TBUS Messages serve the same purpose as Two-Line Elements, to provide information about the orbit of a spacecraft in order to allow a prediction of its position at some time in the near future.
Dundee software (for example, exelem) utilises PART IV of the message so that is the part described below.
Example:
PART IV 2002 032A 19879 112021040195 060422003017873 2175084 01011370 01011974 00114730 23518073 18531846 09862493 12483725 07187892 M071673887 M006672309 M000000000 M00102198 P01110439 P07356529 002137934 080080010 9449 0000500000 M00305916 P00098070 P00512572 32781012 123105 M01279 041006 M00162 123105 P00001 000000 APT 137.62 MHZ, HRPT 1707.0 MHZ, BCN DSB 137.77 MHZ. APT DAY/NIGHT CH 2,4/3,4. VIS CH 2 /0.725 TO 1.0/ AND IR CH 4 10.3 TO 11.3 XMTD DURING S/C DAY. IR CH 3B/3.55 TO 3.93/ AND IR CH 4 /10.3 TO 11.3/ XMTD DURING S/C NIGHT. DCS CLK YR/DAY/TIME UNKNOWN. LAST TIP CLK CORR 12/31/05.CLK ERR AFTER CORR MINUS 1279 MSEC. CLK ERR AS OF 04/10/06 MINUS 162 MSEC. ERR RATE AS OF 12/31/05 PLUS 1 MS/DAY. NEXT CLK CORRECTION UNKNOWN. DAILY ETCUP WAS SET TO -1.0 MSEC AS OF 4/22/03. NNNN
SpacecraftID(LaunchNumber) Orbit AscendingNodeTime Epoch GreenwichHourAngle
AnomalisticPeriod NodalPeriod Eccentricity Perigee RightAscension Inclination
MeanAnomaly SemiMajorAxis X Y Z
Xvelocity Yvelocity Zvelocity BallisticsCoefficient SolarFlux MeanFlux
MagneticIndex DragModulation RadiationPressure
PerigeeMotion
RightAscensionAscendingNode
MeanAnomalyRate
EquatorCrossingLongitude
TIPClockCorrectionDate
ClockError
For more details see the NOAA KLM Users' Guide
 |
Dundee Satellite Receiving Station Home Page | Send Us A Comment |  |
