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LZ4IC > SAREX 13.04.97 05:58l 123 Lines 4154 Bytes #-10577 (0) @ AMSAT
BID : 6153_LZ4IC
Read: GUEST OE7FMI
Subj: STS-83 keps from NASA Web site
Path: DB0AAB<DB0KCP<DB0ULM<DB0LX<DB0RBS<DB0SWR<DB0FP<DB0SRS<DB0ZDF<F6KFG<
F6KVE<F1TIV<F8KLY<F6KDC<F1HAQ<F1MAC<F1OYP<F5JOE<LZ2XA<LZ1DX<LZ4IC
Sent: 970405/2055Z @:LZ4IC.#PLD.BGR.EU #:6153 [Plovdiv] FBB7.00a $:6153_LZ4IC
From: LZ4IC@LZ4IC.#PLD.BGR.EU
To : SAREX@AMSAT
SAREX setup is officially on the flight plan for 22 hours after launch
(e.g. 12:20 pm Eastern Time Saturday). Here's the keps from the NASA WWW
site http://shuttle.nasa.gov/
STS-83 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 V2.1
Vehicle = Current Columbia
Lift off time (UTC) : 1997/ 94:19:20:31.9830
Vector time (UTC) : 1997/ 95: 1: 0: .0000
Vector time (MET) : + 0: 5:39:28.0170
Orbit : 4
Weight (lbs) : 248526.00
Area (sq ft) : 2500.00
Drag Coefficient (Cd) : 2.00
90 day mean solar flux (janski) : 74.00
12 month mean earth geomagnetic index : 1.91
This vector is valid for prediction purposes until 96:12: 0: .0 UTC
M50 Cartesian M50 Keplerian
------------------------------ ------------------------------
X = 2986533.48 A = 6686183.79 meter
Y = -5901270.78 meter E = .0014292
Z = -915456.25 I = 28.28775
XDOT = 6350.495175 Wp = 359.42515
YDOT = 2673.212391 meter/sec RA = 311.74673 deg
ZDOT = 3507.785794 TA = 343.75798
MA = 343.80374
Ha = 171.482 n.mi
Hp = 161.163
M50 Cartesian J2K Cartesian
------------------------------ ------------------------------
X = 9798338.20 X = 3056729.75
Y = -19361124.60 feet Y = -5867490.89 meter
Z = -3003465.40 Z = -900773.60
XDOT = 20834.957922 XDOT = 6303.095363
YDOT = 8770.381859 feet/sec YDOT = 2743.941863 meter/sec
ZDOT = 11508.483575 ZDOT = 3538.528864
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 Columbia
STS-83
1 24755U 97013A 97095.04453759 .00039131 00000-0 11921-3 0 9040
2 24755 28.4670 312.0225 0003182 334.3681 25.6938 15.90168259 53
Satellite: STS-83
Catalog number: 24755
Epoch time: 97095.04453759 = yrday.fracday
Element set: 904
Inclination: 28.4670 deg
RA of node: 312.0225 deg
Eccentricity: .0003182
Arg of perigee: 334.3681 deg
Mean anomaly: 25.6938 deg
Mean motion: 15.90168259 rev/day
Decay rate: 3.91310E-04 rev/day^2
Epoch rev: 5
Checksum: 307
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Philip Chien [M1959.05.31/31.145//KC4YER@amsat.org]
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Message forwarded by LZ4IC, E-Mail GateWay 4/5/97 10:54:43 PM
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