Orbit

Of course, there is the possibility to define the complete initial orbit characteristics (epoch, frame, orbital parameters) using the same [GENOPUS] widget as in [PSIMU], [OPERA] and many other tools.

But GENTLEMAN also get the possibility to define more simply an orbit:

• First, the user will have to select if a LEO or a GEO orbit has to be considered
• Then, selecting “Simple Orbit”, the amount of parameters will be reduced with:

* In case of a LEO, only:

• • • The epoch
    • The perigee altitude
    • The apogee altitude
    • The inclination

By default, the frame will be GCRF, the values for RAAN, argument of perigee and anomaly will be set to zero.

• • In case of a GEO, only:
    • The epoch
    • The delta on the GEO altitude for the perigee altitude
    • The delta on the GEO altitude for the apogee altitude
    • The inclination
    • The longitude

By default, (all parameters set to zero), the orbit will be a GEO one!

Note that there are some checks between the orbit, the vehicle and the forces models characteristics as, for example, to verify that it is not necessary to define an atmospheric model if we are on a GEO.

Note : be careful on the fact that, up to now, due to limitations of PATRIUS algorithms, building a LEO TLE is not possible for a too low eccentricity and a GEO TLE for an epoch before 2005 !