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1994-04-09
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STS-59 Prelaunch Keplerian Orbital Elements
4/5/94: STS-59 elements (April 8 launch)
STS-59
1 00059U 94098.74878017 .00221188 00000-0 11303-3 0 80
2 00059 57.0053 277.0416 0009259 269.9963 90.0094 16.19806752 54
Satellite: STS-59
Catalog number: 00059
Epoch time: 94098.74878017 = (08 APR 94 17:58:14.61 UTC)
Element set: 008
Inclination: 57.0053 deg
RA of node: 277.0416 deg Space Shuttle Flight STS-59
Eccentricity: .0009259 Prelaunch Element set JSC-008
Arg of perigee: 269.9963 deg Launch: 08 APR 94 12:06 UTC
Mean anomaly: 90.0094 deg
Mean motion: 16.19806752 rev/day G. L. Carman
Decay rate: 2.21188e-03 rev/day~2 NASA Johnson Space Center
Epoch rev: 5
Checksum: 325
G.L.CARMAN
STS-59
FLIGHT DAY ONE STATE VECTORS
NOTE:
Vector postings by NASA, Johnson Space Center, Flight Design and
Dynamics Division will be reduced during the next two to three flights
and eliminated later this year. Vectors may be received via remote
access on the NASA REPORTS AND INFORMATION DISSEMINATION (RAID) REMOTE
BULLETIN BOARD SYSTEM (RBBS). Vector postings on RAID are made every
hour except on weekends. The postings contain 2-line el sets, M-50
cartesian elements, and keplerian elements. The postings by the Flight
Design and Dynamics Division will continue until access to the RAID
bulletin board is available through INTERNET. The following information
details how you get an account and password for RAID:
- Call (301)805-3916
- Ask for a new account and password for NASA REPORTS AND INFORMATION
DISSEMINATION (RAID) REMOTE BULLETIN BOARD SYSTEM (RBBS)
- PROVIDE YOUR NAME/ADDRESS/PHONE NUMBER
STS-59
PREDICTED FLIGHT DAY ONE STATE VECTORS
ON ORBIT OPERATIONS
(Posted 4/07/94 by Roger Simpson)
The following vector for the flight of STS-59 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 nominally scheduled trim
burn.
UPDATE SCHEDULE
DAILY
Lift off Time : 1994/098/12:06:00.000
Lift off Date : 04/98/94
ORBITER VECTOR
Vector Time (GMT) : 098/17:04:38.500
Vector Time (MET) : 000/04:58:38.500
Orbit Count : 004
Weight : 236850.0 LBS
Drag Coefficient : 2.00
Drag Area : 1208.0 SQ FT
M50 Elements Keplerian Elements
----------------------- --------------------------
X = 5121307.8 FT A = 3563.4919 NM
Y = 17966359.0 FT E = 0.000384
Z = 10938419.7 FT I (M50) = 56.76478 DEG
Xdot = -12845.406077 FT/S Wp (M50) = 77.47579 DEG
Ydot = 14018.734872 FT/S RAAN (M50) = 276.65027 DEG
Zdot = -16993.995456 FT/S / N (True) = 65.36157 DEG
Anomalies \ M (Mean) = 65.32153 DEG
Ha = 118.3075 NM
Hp = 118.2540 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.
.
POSTED BY RSIMPSON AT VMSPFHOU ON VMSPFHOU.VMBOARDS:PAONEWS
---
■ Via FTL BBS (404-292-8761) and NASA Spacelink (205-895-0028)