By J.J. Pocha
` The booklet is a good written and is acceptable for a extensive diversity of readers from scholars to managers drawn to studying in regards to the undertaking layout challenge and research recommendations for the geo-synchronous orbit. '
Canadian Aeronautics and area magazine, March 1988
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Additional info for An Introduction to Mission Design for Geostationary Satellites
The monitoring is done automatically, by computers examining the telemetry as it is received, checking that the parameters are within acceptable limits, and flagging and identifying discrepancies when they are detected. Telemetry also enables the control centre to determine the spacecraft's attitude, through the output of its attitude sensors. 3 Thruster and Sensor Calibration To ensure that manoeuvres are performed accurately, the characteristics of the thrusters used must be known accurately.
Accuracy of the launch vehicle. Dispersions in the ascent trajectory of the launch vehicle will result in errors in the transfer orbit parameters. As there is coupling between the elements of the error vector, we have a fully populated error covariance matrix where diagonal terms are the variances of the individual elements. The injection error covariance matrix can be expressed in many forms. For example, the matrix can be expressed in terms of the elements of the transfer orbit: a e i w Q f semi-major axis eccentricity inclination argument of perigee right ascension of ascending node (relative to the Greenwich meridian) true anomaly Or it can be expressed in terms of satellite position and velocity at injection: r long.
All the above constraints are super-imposed and simultaneously satisfied to derive the overall launch window for the satellite. If the launch takes place in conformity with the launch window, a successful launch will result in all the constraints being satisfied as required. 2 Launch Window Derivation The calculation of the launch window depends upon the mission characteristics of the spacecraft. For OTS, for example, there was only one set of nominal transfer orbit parameters, and these were employed in the assessment.
An Introduction to Mission Design for Geostationary Satellites by J.J. Pocha