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Monster Media 1993 #2
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STS-57
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1993-06-21
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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 JSC-004
STS-57
1 22684U 93 37 A 93172.79471347 .00001893 00000-0 34308-4 0 48
2 22684 28.4605 311.7770 0046761 44.7798 315.6599 15.43599598 59
Satellite: STS-57
Catalog number: 22684
Epoch time: 93172.79471347 = (21 JUN 93 19:04:23.24 UTC)
Element set: 004
Inclination: 28.4605 deg
RA of node: 311.7770 deg Space Shuttle Flight STS-57
Eccentricity: .0046761 Keplerian Element set JSC-004
Arg of perigee: 44.7798 deg from NASA flight Day 1 vector
Mean anomaly: 315.6599 deg
Mean motion: 15.43599598 rev/day G. L. Carman
Decay rate: 1.893e-05 rev/day~2 NASA Johnson Space Center
Epoch rev: 5
Checksum: 348
G.L.CARMAN
STS-57 FLIGHT DAY ONE STATE VECTORS
06/21/93 14:51 MONDAY
STS-57
FLIGHT DAY 1 STATE VECTORS
ON ORBIT OPERATIONS
(Posted 06/21/93 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, after the OMS-2 maneuver. 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 2: Tuesday, 1830 GMT, 1:30 p.m. CDT
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) : 172/18:40:00.000
Vector Time (MET) : 000/05:32:38.047
Orbit Count : 004
Weight : 239178.0 LBS
Drag Coefficient : 2.00
Drag Area : 2750.0 SQ FT
M50 Elements Keplerian Elements
----------------------- --------------------------
X = -15906005.8 FT A = 3680.2832 NM
Y = -11757395.6 FT E = 0.004526
Z = -10590706.4 FT I (M50) = 28.26366 DEG
Xdot = 15309.969715 FT/S Wp (M50) = 43.22441 DEG
Ydot = -19750.301928 FT/S RAAN (M50) = 311.64923 DEG
Zdot = -906.114995 FT/S / N (True) = 222.21199 DEG
Anomalies \ M (Mean) = 222.56136 DEG
Ha = 252.574 NM
Hp = 215.544 NM
The following is a preliminary maneuver plan for the Orbiter prior to
Eureca rendezvous:
POST BURN
MNVR GMT IGN MET IGN DVX DVY DVZ HA HP
1 173/11:36:05 000/22:28:43 3.45 0.00 0.00 252.4 217.7
2 173/16:16:23 001/03:09:02 0.00 -1.08 0.00 252.5 217.6
3 173/17:49:26 001/04:42:04 4.00 0.00 0.00 252.5 219.9
4 174/09:22:57 001/20:15:35 3.60 0.00 0.00 252.4 222.0
5 174/10:56:21 001/21:48:59 3.60 0.00 0.00 252.4 224.0
6 174/17:07:22 002/04:00:00 46.77 0.00 0.84 255.1 249.3
7 174/19:01:05 002/05:53:43 4.00 0.00 0.00 255.1 251.7
8 175/09:07:18 002/19:59:56 4.64 0.00 0.00 255.0 254.3
9 175/09:54:20 002/20:46:58 2.25 0.00 0.00 256.3 254.8
10 175/13:02:33 002/23:55:11 3.02 0.00 0.48 258.0 254.8
11 175/15:00:00 003/02:00:00 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 : 2.00
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,
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