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Software Vault: The Gold Collection
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Software Vault - The Gold Collection (American Databankers) (1993).ISO
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cdr21
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gsfc_014.zip
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STS-57
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1993-06-24
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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. This program may prove useful on occasions when the M-50
elements are more current than the 2-line elements.
STS-57 element set GSFC-014 (orbit 49)
STS-57
1 22684U 93 37 A 93175.64821865 0.00000990 00000-0 30148-4 0 145
2 22684 28.4591 292.0278 0005299 194.1335 165.9112 15.29165967 493
Satellite: STS-57
Catalog number: 22684
Epoch time: 93175.64821865 (24 JUN 93 15:33:26.09 UTC)
Element set: GSFC-014
Inclination: 28.4591 deg
RA of node: 292.0278 deg Space Shuttle Flight STS-57
Eccentricity: 0.0005299 Keplerian Elements
Arg of perigee: 194.1335 deg
Mean anomaly: 165.9112 deg
Mean motion: 15.29165967 rev/day Semi-major Axis: 6856.4363 Km
Decay rate: 0.99E-05 rev/day*2 Apogee Alt: 481.68 Km
Epoch rev: 49 Perigee Alt: 474.42 Km
NOTE - This element set is based on NORAD element set # 014.
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 4 STATE VECTORS
ON ORBIT OPERATIONS
(Posted 06/24/93 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.
***NOTE***
THE FOLLOWING IS THE SCHEDULE TO BE USED TO UPDATE THE ORBITER VECTOR
BEING POSTED ON THE JSC PAO BULLETIN BOARD:
FLIGHT DAY 5: FRIDAY, 2000 GMT, 3:00 p.m. CDT
FLIGHT DAY 8: MONDAY, 1400 GMT, 9:00 a.m. CDT
Lift off Time : 1993/172/13:07:21.953
Lift off Date : 06/21/93
Vector Time (GMT) : 175/18:47:21.953
Vector Time (MET) : 003/05:40:00.000
Orbit Count : 051
Weight : 243584.0 LBS
Drag Coefficient : 2.00
Drag Area : 2750.0 SQ FT
M50 Elements Keplerian Elements
----------------------- --------------------------
X = 14493930.9 FT A = 3705.2990 NM
Y = -16708000.7 FT E = 0.001032
Z = 4101483.1 FT I (M50) = 28.24192 DEG
Xdot = 15598.841162 FT/S Wp (M50) = 61.18081 DEG
Ydot = 16235.131015 FT/S RAAN (M50) = 290.74579 DEG
Zdot = 10924.454241 FT/S / N (True) = 321.48173 DEG
Anomalies \ M (Mean) = 321.55535 DEG
Ha = 259.876 NM
Hp = 254.590 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.
POSTED BY RSIMPSON AT VMSPFHOU ON VMSPFHOU.VMBOARDS:PAONEWS