This paper presents the trajectory control strategies for the de-orbiting and re-entry phases of a micro satellite equipped with a deployable and controlled aero-brake. They are framed in the design of the Italian space mission MISTRAL (MIcro-SaTellite with Air-Launchable Re-entry capabilities) developed under the supervision of the DAC-Campanian Aerospace District. The proposed control approach makes use of two different control strategies for the de-orbiting and re-entry phases, respectively. The former is based on a linear quadratic optimal control, whereas the latter is based on a model predictive control approach. Numerical simulation results demonstrate the effectiveness of the proposed approach which guarantees a good compromise between stability and performance during the mission phases of interest.

Trajectory control algorithms for the de-orbiting and Re-entry of the MISTRAL satellite

L. Blasi;
2023

Abstract

This paper presents the trajectory control strategies for the de-orbiting and re-entry phases of a micro satellite equipped with a deployable and controlled aero-brake. They are framed in the design of the Italian space mission MISTRAL (MIcro-SaTellite with Air-Launchable Re-entry capabilities) developed under the supervision of the DAC-Campanian Aerospace District. The proposed control approach makes use of two different control strategies for the de-orbiting and re-entry phases, respectively. The former is based on a linear quadratic optimal control, whereas the latter is based on a model predictive control approach. Numerical simulation results demonstrate the effectiveness of the proposed approach which guarantees a good compromise between stability and performance during the mission phases of interest.
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11591/485851
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