Year: 2025
Type: article
Abstract: In this work, a comparison was made between possible detumbling and Sun-pointing attitude controls for the USAT-I 3U CubeSat, considering a magnetic-only control versus a combination between coils and a single reaction wheel. The simulation considered software-in-the-loop simulation using NASA's 42 simulator with ad-hoc control law routines. The result is instrumental in defining the trade-off at the system level, considering the power generation on each case for a class of Sun-synchronous orbits as a function of the orbit local hour. As the satellite orbit is not known in advance, the control must be evaluated along different scenarios, with and without an eclipse, considering a near circular and near polar orbit as typical for LEO launch opportunities. For all these actuator cases the nonlinear system is also time varying and underactuated, hence the stability analysis was made using the averaging theory. This includes a Sun-pointing mode with spin, which makes the mission more feasible under operational constraints. The Sun-pointing error feedback was evaluated using a partial quaternion defined in this context.
Source: Metascience in Aerospace
DOI: 10.3934/mina.2025003
Authors: Elián Hanisch, Pablo Servidia, CONAE - National Commission of Space Activities, Av. Paseo Colón 751, CABA, Argentina
Language: English
Subfield: Aerospace Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: hybrid
OpenAlex ID: W4413307662