NetSat—Challenges and lessons learned of a formation of 4 nano-satellites

Scharnagl, Julian; Haber, Roland; Dombrovski, Veaceslav; Schilling, Klaus

doi:10.1016/j.actaastro.2022.09.036

Cited by 12 publications

(2 citation statements)

References 11 publications

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“…Exploiting solar panels and photodiodes, this work achieved an estimation accuracy in the order of 10 deg. Similar conclusions are also possible analyzing the mission results of the NetSat satellites, whose overview is summarized in the work of Scharnagl [20].…”

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confidence: 56%

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

Colagrossi

Lavagna

Bertacin

2023

Sensors

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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 (1σa) and the orbital position knowledge within 10 m (1σo). 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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confidence: 56%

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

Colagrossi

Lavagna

Bertacin

2023

Sensors

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“…Formation satellites, consisting of multiple satellites, are widely used in the fields of communication, remote sensing, navigation, and reconnaissance [1]. To accomplish specific tasks, formation satellites regularly require the reconfiguration of their relative trajectories or positions.…”

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confidence: 99%

Study on trajectory optimization of satellite rapid orbit formation flying for space object

He,

Chen,

Liu

2024

J. Phys.: Conf. Ser.

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This paper proposes a method of collaborative trajectory planning that utilizes convex optimization and IFPSO to tackle the issue of rapid formation reconstruction by multiple satellites in a low Earth circular orbit. The trajectory optimisation in this study uses convex optimisation and takes into account thrust limitations and safety distance. The time optimal solution is replaced by the path optimal solution, resulting in a suboptimal solution. The time-suboptimal trajectory solving method for formation flying using the CVX software is designed. The IFPSO is used to allocate configurations and waypoints for formation reconstruction, with the aim of balancing fuel consumption across the fleet and reducing the overall fuel consumption of the satellite. The effectiveness of the proposed approach is confirmed by numerical simulation. Despite sacrificing some computational efficiency, the method offered can solve the issues of configuration allocation and trajectory optimization.

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Advanced test environment for automated attitude control testing of fully integrated CubeSats on system level

Ruf,

von Arnim,

Kempf

et al. 2023

CEAS Space J

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NetSat—Challenges and lessons learned of a formation of 4 nano-satellites

Cited by 12 publications

References 11 publications

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

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

Study on trajectory optimization of satellite rapid orbit formation flying for space object

Advanced test environment for automated attitude control testing of fully integrated CubeSats on system level

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