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Monster Media 1993 #2
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STS-57
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1993-06-29
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STS-57 KEPLERIAN ORBITAL ELEMENTS
SPACELINK NOTE: Spacelink contains an IBM MS-DOS/Windows program (V2L9322.ZIP)
that will convert M-50 state vectors into the 2-line format preferred by many
callers. Enter IBM at the GO TO prompt and check out the section on satellite
tracking programs.
STS-57 element set GSFC-022 (orbit 112)
STS-57
1 22684U 93 37 A 93179.72593670 0.00002843 00000-0 51876-4 0 227
2 22684 28.4571 263.6705 0061374 75.9241 284.8171 15.44685342 1126
Satellite: STS-57
Catalog number: 22684
Epoch time: 93179.72593670 (28 JUN 93 17:25:20.93 UTC)
Element set: GSFC-022
Inclination: 28.4571 deg
RA of node: 263.6705 deg Space Shuttle Flight STS-57
Eccentricity: 0.0061374 Keplerian Elements
Arg of perigee: 75.9241 deg
Mean anomaly: 284.8171 deg
Mean motion: 15.44685342 rev/day Semi-major Axis: 6810.4349 Km
Decay rate: 0.28E-04 rev/day*2 Apogee Alt: 473.85 Km
Epoch rev: 112 Perigee Alt: 390.25 Km
NOTE - This element set is based on NORAD element set # 022.
The spacecraft has been propagated to the next ascending
node, and the orbit number has been adjusted to bring it
into agreement with the NASA numbering convention.
R.A. Parise, Goddard Space Flight Center
G.L.CARMAN
STS-57 FLIGHT DAY 8 STATE VECTOR
STS-57
FLIGHT DAY 8 STATE VECTORS
ON ORBIT OPERATIONS
(Posted 06/28/93 by Roger Simpson)
The following vector for the flight of STS-57 is provided by NASA Johnson
Space Center, Flight Design and Dynamics Division for use in ground track
plotting programs. The vector represents the trajectory of Endeavour
during on orbit operations after the rendezvous with Eureca.
Lift off Time : 1993/172/13:07:21.953
Lift off Date : 06/21/93
Vector Time (GMT) : 179/17:07:21.953
Vector Time (MET) : 007/04:00:00.000
Orbit Count : 111
Weight : 239544.0 LBS
Drag Coefficient : 2.00
Drag Area : 2750.0 SQ FT
M50 Elements Keplerian Elements
----------------------- --------------------------
X = -19323242.8 FT A = 3678.7196 NM
Y = -5706691.9 FT E = 0.005996
Z = -9921568.0 FT I (M50) = 28.20246 DEG
Xdot = 5047.439912 FT/S Wp (M50) = 73.52421 DEG
Ydot = -24091.412670 FT/S RAAN (M50) = 263.12893 DEG
Zdot = 4232.829273 FT/S / N (True) = 217.28186 DEG
Anomalies \ M (Mean) = 217.69954 DEG
Ha = 256.345 NM
Hp = 207.758 NM
Mean of 1950 (M50) : Inertial, right-handed Cartesian system whose
Coordinate System origin is the center of the earth. The epoch
is the beginning of the Besselian year 1950.
X axis: Mean vernal equinox of epoch
Z axis: Earth's mean rotational axis of epoch
Y axis: Completes right-hand system
A: Semi-major axis
E: Eccentricity N: True anomaly
I: Inclination M: Mean anomaly
Wp: Argument of perigee Ha: Height of apogee
RAAN: Right ascension of ascending node Hp: Height of perigee
Questions regarding these postings may be addressed to Roger Simpson,
Mail Code DM4, L. B. J. Space Center, Houston, Texas 77058,
Telephone (713) 483-1928.
Dear Customer, we are in the process of reviewing the contents of
this product and are interested in determining if it fits your needs.
If you use these state vectors, please drop us a postcard and
let us know what we can do to improve your use of this product.