The aim of this paper is to study a feedback control system that is able to stabilize the dynamics of a spinning E-sail-based spacecraft around a heliostationary position at a distance of about one astronomical unit from the sun. The analysis is made with a recent mathematical model, which allows the actual tether shape to be accurately described and the thrust and torque vectors to be written in a compact, analytical, form. In this context, the spacecraft attitude motion is investigated, and the effects of a propulsive torque on the rotational stability are discussed with the aid of a linearized approach.
Stability and Control of Spinning Electric Solar Wind Sail in Heliostationary Orbit
bassetto MPrimo
Methodology
;mengali GSecondo
Validation
;quarta a
Ultimo
Conceptualization
2019-01-01
Abstract
The aim of this paper is to study a feedback control system that is able to stabilize the dynamics of a spinning E-sail-based spacecraft around a heliostationary position at a distance of about one astronomical unit from the sun. The analysis is made with a recent mathematical model, which allows the actual tether shape to be accurately described and the thrust and torque vectors to be written in a compact, analytical, form. In this context, the spacecraft attitude motion is investigated, and the effects of a propulsive torque on the rotational stability are discussed with the aid of a linearized approach.File | Dimensione | Formato | |
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[2019] Stability and Control of Spinning Electric Solar Wind Sail in Heliostationary Orbit.pdf
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