Abstract:
Rigidly linked nanosatellites are simulated as part of a PhD research on a new
concept of space structure. Applications include a 1D interferometer in Earth
and Lagrange orbits and a 3D Solar concentrator in Earth and Moon orbit.
Simulation methods include a link tension derivation based on tether dynamics,
and a simple On-Off constant thrust nanosatellite controller. Results show the
basic controllability of most proposed applications. At system design level, the
controller does not provide adequate lifetime in its current form, but the
concept is in principle feasible.
