.89678314627136 km/s
    Zdot:                2.65726299999999 km/s
ndot/2 (drag):              0.00000170998 rev/day^2
nddt/6:                       0.00000E+00 rev/day^3
Bstar:                        5.40253E-06 1/Earth Radii
Elset #:                               12
Rev @ Epoch:               28.88055679003


Keplerian Elements (Amsat format):

Satellite: STS-72      
Catalog number: 23762
Epoch time:      96013.16891124
Element set:      12
Inclination:       28.4484 deg
RA of node:        81.1932 deg
Eccentricity:    0.0002476
Arg of perigee:   126.8131 deg
Mean anomaly:     190.1700 deg
Mean motion:   15.31735718 rev/day
Decay rate:    1.70998e-06 rev/day^2
Epoch rev:              28
Check sum:             291

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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