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 --- Astronomy is lights in the sky. --- 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