Download An Introduction to Mission Design for Geostationary by J.J. Pocha PDF
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 concerning the undertaking layout challenge and research concepts for the geo-synchronous orbit. '
Canadian Aeronautics and house magazine, March 1988
Read or Download An Introduction to Mission Design for Geostationary Satellites PDF
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Additional resources for An Introduction to Mission Design for Geostationary Satellites
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. lat. 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.
Lat. 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.
JID LLI« ::> 0:: a Z 0 0:: 0 UJ ::s::: 0:: > rr e:( 0:: e:( u 0 z -I e:( :1: m- -~ co_ o co e:( r--e:( r tzl1lm I- 0 ~~~ ~0:: ;~~ 8~ e- mm. 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.