Download e-book for iPad: An Introduction to Mission Design for Geostationary by J.J. Pocha

By J.J. Pocha

ISBN-10: 9400938578

ISBN-13: 9789400938571

ISBN-10: 9401082154

ISBN-13: 9789401082150

` 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 venture layout challenge and research thoughts for the geo-synchronous orbit. '
Canadian Aeronautics and area magazine, March 1988

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Additional resources for An Introduction to Mission Design for Geostationary Satellites

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The overall launch window is then obtained. 3 When the launch vehicle is the Shuttle, slightly different considerations apply for the launch window. These are outlined briefly here. Unlike conventional launch vehicles, for a Shuttle launch, the time of injection into transfer orbit is not closely tied to the time of launch. This is because there is flexibility in the selection of both deployment time and perigee stage ignition time, once the Shuttle has achieved the near-Earth parking orbit. Injection opportunities will occur every time the parking orbit crosses the Equatorial plane.

If it is within acceptable limits the manoeuvre is complete; if not, further manoeuvres are executed until the desired spin rate is obtained. 4 Ground Station Coverage 43 For example, the first ECS spacecraft was injected into transfer orbit by the Ariane 1 vehicle with a spin rate of 10 rpm. 5 rpm was required. The spin-up manoeuvre was executed in two phases. 5 rpm. The first manoeuvre was executed soon after injection into transfer orbit, while the second was carried out after first apogee passage, and after the execution of the first attitude slew manoeuvre.

1982, "Soviet Launch Vehicles: An Overview", J. 51-58. S. 330-333 and 340. (i) Parfitt, 1. 2, Summer 1986. H. : 1979, "Launch Window for a Shuttle-Based Geosynchronous Orbit Mission", J. 439-441. l Introduction The function of the transfer orbit is to take the spacecraft up to geosynchronous altitude for the purpose of performing the apogee manoeavre. The transfer orbit is the intermediate stage in a Hohman Transfer manoeuvre between the nearEarth, circular, parking orbit and the geosynchronous orbit, and as such, one apse is at parking orbit altitude, while the other is at geosynchronous orbit altitude.

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


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