Current STS-72 TLEs, KEPs and State Vector <Set 29, Rev 075>

David Cottle (dcottle@ozemail.com.au)
Mon, 15 Jan 1996 20:11:33 -0800

STS-72      
1 23762U 96001A   96016.08686094  .00002627  00000-0  85462-5 0   290
2 23762  28.4523  59.7383 0007181 347.3257  33.9455 15.89397970   758

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:        96016.08686093700
                        01/16/1996  02:05:04.784 UTC
ECI X:                   1296.44395635154 km
    Y:                   6445.60538621194 km
    Z:                   1152.52600000000 km
    Xdot:                -6.8872443977375 km/s
    Ydot:                0.76949015797765 km/s
    Zdot:                3.43616400000000 km/s
ndot/2 (drag):              0.00002626564 rev/day^2
nddt/6:                       0.00000E+00 rev/day^3
Bstar:                        8.54618E-06 1/Earth Radii
Elset #:                               29
Rev @ Epoch:               75.05905229078

Keplerian Elements (Amsat format):

Satellite: STS-72      
Catalog number: 23762
Epoch time:      96016.08686094
Element set:      29
Inclination:       28.4523 deg
RA of node:        59.7383 deg
Eccentricity:    0.0007181
Arg of perigee:   347.3257 deg
Mean anomaly:      33.9455 deg
Mean motion:   15.89397970 rev/day
Decay rate:    2.62656e-05 rev/day^2
Epoch rev:              75
Check sum:             345

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
		W.W.W. Page   : http://www.ozemail.com.au/~dcottle/
.