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An Effective Sensor Architecture for Full-Attitude Determination in the HERMES Nano-Satellites

The High Energy Rapid Modular Ensemble of Satellites (HERMES) is a constellation of 3U nano-satellites for high energy astrophysics. The HERMES nano-satellites’ components have been designed, verified, and tested to detect and localize energetic astrophysical transients, such as short gamma-ray burs...

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Autores principales: Colagrossi, Andrea, Lavagna, Michèle, Bertacin, Roberto
Formato: Online Artículo Texto
Lenguaje:English
Publicado: MDPI 2023
Materias:
Acceso en línea:https://www.ncbi.nlm.nih.gov/pmc/articles/PMC10007507/
https://www.ncbi.nlm.nih.gov/pubmed/36904596
http://dx.doi.org/10.3390/s23052393
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author Colagrossi, Andrea
Lavagna, Michèle
Bertacin, Roberto
author_facet Colagrossi, Andrea
Lavagna, Michèle
Bertacin, Roberto
author_sort Colagrossi, Andrea
collection PubMed
description The High Energy Rapid Modular Ensemble of Satellites (HERMES) is a constellation of 3U nano-satellites for high energy astrophysics. The HERMES nano-satellites’ components have been designed, verified, and tested to detect and localize energetic astrophysical transients, such as short gamma-ray bursts (GRBs), which are the electromagnetic counterparts of gravitational wave events, thanks to novel miniaturized detectors sensitive to X-rays and gamma-rays. The space segment is composed of a constellation of CubeSats in low-Earth orbit (LEO), ensuring an accurate transient localization in a field of view of several steradians exploiting the triangulation technique. To achieve this goal, guaranteeing a solid support to future multi-messenger astrophysics, HERMES shall determine its attitude and orbital states with stringent requirements. The scientific measurements bind the attitude knowledge within 1 deg ([Formula: see text]) and the orbital position knowledge within 10 m ([Formula: see text]). These performances shall be reached considering the mass, volume, power, and computation constraints of a 3U nano-satellite platform. Thus, an effective sensor architecture for full-attitude determination was developed for the HERMES nano-satellites. The paper describes the hardware typologies and specifications, the configuration on the spacecraft, and the software elements to process the sensors’ data to estimate the full-attitude and orbital states in such a complex nano-satellite mission. The aim of this study was to fully characterize the proposed sensor architecture, highlighting the available attitude and orbit determination performance and discussing the calibration and determination functions to be implemented on-board. The presented results derived from model-in-the-loop (MIL) and hardware-in-the-loop (HIL) verification and testing activities and can serve as useful resources and a benchmark for future nano-satellite missions.
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spelling pubmed-100075072023-03-12 An Effective Sensor Architecture for Full-Attitude Determination in the HERMES Nano-Satellites Colagrossi, Andrea Lavagna, Michèle Bertacin, Roberto Sensors (Basel) Article The High Energy Rapid Modular Ensemble of Satellites (HERMES) is a constellation of 3U nano-satellites for high energy astrophysics. The HERMES nano-satellites’ components have been designed, verified, and tested to detect and localize energetic astrophysical transients, such as short gamma-ray bursts (GRBs), which are the electromagnetic counterparts of gravitational wave events, thanks to novel miniaturized detectors sensitive to X-rays and gamma-rays. The space segment is composed of a constellation of CubeSats in low-Earth orbit (LEO), ensuring an accurate transient localization in a field of view of several steradians exploiting the triangulation technique. To achieve this goal, guaranteeing a solid support to future multi-messenger astrophysics, HERMES shall determine its attitude and orbital states with stringent requirements. The scientific measurements bind the attitude knowledge within 1 deg ([Formula: see text]) and the orbital position knowledge within 10 m ([Formula: see text]). These performances shall be reached considering the mass, volume, power, and computation constraints of a 3U nano-satellite platform. Thus, an effective sensor architecture for full-attitude determination was developed for the HERMES nano-satellites. The paper describes the hardware typologies and specifications, the configuration on the spacecraft, and the software elements to process the sensors’ data to estimate the full-attitude and orbital states in such a complex nano-satellite mission. The aim of this study was to fully characterize the proposed sensor architecture, highlighting the available attitude and orbit determination performance and discussing the calibration and determination functions to be implemented on-board. The presented results derived from model-in-the-loop (MIL) and hardware-in-the-loop (HIL) verification and testing activities and can serve as useful resources and a benchmark for future nano-satellite missions. MDPI 2023-02-21 /pmc/articles/PMC10007507/ /pubmed/36904596 http://dx.doi.org/10.3390/s23052393 Text en © 2023 by the authors. https://creativecommons.org/licenses/by/4.0/Licensee MDPI, Basel, Switzerland. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license (https://creativecommons.org/licenses/by/4.0/).
spellingShingle Article
Colagrossi, Andrea
Lavagna, Michèle
Bertacin, Roberto
An Effective Sensor Architecture for Full-Attitude Determination in the HERMES Nano-Satellites
title An Effective Sensor Architecture for Full-Attitude Determination in the HERMES Nano-Satellites
title_full An Effective Sensor Architecture for Full-Attitude Determination in the HERMES Nano-Satellites
title_fullStr An Effective Sensor Architecture for Full-Attitude Determination in the HERMES Nano-Satellites
title_full_unstemmed An Effective Sensor Architecture for Full-Attitude Determination in the HERMES Nano-Satellites
title_short An Effective Sensor Architecture for Full-Attitude Determination in the HERMES Nano-Satellites
title_sort effective sensor architecture for full-attitude determination in the hermes nano-satellites
topic Article
url https://www.ncbi.nlm.nih.gov/pmc/articles/PMC10007507/
https://www.ncbi.nlm.nih.gov/pubmed/36904596
http://dx.doi.org/10.3390/s23052393
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