Current STS-72 TLEs, KEPs and State Vector <Set 25, Rev 064>

David Cottle (dcottle@ozemail.com.au)
Mon, 15 Jan 1996 03:52:21 -0800

STS-72      
1 23762U 96001A   96015.41847965  .00002327  00000-0  82412-5 0   257
2 23762  28.4518  64.7169 0007079 315.3670 194.6786 15.87717994   640

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:        96015.41847965300
                        01/15/1996  10:02:36.642 UTC
ECI X:                   -5128.0955785486 km
    Y:                   -3987.9823399280 km
    Z:                   1588.46499999999 km
    Xdot:                3.67273682748614 km/s
    Ydot:                -5.9982380167359 km/s
    Zdot:                -3.1899959999999 km/s
ndot/2 (drag):              0.00002327281 rev/day^2
nddt/6:                       0.00000E+00 rev/day^3
Bstar:                        8.24122E-06 1/Earth Radii
Elset #:                               25
Rev @ Epoch:               64.41683740596

Keplerian Elements (Amsat format):

Satellite: STS-72      
Catalog number: 23762
Epoch time:      96015.41847965
Element set:      25
Inclination:       28.4518 deg
RA of node:        64.7169 deg
Eccentricity:    0.0007079
Arg of perigee:   315.3670 deg
Mean anomaly:     194.6786 deg
Mean motion:   15.87717994 rev/day
Decay rate:    2.32728e-05 rev/day^2
Epoch rev:              64
Check sum:             352

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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