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Some comments on the TLE problemetic Main point:

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

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Some comments on the TLE problemetic Main point:

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  1. 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’

  2. FOR OPM WITH AND WITHOUT CHANGES INPUT CCSDS WORLD similar but in an other semantic to the keplerian elements onlyof OPM but in mean elements need only SGP4 or SDP4 Mean orbital elements in TLE format Extrapolation only with SGP4 for low earth orbit SDP4 for deep earh orbit IDENTICAL to the osculating elementsonlyof OPM results osculating elements in Thrue Of Date Position Velocity need to Assume Concsistency with B* parameter and DRAG_AREA SOLAR_RAD_AREA DRAG_COEFF SOLAR_RAD_COEFF problem of propagation accuracy

  3. FOR OEM without change CCSDS WORLD Mean orbital elements in TLE format Extrapolation only with SGP4 for low earth orbit SDP4 for deep earh orbit identical to the osculating elements only of OEM results osculating elements in Thrue Of Date Position Velocity Need to assume Concsistency with B* parameter and DRAG_AREA SOLAR_RAD_AREA DRAG_COEFF SOLAR_RAD_COEFF

  4. FOR A TLE LIKE OPM OR OEM INPUT OSCULATING ELEMENTS NEW OPM IN Mean orbital elements in TLE format EPHEMERIS GENERATION NEW OEM 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 Assume Concsistency with B* parameter and DRAG_AREA SOLAR_RAD_AREA DRAG_COEFF SOLAR_RAD_COEFF results Kindof mean elements in Thrue Of Date Position Velocity ( parameter B*…?)

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