Space-based antenna systems for the search of signals from extra-terrestrial intelligence are discussed. Independent studies of the ecliptic solar-sailing transfer problem from the geosynchronous departure orbit to Sun-Earth collinear transterrestrial liberation point were conducted. They were based on a relatively simple mathematical model describing attitude-controlled spacecraft motion in the ecliptic plane as governed by solar and terrestrial gravitational attraction together with the solar radiation pressure. The resulting equations of motion were integrated numerically for a relevant range of values of spacecraft area-to-mass ratio and for an appropriate spacecraft attitude-control law known to lead to Earth escape. Experimentation with varying initial conditions in the departure orbit, and with attitude-control law modification after having achieved Earth escape, established the feasibility of component deployment by means of solar sailing. Details are presented.
Space-Based Seti
1990
5 pages
Report
No indication
English
Astronautics , Spacecraft Trajectories & Flight Mechanics , Antenna design , Extraterrestrial intelligence , Project seti , Solar sails , Spacecraft motion , Geosynchronous orbits , Mathematical models , Attitude control , Collinearity , Ecliptic , Equations of motion , Radiation pressure , Radio signals , Solar radiation , Libration points
NTRS | 1990
|Online Contents | 1999
|British Library Conference Proceedings | 1999
|Online Contents | 1999
|British Library Conference Proceedings | 1999
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