STS-71 rev 18 Vectors & TLE's

>From the NASA Shuttle Web:

----------------------------------------------------------------------

                         STS-71   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!

Vehicle = Atlantis KPT 010 Anchor

Lift off time (GMT) : 1995:178:19:32:18.953

Vector time (GMT) :  179:13:38:30.140
Vector time (MET) : +  0:18: 6:11.187
Orbit :    12
Weight (lbs) : 235750.20
Area (sq ft) : 2000.00
Drag Coefficient (Cd) :  2.00
90 day mean solar flux (janski) :  78.00
12 month mean earth geomagnetic index :  2.46

This vector is valid for prediction purposes until 180: 0: 0:  .0 GMT

 M50 Cartesian                                 M50 Keplerian

------------------------------                     --------------------
X    =   -1204207.74                           A  =    6731191.85 meter
Y    =    6661461.96 meter                     E  =      .0057264
Z    =       5767.09                           I  =      51.91941
XDOT =  -4642.148886                           Wp =     172.89823
YDOT =   -849.970687 meter/sec                 RA =     100.20858 deg
ZDOT =   6022.948247                           TA =     187.16378
                                         MA =     187.24596
                                         Ha =       211.438 n.mi
                                         Hp =       169.812

 J2K Cartesian

------------------------------
X    =   -1278614.37
Y    =    6647583.78 meter
Z    =       -265.14
XDOT =  -4661.567770
YDOT =   -901.975469 meter/sec
ZDOT =   6000.344008

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  = beginning of Julian date 2451545.0
X axis = mean vernal equinox of epoch
Z axis = earth mean rotation axis of epoch
Y axis = completes right handed cartesian earth centered system

           USSPACECOM TWO LINE MEAN ELEMENT SET

Atlantis KPT 010 Anchor
1 23600U 95030A   95179.56840440  .00073094  00000+0  27280-3 0  9075
2 23600  51.6494 100.8295 0065448 181.3862 178.6967 15.74326963   126

Vehicle:  Atlantis KPT 010 Anchor
Catalog number:   23600
Epoch time:       95179.56840440 yrday.frac day
Element set:     907
Mean inclination:        51.6494 deg
Mean ra of node:        100.8295 deg
Mean eccentricity:      .0065448
Mean arg of perigee:    181.3862 deg
Mean mean anomaly:      178.6967 deg
Mean mean motion:    15.74326963 rev/day
Mean decay rate:     0.73094D-03 rev/day^2
Bstar:               0.27280D-03 inverse earth radii
Epoch rev:           12

----------------------------------------------------------------------

                   STS-71   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!

Vehicle = Atlantis KPT 010 Anchor Post-NH

Lift off time (GMT) : 1995:178:19:32:18.953

Vector time (GMT) :  179:22:46:59.120
Vector time (MET) : +  1: 3:14:40.167
Orbit :    18
Weight (lbs) : 235574.00
Area (sq ft) : 2000.00
Drag Coefficient (Cd) :  2.00
90 day mean solar flux (janski) :  78.00
12 month mean earth geomagnetic index :  2.46

This vector is valid for prediction purposes until 180: 8: 0:  .0 GMT.
    ***Use Mir-based predictions following this time***

 M50 Cartesian                                 M50 Keplerian

------------------------------                     --------------------
X    =    -976801.39                           A  =    6735236.05 meter
Y    =    6707075.30 meter                     E  =      .0063558
Z    =       4760.69                           I  =      51.92047
XDOT =  -4664.223910                           Wp =     174.39806
YDOT =   -688.424123 meter/sec                 RA =      98.25462 deg
ZDOT =   6017.357868                           TA =     185.65306
                                         MA =     185.72515
                                         Ha =       215.923 n.mi
                                         Hp =       169.694

 J2K Cartesian

------------------------------
X    =   -1051729.93
Y    =    6695736.47 meter
Z    =       -167.80
XDOT =  -4685.419909
YDOT =   -740.685623 meter/sec
ZDOT =   5994.642045

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  = beginning of Julian date 2451545.0
X axis = mean vernal equinox of epoch
Z axis = earth mean rotation axis of epoch
Y axis = completes right handed cartesian earth centered system

           USSPACECOM TWO LINE MEAN ELEMENT SET

Atlantis KPT 010 Anchor Post-NH
1 23600U 95030A   95179.94929537  .00073094  00000+0  27300-3 0  9086
2 23600  51.6490  98.8688 0071891 181.9594 178.1134 15.72904686   180

Vehicle:  Atlantis KPT 010 Anchor Post-NH
Catalog number:   23600
Epoch time:       95179.94929537 yrday.frac day
Element set:     908
Mean inclination:        51.6490 deg
Mean ra of node:         98.8688 deg
Mean eccentricity:      .0071891
Mean arg of perigee:    181.9594 deg
Mean mean anomaly:      178.1134 deg
Mean mean motion:    15.72904686 rev/day
Mean decay rate:     0.73094D-03 rev/day^2
Bstar:               0.27300D-03 inverse earth radii
Epoch rev:           18
----------------------------------------------------------------------