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
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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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