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Get 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 ebook is a good written and is appropriate for a wide diversity of readers from scholars to managers attracted to studying in regards to the venture layout challenge and research strategies for the geo-synchronous orbit. '
Canadian Aeronautics and house magazine, March 1988

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Additional info for An Introduction to Mission Design for Geostationary Satellites

Sample text

I~ ~ ~ • 'f; ,.. l;i. t e:( e:( 0 M M_ e:( 0 N N_ e:( 0 LLl O L.. 5 ECS Ground Station Coverage in Transfer Orbit Z in 0:: L. ,UJ UJ Z UJ UJ ..... 5 Other importan t parameters that are evaluated are: • slant range from the ground station to the spacecraft - for TTC link budget calculations; • the rate of change of slant range - to assess the affect of Doppler shift on the TTC link budget. The coverage must be obtained not only for the nominal transfer orbit, but also for the most important "dispersed" cases.

V Az. E!. radius geographic longitude at injection geographic latitude at injection velocity azimuth angle of spin axis elevation angle of spin axis Knowledge of the covariance matrix is required at an early stage in mission design, as it is used to derive the propellant required for the apogee manoeuvre and station acquisition. 5 The information on launch vehicles, required for mission design, is obtained from the launch vehicle User Manuals. Examples of these are cited below. (a) PAM-D/PAM-DII User Requirements Document.

The velocity increment, ~ V, required for inclination change is directly dependent upon the velocity of the spacecraft along the orbit when the manoeuvre is made. It is very much more efficient, therefore, to remove the inclination when the spacecraft is at transfer orbit apogee and travelling slowly, than when the spacecraft is at perigee and travelling very much more quickly. It would seem perverse, therefore, to remove inclination at the perigee of the transfer orbit and indeed only a very small amount of inclination is removed at perigee during injection into GTO.

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

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