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


Home Page Dundee Satellite Receiving Station Home Page      Send Us A Comment Send Us A Comment