STS 69 is in orbit, i = 28

Walter Nissen (dk058@cleveland.Freenet.Edu)
Thu, 7 Sep 1995 12:07:00 -0400

STS69 successfully launched within seconds of the schedule at 950907 1509. 
 
I was prowling around http://shuttle.nasa.gov, selected Orbit, and then 
Shuttle State Vector and found the appendix.  Note TLE and "valid for". 
 
I wonder if we should express our desires for advance TLEs to 
don.j.pearson1@jsc.nasa.gov? 
 
Cheers. 
 
Walter Nissen             dk058@cleveland.freenet.edu             216-243-4980 
 
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Astronomy is lights in the sky. 
 
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                         STS-69   STATE VECTOR 
 
The following on-orbit vector is provided by NASA Johnson Space Center 
Flight Design and Dynamics Division for use in ground track 
plotting programs. It should not be used for precise applications 
or analysis! 
 
Please direct any comments to: 
DM42/ Head, Orbit Flight Dynamics Group at email: 
don.j.pearson1@jsc.nasa.gov 
 
Data were generated using application SPCM V2.0 
 
Vehicle = Endeavour Predicted Post-OMS-2 
 
Lift off time (UTC) : 1995:250:15: 9:  .000 
 
Vector time (UTC) :  250:15:53:54.8100 
Vector time (MET) : +  0: 0:44:54.810 
Orbit :     1 
Weight (lbs) : 245273.00 
Area (sq ft) : 2752.00 
Drag Coefficient (Cd) :  2.00 
90 day mean solar flux (janski) :  78.50 
12 month mean earth geomagnetic index :  3.18 
 
This vector is valid for prediction purposes until 252: 0: 0:  .0 UTC 
 
       M50 Cartesian                                 M50 Keplerian 
X    =    2005244.16                           A  =    6754320.54 meter 
Y    =   -5698964.27 meter                     E  =      .0007214 
Z    =   -3009356.71                           I  =      28.63296 
XDOT =   6887.500129                           Wp =     254.65636 
YDOT =   3136.829692 meter/sec                 RA =      43.55098 deg 
ZDOT =  -1349.641307                           TA =     353.84756 
                                               MA =     353.85642 
                                               Ha =       205.744 n.mi 
                                               Hp =       200.482 
 
       J2K Cartesian 
X    =    2083426.03 
Y    =   -5676109.92 meter 
Z    =   -2999422.92 
XDOT =   6858.479929 
YDOT =   3213.665280 meter/sec 
ZDOT =  -1316.244174 
 
M5O    = Inertial mean of year 1950 frame of reference 
Epoch  = beginning of Besselian year 1950 
X axis = mean vernal equinox of epoch 
Z axis = earth mean rotation axis of epoch 
Y axis = completes right handed cartesian earth centered system 
 
J2K    = Inertial mean of year 2000 frame of reference 
Epoch  = Julian date 2451545.0 TDT 
X axis = mean vernal equinox of epoch 
Z axis = earth mean rotation axis of epoch 
Y axis = completes right handed cartesian earth centered system 
 
The mean element set is posted at a UTC for which position is 
just north of the next ascending node relative to the above 
vector time 
 
                 USSPACECOM TWO LINE MEAN ELEMENT SET 
 
Endeavour Predicted Post-OMS-2 
1 80069U          95250.68212189  .00001980  00000-0  50309-5 0  9025 
2 80069  28.4680  43.6332 0004982 271.9985  88.0212 15.64898689    25 
 
Satellite: Endeavour Predicted Post-OMS-2 
Catalog number: 80069 
Epoch time:      95250.68212189   =     yrday.fracday 
Element set:     902 
Inclination:       28.4680 deg 
RA of node:        43.6332 deg 
Eccentricity:     .0004982 
Arg of perigee:   271.9985 deg 
Mean anomaly:      88.0212 deg 
Mean motion:   15.64898689 rev/day 
Decay rate:    1.97996E-05 rev/day^2 
Epoch rev:               2 
Checksum:              342