Some comments on the TLE problemetic Main point: the TLE are self consistent and need no other...
4
Some comments on the TLE problemetic Main point: the TLE are self consistent and need no other informations The only extrapolation program usable is SGP4 or SDP4 To include the TLE in the “CCSDS world “ there are two faces: the <form < = syntaxe == no problem The <physical content < = semantic difficult (or impossible) to achieve In fact it depends on the accuracy needed and the extrapolation horizon. In any case the SGP4 and SDP4 models are mandatory so they must be well and ‘uniquely ‘ define in my opinion ,the following pictures give the possible interfaces between ‘TLE world’ and ‘CCSDS world’
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Transcript of Some comments on the TLE problemetic Main point: the TLE are self consistent and need no other...
Some comments on the TLE problemetic
Main point: the TLE are self consistent and need no other informationsThe only extrapolation program usable is SGP4 or SDP4
To include the TLE in the “CCSDS world “ there are two faces:
the <form < = syntaxe == no problem
The <physical content < = semantic difficult (or impossible) to achieve In fact it depends on the accuracy needed and the extrapolation horizon.
In any case the SGP4 and SDP4 models are mandatory so they must be well and ‘uniquely ‘ define
in my opinion ,the following pictures give the possible interfaces between ‘TLE world’ and ‘CCSDS world’
Mean orbital elements in TLE format
Extrapolation only with
SGP4 for low earth orbit
SDP4 for deep earh orbit
similar but in an other semantic to the keplerian elements only of OPM
but in mean elements
need only
SGP4 or SDP4
results
osculating elements in Thrue Of Date
Position Velocity
IDENTICAL to the osculating elements only of OPM
FOR OPM WITH AND WITHOUT CHANGES
need to Assume Concsistency with B* parameter and
DRAG_AREA SOLAR_RAD_AREA
DRAG_COEFF SOLAR_RAD_COEFF
INPUT
problem of propagation accuracy
CCSDS WORLD
Mean orbital elements in TLE format
Extrapolation only with
SGP4 for low earth orbit
SDP4 for deep earh orbit
results
osculating elements in Thrue Of Date
Position Velocity
identical to the osculating elements only of OEM
FOR OEM without change
Need to assume Concsistency with B* parameter
and
DRAG_AREA SOLAR_RAD_AREA
DRAG_COEFF SOLAR_RAD_COEFF
CCSDS WORLD
NEW OPM IN
Mean orbital elements in TLE format
OD using ephemeris as measurements only with
SGP4 for low earth orbit
OR
SDP4 for deep earh orbit
results
Kind of mean elements in Thrue Of Date
Position Velocity ( parameter B*…?)
FOR A TLE LIKE OPM OR OEM
Assume Concsistency with B* parameter
and
DRAG_AREA SOLAR_RAD_AREA
DRAG_COEFF SOLAR_RAD_COEFF
INPUT
OSCULATING ELEMENTS
EPHEMERIS GENERATION
NEW OEM IN
Mean orbital elements in TLE format
