Read e-book online An Introduction to Mission Design for Geostationary PDF

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By J.J. Pocha

ISBN-10: 9400938578

ISBN-13: 9789400938571

ISBN-10: 9401082154

ISBN-13: 9789401082150

` The e-book is a good written and is acceptable for a wide variety of readers from scholars to managers attracted to studying concerning the project layout challenge and research innovations for the geo-synchronous orbit. '
Canadian Aeronautics and area magazine, March 1988

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Extra resources for An Introduction to Mission Design for Geostationary Satellites

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The total width of each of these launch windows shall be 2 hours. 2 To satisfy the above requirements the user must select injection opportunities consistent with the requirements below: • All on-orbit mission operations shall be capable of being performed within a 24-hour period of on-orbit time without conflicting with the performance of routine crew activity during this period. • For launch during at least 80% of each of the appropriate standard launch windows for shared flights, payloads shall be designed such that all orbit/ Sun constraints are satisfied for both ascending and descending equatorial node deployments on the 33rd orbital revolution of the Shuttle.

2. Now if a spacecraft wishes to avoid North-South station-keeping manoeuvres, and still wishes to minimise its orbit inclination over its operational lifetime, it is clear that the orbit pole must initially be placed on the side of the North Pole, remote from the Vernal Equinox. Only then will the orbit inclination first reduce, pass through a minimum, and then increase again. This implies that the initial value of the right ascension of the orbit's ascending node must be in the region of 270 0 .

3 The Launch Event Sequence for MARECS on Ariane Event First Stage Ignition Lift Off Umbilical Eject Start of Pitch Program First Stage Burn Out First Stage Separation Second Stage Full Thrust Fairing Jettison Second Stage Burn Out Second Stage Separation Third Stage Full Thrust Third Stage Cut-Off by Guidance Computer Start of Payload Re-orientation to Nominal AMF Attitude Slow Spin-Up to 10 rpm. accuracy of the launch vehicle. Dispersions in the ascent trajectory of the launch vehicle will result in errors in the transfer orbit parameters.

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


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