Current STS-72 TLEs, KEPs and State Vector <Set 05, Rev 011>

David Cottle (dcottle@ozemail.com.au)
Thu, 11 Jan 1996 20:02:05 -0800

>X-Sender: dcottle@ozemail.com.au
>Date: Thu, 11 Jan 1996 19:59:32 -0800
>To: STS TLE 2
>From: David Cottle <dcottle@ozemail.com.au>
>Subject: Current STS-72 TLEs, KEPs and State Vector <Set 05, Rev 011>
>
>STS-72      
>1 23762U 96001A   96012.08488769  .00015181  97191-9  12403-4 0    58
>2 23762  28.4493  88.9048 0204033  60.1300 293.0948 15.82402091   110
>
>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:        96012.08488768500
>                        01/12/1996  02:02:14.295 UTC
>ECI X:                   1040.86922424525 km
>    Y:                   6548.59949457960 km
>    Z:                   -495.66699999999 km
>    Xdot:                -6.7497380816721 km/s
>    Ydot:                1.19761367041567 km/s
>    Zdot:                3.67148800000001 km/s
>ndot/2 (drag):              0.00015181208 rev/day^2
>nddt/6:                       9.71910E-10 rev/day^3
>Bstar:                        1.24033E-05 1/Earth Radii
>Elset #:                                5
>Rev @ Epoch:               11.98119262377
>
>
>Keplerian Elements (Amsat format):
>
>Satellite: STS-72      
>Catalog number: 23762
>Epoch time:      96012.08488769
>Element set:       5
>Inclination:       28.4493 deg
>RA of node:        88.9048 deg
>Eccentricity:    0.0204033
>Arg of perigee:    60.1300 deg
>Mean anomaly:     293.0948 deg
>Mean motion:   15.82402091 rev/day
>Decay rate:    1.51812e-04 rev/day^2
>Epoch rev:              11
>Check sum:             286
>
>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/
>.
>
>

--------------
		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/
.