STS-74 Vectors

Rainer Kracht (0412188960-0001@t-online.de)
Mon, 13 Nov 95 21:09 +0100

STS-74 Vectors

I have found this at 
http://shuttle.nasa.gov/sts-74/orbit/orbiter/sighting/shuttle.txt

Rainer Kracht
0412188960-0001@t-online.de

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


                              STS-74   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 = Atlantis Post NC-1              

     Lift off time (UTC) : 1995:316:12:30:42.977

     Vector time (UTC) :  316:23:18:13.9000
     Vector time (MET) : +  0:10:47:30.923
     Orbit :     8
     Weight (lbs) : 236050.00
     Area (sq ft) : 2500.00
     Drag Coefficient (Cd) :  2.00
     90 day mean solar flux (janski) :  76.20
     12 month mean earth geomagnetic index :  2.76

     This vector is valid for prediction purposes until 317:16: 0:  .0 UTC


            M50 Cartesian                                 M50 Keplerian

     ------------------------------                     --------------------
     X    =   -4542413.91                           A  =    6693757.17 meter
     Y    =    -666124.73 meter                     E  =      .0026541
     Z    =    4857875.86                           I  =      51.81470
     XDOT =   3419.313860                           Wp =      10.70061
     YDOT =  -6528.477546 meter/sec                 RA =     132.01447 deg
     ZDOT =   2325.678608                           TA =      56.91495
                                                    MA =      56.66040
                                                    Ha =       180.004 n.mi
                                                    Hp =       160.819

            J2K Cartesian

     ------------------------------
     X    =   -4558234.31
     Y    =    -716994.42 meter
     Z    =    4835764.99
     XDOT =   3480.740798
     YDOT =  -6489.908477 meter/sec
     ZDOT =   2342.442912



     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


Atlantis Post NC-1              

STS-74  
1 23741U          95317.02234132  .00083907  00000-0  10188-3 0  9065
2 23741  51.6417 132.4532 0029699 358.4722   1.6351 15.83913244    94

Satellite: STS-74  
Catalog number: 23741
Epoch time:      95317.02234132   =     yrday.fracday
Element set:     906
Inclination:       51.6417 deg
RA of node:       132.4532 deg
Eccentricity:     .0029699
Arg of perigee:   358.4722 deg
Mean anomaly:       1.6351 deg
Mean motion:   15.83913244 rev/day
Decay rate:    8.39070E-04 rev/day^2
Epoch rev:               9
Checksum:              295


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


                              STS-74   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 = Predicted Atlantis Post NC-2    

     Lift off time (UTC) : 1995:316:12:30:42.977

     Vector time (UTC) :  317:16:11:29.7900
     Vector time (MET) : +  1: 3:40:46.813
     Orbit :    19
     Weight (lbs) : 233814.80
     Area (sq ft) : 2500.00
     Drag Coefficient (Cd) :  2.00
     90 day mean solar flux (janski) :  76.20
     12 month mean earth geomagnetic index :  2.76

     This vector is valid for prediction purposes until 318: 0: 0:  .0 UTC


            M50 Cartesian                                 M50 Keplerian

     ------------------------------                     --------------------
     X    =    -665775.49                           A  =    6745578.82 meter
     Y    =   -4948279.42 meter                     E  =      .0033178
     Z    =    4568301.86                           I  =      51.83576
     XDOT =   5982.677892                           Wp =     313.28816
     YDOT =  -3660.543442 meter/sec                 RA =     128.31584 deg
     ZDOT =  -3084.970948                           TA =     167.55573
                                                    MA =     167.47361
                                                    Ha =       210.477 n.mi
                                                    Hp =       186.309

            J2K Cartesian

     ------------------------------
     X    =    -632606.91
     Y    =   -4955536.97 meter
     Z    =    4565147.31
     XDOT =   6038.144301
     YDOT =  -3593.350925 meter/sec
     ZDOT =  -3055.765261



     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


Predicted Atlantis Post NC-2    

STS-74  
1 23741U          95317.71704137  .00083907  00000-0  10188-3 0  9079
2 23741  51.6471 128.8383 0037437 300.9675  58.7808 15.66193262   209

Satellite: STS-74  
Catalog number: 23741
Epoch time:      95317.71704137   =     yrday.fracday
Element set:     907
Inclination:       51.6471 deg
RA of node:       128.8383 deg
Eccentricity:     .0037437
Arg of perigee:   300.9675 deg
Mean anomaly:      58.7808 deg
Mean motion:   15.66193262 rev/day
Decay rate:    8.39070E-04 rev/day^2
Epoch rev:              20
Checksum:              324


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


                              STS-74   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 = Current Mir                     

     Lift off time (UTC) : 1995:316:12:30:42.977

     Vector time (UTC) :  316:23:18:28.8000
     Vector time (MET) : +  0:10:47:45.823
     Orbit : 55614
     Weight (lbs) : 246037.00
     Area (sq ft) : 3603.00
     Drag Coefficient (Cd) :  2.00
     90 day mean solar flux (janski) :  76.20
     12 month mean earth geomagnetic index :  2.76

     This vector is valid for prediction purposes until 321: 0: 0:  .0 UTC


            M50 Cartesian                                 M50 Keplerian

     ------------------------------                     --------------------
     X    =    4097300.07                           A  =    6777904.59 meter
     Y    =   -5353982.03 meter                     E  =      .0010718
     Z    =     650133.49                           I  =      51.85268
     XDOT =   4136.608657                           Wp =     123.74210
     YDOT =   2430.503545 meter/sec                 RA =     131.76994 deg
     ZDOT =  -5989.355794                           TA =      49.24721
                                                    MA =      49.15422
                                                    Ha =       219.770 n.mi
                                                    Hp =       211.925

            J2K Cartesian

     ------------------------------
     X    =    4153688.51
     Y    =   -5307861.67 meter
     Z    =     670180.01
     XDOT =   4138.233194
     YDOT =   2476.757250 meter/sec
     ZDOT =  -5969.251297



     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


Current Mir                     

STS-74  
1 16609U 86017A   95317.00455932  .00002873  00000-0  19312-4 0  9087
2 16609  51.6450 132.3330 0002657 325.7430  34.3553 15.58000851556152

Satellite: STS-74  
Catalog number: 16609
Epoch time:      95317.00455932   =     yrday.fracday
Element set:     908
Inclination:       51.6450 deg
RA of node:       132.3330 deg
Eccentricity:     .0002657
Arg of perigee:   325.7430 deg
Mean anomaly:      34.3553 deg
Mean motion:   15.58000851 rev/day
Decay rate:    2.87304E-05 rev/day^2
Epoch rev:           55615
Checksum:              294


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