By J.J. Pocha
` The publication is a good written and is appropriate for a extensive variety of readers from scholars to managers attracted to studying in regards to the project layout challenge and research ideas for the geo-synchronous orbit. '
Canadian Aeronautics and house magazine, March 1988
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Extra resources for An Introduction to Mission Design for Geostationary Satellites
We consider now the case of the multi-burn apogee engine firing (AEF) strategy. The differences from the solid motor case are somewhat greater. Here the apogee manoeuvre algorithm is completely different. 2, and this section should be read, before proceeding further, to obtain an understanding of the reasoning behind such a strategy. Once a multi-burn strategy has been selected with due regard to operational constraints, it is used within the transfer orbit optimisation analysis. This varies the transfer orbit's apogee height, inclination and argument of perigee with a view to maximising the spacecraft mass on-station.
The largest dispersion caused by non-nominal vehicle performance is on apogee height. It is, therefore, this parameter that is the subject of the optimisation. Clearly, this adds a further factor to the apogee biasing discussed earlier. 2 Optimising the Transfer Orbit for a Free-Drift Mission Some geostationary spacecraft do not require to be kept within tight latitude limits, though, in order to avoid interference with other spacecraft, tight longitude limits must still be observed. As the latitude deadband is wide, it may be possible to avoid North-South station-keeping altogether, but if this is to be the case, the orientation of the orbit plane at the start of the spacecraft's useful life on station must be carefully set up.
5 ECS Ground Station Coverage in Transfer Orbit Z in 0:: L. ,UJ UJ Z UJ UJ ..... 5 Other importan t parameters that are evaluated are: • slant range from the ground station to the spacecraft - for TTC link budget calculations; • the rate of change of slant range - to assess the affect of Doppler shift on the TTC link budget. The coverage must be obtained not only for the nominal transfer orbit, but also for the most important "dispersed" cases. The orbit dispersion having the greatest effect upon coverage is the apogee height.