An Introduction to Mission Design for Geostationary by J.J. Pocha

By J.J. Pocha

` The ebook is a good written and is appropriate for a wide variety of readers from scholars to managers attracted to studying in regards to the undertaking layout challenge and research options for the geo-synchronous orbit. '
Canadian Aeronautics and area magazine, March 1988

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2 Also to be considered in the optimisation process is the non-nominal performance of the launch vehicle. To allow for transfer orbit dispersions, the optimisation is carried out on a statistical basis, and the spacecraft beginning-of-life (BOL) mass is optimised taking into account non-nominal performances of the launch vehicle and spacecraft propulsion system to some probability level - usually 99%. Let us now see, in a simple way, how small changes in orbit parameters can lead to some increase in spacecraft BOL mass.

Many activities must be performed in a relatively short time, with the spacecraft moving rapidly through the sky. The principal activities that must be performed are: • • • • • • • • tracking and orbit determination, spacecraft telemetry monitoring and check-out, thruster and sensor calibration, appendage deployment, spin-up or spin-down manoeuvres, attitude reorientation, or slew, manoeuvres, orbit adjust manoeuvres, apogee manoeuvre(s). Let us consider each in turn. 1 Tracking and Orbit Determination Information on the transfer orbit characteristics is required early in this phase, and throughout it, to support activities such as slew manoeuvres, orbit adjust manoeuvres, apogee manoeuvre(s), and ground station network control.

Attitude reconstitution requires knowledge of the spacecraft's position with respect to the Earth and the Sun, information which is provided by orbit determination. Manoeuvre design requires a good knowledge of the current orbit, so the spacecraft attitude may be adjusted to achieve the required target orbit. For the apogee manoeuvre, when a solid propellant motor is used, only the direction of thrust may be adjusted; when a liquid propellant motor is used, both the attitude and the firing duration may be adjusted.

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