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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_013.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-013 (orbit 45) Thursday 9 a.m.
STS-57
1 22684U 93 37 A 93175.38725379 0.00001043 00000-0 30762-4 0 130
2 22684 28.4597 293.8133 0005364 257.1483 102.8513 15.30348357 454
Satellite: STS-57
Catalog number: 22684
Epoch time: 93175.38725379 (24 JUN 93 09:17:38.73 UTC)
Element set: GSFC-013
Inclination: 28.4597 deg
RA of node: 293.8133 deg Space Shuttle Flight STS-57
Eccentricity: 0.0005364 Keplerian Elements
Arg of perigee: 257.1483 deg
Mean anomaly: 102.8513 deg
Mean motion: 15.30348357 rev/day Semi-major Axis: 6852.9042 Km
Decay rate: 0.10E-04 rev/day*2 Apogee Alt: 478.19 Km
Epoch rev: 45 Perigee Alt: 470.84 Km
NOTE - This element set is based on NORAD element set # 013.
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 2 STATE VECTORS
ON ORBIT OPERATIONS
(Posted 06/22/93 by Roger Simpson)
The following vectors for the flight of STS-57 are provided by NASA
Johnson Space Center, Flight Design and Dynamics Division for use in
ground track plotting programs. The first vector represents the
trajectory of Endeavour during on orbit operations. The second vector
represents the trajectory of Eureca prior to rendezvous.
***NOTE***
THE FOLLOWING IS THE SCHEDULE TO BE USED TO UPDATE THE ORBITER VECTOR
BEING POSTED ON THE JSC PAO BULLETIN BOARD:
FLIGHT DAY 3: Wednesday, 2000 GMT, 3:00 p.m. CDT
FLIGHT DAY 4: Thursday, 1600 GMT, 11:00 a.m. CDT (POST RENDEZVOUS)
FLIGHT DAY 5: FRIDAY, 2000 GMT, 3:00 p.m. CDT (Last Vector before Deorb)
Lift off Time : 1993/172/13:07:21.953
Lift off Date : 06/21/93
ORBITER VECTOR
Vector Time (GMT) : 173/18:00:00.000
Vector Time (MET) : 001/04:52:38.047
Orbit Count : 019
Weight : 238283.0 LBS
Drag Coefficient : 2.00
Drag Area : 2750.0 SQ FT
M50 Elements Keplerian Elements
----------------------- --------------------------
X = -14360123.3 FT A = 3682.0413 NM
Y = -13662556.2 FT E = 0.004259
Z = -10523753.0 FT I (M50) = 28.24456 DEG
Xdot = 16626.475407 FT/S Wp (M50) = 54.42324 DEG
Ydot = -18607.136815 FT/S RAAN (M50) = 304.81720 DEG
Zdot = 1625.577968 FT/S / N (True) = 223.30440 DEG
Anomalies \ M (Mean) = 223.63991 DEG
Ha = 253.350 NM
Hp = 218.073 NM
The following is a preliminary maneuver plan for the Orbiter prior to
Eureca rendezvous:
POST BURN
MNVR MET IGN DVX DVY DVZ HA HP
1 001/20:15:48 3.60 0.00 0.00 253.2 220.2
2 001/21:49:12 3.60 0.00 0.00 253.2 222.2
3 002/04:01:52 52.50 0.00 0.00 254.8 252.2
4 002/18:25:28 4.23 0.00 0.00 254.9 254.3
5 002/19:12:30 2.71 0.00 0.00 255.8 254.9
6 002/22:20:43 3.03 -0.15 0.00 257.7 254.9
7 003/01:00:00 GRAPPLE
TARGET VECTOR (NEXT UPDATE WEDNESDAY)
Vector Time (GMT) : 172/16:07:21.953
Vector Time (MET) : 000/03:00:00.000
Orbit Count : 4953
Weight : 8900.0 LBS
Drag Coefficient : 1.40 (Cd)
Drag Area : 305.0 SQ FT
M50 Elements Keplerian Elements
----------------------- --------------------------
X = -2575284.8 FT A = 3704.7291 NM
Y = 21307418.3 FT E = 0.001884
Z = 6648045.2 FT I (M50) = 28.28354 DEG
Xdot = -23274.938175 FT/S Wp (M50) = 131.89307 DEG
Ydot = 87.337678 FT/S RAAN (M50) = 312.03794 DEG
Zdot = -9269.859068 FT/S / N (True) = 9.46570 DEG
Anomalies \ M (Mean) = 9.43024 DEG
Ha = 260.547 NM
Hp = 253.717 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