By J.J. Pocha
` The ebook is a good written and is acceptable for a large variety of readers from scholars to managers drawn to studying concerning the challenge layout challenge and research concepts 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
Example text
Analysis has shown that a node-shift capability of about ±80 0 is usually required to satisfy launch window requirements. The node-shifting manoeuvres are carried out either by the apogee motor or by the satellite's reaction control system, or by a combination of the two. For node-shifting to be performed efficiently, the elements of the transfer orbit must be selected to suit the node-shift required. The transfer orbit elements are, however, achieved by the guidance program stored in the launcher's guidance system, and it is totally impractical to provide for a different program for each node-shift in the range -80 0 to +80 0 .
Calibration is achieved by commanding the thruster to execute a manoeuvre which is observable on the ground. Comparison of thruster action time with known initial and final states allows its delivered total impulse to be determined. This information is then used in the design of other manoeuvres performed by that thruster. Sensor calibration serves a similar purpose. If gyros are used in transfer orbit for the control of a three-axis stabilised spacecraft, initialisation, drift-rate estimation, and scale factor estimation are all performed in orbit, with the necessary support from the ground network.
At apogee, five and a quarter hours after injection into transfer orbit. To enable the manoeuvre to be planned and executed in a timely fashion requires that the decision to implement it be made in an hour or two after injection. The ground network, therefore, has about two hours or less to track the spacecraft and determine the orbit elements. Great accuracy is not required, and it suffices to know the perigee height to within about ±5 km. 5 Orbit Determination Requirements 49 Perigee ralsll1g manoeuvres are more likely to be required with expendable launch vehicles than with the Shuttle for two reasons.