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Dr. Fabrizio Stesina
Politecnico di Torino, Mechanical and AeroSpace Engineering

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0 Avionics Design
0 Avionics Integration
0 Concurrent Engineering
0 Integration Testing
0 Space Systems

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Journal article
Published: 22 July 2021 in Aerospace
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The release and retrieval of a CubeSat from a big spacecraft is useful for the external inspection and monitoring of the big spacecraft. However, docking maneuvers during the retrieval are challenging since safety constraints and high performance must be achieved, considering the small dimensions and the actual small satellites technology. The trajectory control is crucial to have a soft, accurate, quick, and propellant saving docking. The present paper deals with the design of a tracking model predictive controller (TMPC) tuned to achieve the stringent docking requirements for the retrieval of a CubeSat within the cargo bay of a large cooperative vehicle. The performance of the TMPC is verified using a complex model that includes non-linearities, uncertainties of the CubeSat parameters, and environmental disturbances. Moreover, 300 Monte Carlo runs demonstrate the robustness of the TMPC solution.

ACS Style

Fabrizio Stesina. Tracking Model Predictive Control for Docking Maneuvers of a CubeSat with a Big Spacecraft. Aerospace 2021, 8, 197 .

AMA Style

Fabrizio Stesina. Tracking Model Predictive Control for Docking Maneuvers of a CubeSat with a Big Spacecraft. Aerospace. 2021; 8 (8):197.

Chicago/Turabian Style

Fabrizio Stesina. 2021. "Tracking Model Predictive Control for Docking Maneuvers of a CubeSat with a Big Spacecraft." Aerospace 8, no. 8: 197.

Journal article
Published: 16 November 2020 in Aerospace
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Miniaturized propulsion systems can enable many future CubeSats missions. The advancement of the Technology Readiness Level of this technology passes through the integration in a CubeSat platform and the assessment of the impact and the interactions of the propulsion systems on the actual CubeSat technology and vice versa. The request of power, the thermal environmental, and the electromagnetic emissions generated inside the platform require careful analyses. This paper presents the upgraded design and the validation of a CubeSat test platform (CTP) that can interface a wide range of new miniaturized propulsion systems and gather unprecedented information for these analyses, which can be fused with the commonly used ground support equipment. The CTP features are reported, and the main achievements of the tests are shown, demonstrating the effective capabilities of the platform and how it allows for the investigation of the mutual interactions at system level between propulsion systems and the CubeSat technology.

ACS Style

Fabrizio Stesina; Sabrina Corpino; Daniele Calvi. A Test Platform to Assess the Impact of Miniaturized Propulsion Systems. Aerospace 2020, 7, 163 .

AMA Style

Fabrizio Stesina, Sabrina Corpino, Daniele Calvi. A Test Platform to Assess the Impact of Miniaturized Propulsion Systems. Aerospace. 2020; 7 (11):163.

Chicago/Turabian Style

Fabrizio Stesina; Sabrina Corpino; Daniele Calvi. 2020. "A Test Platform to Assess the Impact of Miniaturized Propulsion Systems." Aerospace 7, no. 11: 163.

Technical note
Published: 01 April 2020 in Aerospace
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Given the role of Cubesats in the new space economy, a statistically relevant number of CubeSats have flown, and considering the high percentage of failed missions, the investigation of in-orbit anomalies becomes of paramount importance. It is rare to find data about mission failures, probably because the partial or total absence of telemetry does not encourage any analysis. The lack of data from the spacecraft in orbit can be mitigated through ad-hoc verification campaigns on satellite models when in-orbit anomalies are experienced. This paper shows an effective testing activity conducted on models of the spacecraft to understand the root cause of a severe anomaly that occurred during mission operations. The tests are part of a comprehensive methodology for root causes analysis. The paper aims at sharing the experience built upon a practical case of interest. More importantly, this work has the ambition of fostering the research on key topics of reliability, mission operations and assembly, and integration and verification/test processes, which have shown to be critical. The activity presented in this paper demonstrates that investigating the anomalies can help recover the mission of interest but can also support building a heritage that is still missing for CubeSat missions today.

ACS Style

Fabrizio Stesina; Sabrina Corpino. Investigation of a CubeSat in Orbit Anomaly through Verification on Ground. Aerospace 2020, 7, 38 .

AMA Style

Fabrizio Stesina, Sabrina Corpino. Investigation of a CubeSat in Orbit Anomaly through Verification on Ground. Aerospace. 2020; 7 (4):38.

Chicago/Turabian Style

Fabrizio Stesina; Sabrina Corpino. 2020. "Investigation of a CubeSat in Orbit Anomaly through Verification on Ground." Aerospace 7, no. 4: 38.

Journal article
Published: 04 September 2019 in Aerospace
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Miniaturized electric propulsion systems are one of the main technologies that could increase interest in CubeSats for future space missions. However, the integration of miniaturized propulsion systems in modern CubeSat platforms presents some issues due to the mutual interactions in terms of power consumption, chemical contamination and generated thermal and electro-magnetic environments. The present paper deals with the validation of a flexible test platform to assess the interaction of propulsion systems with CubeSat-technologies from mechanical, electrical, magnetic, and chemical perspectives. The test platform is a 6U CubeSat hosting an electric propulsion system and able to manage a variety of electric propulsion systems. The platform can regulate and distribute electric power (up to 60 W), exchange data according to several protocols (e.g., CAN bus, UART, I2C, SPI), and provide different mechanical layouts in 4U box completely dedicated to the propulsion system. Moreover, the data gathered by the onboard sensors are combined with the data from external devices and tools providing unprecedented information about the mutual behavior of a CubeSat platform and an electric propulsion system.

ACS Style

Fabrizio Stesina. Validation of a Test Platform to Qualify Miniaturized Electric Propulsion Systems. Aerospace 2019, 6, 99 .

AMA Style

Fabrizio Stesina. Validation of a Test Platform to Qualify Miniaturized Electric Propulsion Systems. Aerospace. 2019; 6 (9):99.

Chicago/Turabian Style

Fabrizio Stesina. 2019. "Validation of a Test Platform to Qualify Miniaturized Electric Propulsion Systems." Aerospace 6, no. 9: 99.

Conference paper
Published: 01 September 2019 in 2019 8th International Workshop on Tracking, Telemetry and Command Systems for Space Applications (TTC)
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This paper deals with the activities led in the framework of [email protected] cubesat mission to decode the downlink telemetry signal, which was affected since launch by a power drop in the order of 20dB with respect to the computed link budget. Despite optimization of the ground station, with installation of higher gain antennas and more performant low noise amplifiers, it was not always possible to directly decode the received signal using existing modems, either hardware or software based. Therefore, a dedicated signal demodulation algorithm was developed and used to post-process all recorded data since launch. The algorithm has been verified and optimized by checking its performance against test data and then it was used to extract useful information from recorded satellite telemetry.

ACS Style

Alberto Busso; Mario Sousa; Marco Mascarello; Fabrizio Stesina. A procedure to recover data of a cubesat mission at very low S/N ratio. 2019 8th International Workshop on Tracking, Telemetry and Command Systems for Space Applications (TTC) 2019, 1 -8.

AMA Style

Alberto Busso, Mario Sousa, Marco Mascarello, Fabrizio Stesina. A procedure to recover data of a cubesat mission at very low S/N ratio. 2019 8th International Workshop on Tracking, Telemetry and Command Systems for Space Applications (TTC). 2019; ():1-8.

Chicago/Turabian Style

Alberto Busso; Mario Sousa; Marco Mascarello; Fabrizio Stesina. 2019. "A procedure to recover data of a cubesat mission at very low S/N ratio." 2019 8th International Workshop on Tracking, Telemetry and Command Systems for Space Applications (TTC) , no. : 1-8.

Journal article
Published: 01 February 2018 in Journal of Guidance, Control, and Dynamics
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Space Debris removal is a critical issue related to space research. One of the key requirements for a removal mission is the assessment of the target rotational dynamics. Ground observations are not sufficient for reaching the accuracy level required to guide the chaser spacecraft during the capture maneuver. Moreover, the guidance and control strategy for the chaser to approach the target is a critical aspect of such missions. This paper presents simulation results of two complementary methods, one for estimating the entire rotational dynamic state of the target and the other for accurately controlling the approach maneuver. In particular, the information coming from the identification and prediction of the actual motion of the tumbling axis of the target is exploited by the second method for aligning the docking interface of the chaser with that axis at the instant of capture. The dynamics estimation is based on Kalman filtering in an original combination with compressive sampling techniques for making the method robust to failures of observation sensors. The guidance of the chaser is based on a model predictive control law. The combined simulation of the employment of the methods has revealed the feasibility of the global approach.

ACS Style

Sabrina Corpino; Stefano Mauro; Stefano Pastorelli; Fabrizio Stesina; Gabriele Biondi; Loris Franchi; Tharek Mohtar. Control of a Noncooperative Approach Maneuver Based on Debris Dynamics Feedback. Journal of Guidance, Control, and Dynamics 2018, 41, 431 -448.

AMA Style

Sabrina Corpino, Stefano Mauro, Stefano Pastorelli, Fabrizio Stesina, Gabriele Biondi, Loris Franchi, Tharek Mohtar. Control of a Noncooperative Approach Maneuver Based on Debris Dynamics Feedback. Journal of Guidance, Control, and Dynamics. 2018; 41 (2):431-448.

Chicago/Turabian Style

Sabrina Corpino; Stefano Mauro; Stefano Pastorelli; Fabrizio Stesina; Gabriele Biondi; Loris Franchi; Tharek Mohtar. 2018. "Control of a Noncooperative Approach Maneuver Based on Debris Dynamics Feedback." Journal of Guidance, Control, and Dynamics 41, no. 2: 431-448.

Journal article
Published: 30 April 2017 in International Review of Aerospace Engineering (IREASE)
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ACS Style

Fabrizio Stesina; Sabrina Corpino; Lorenzo Feruglio. An In-The-Loop Simulator for the Verification of Small Space Platforms. International Review of Aerospace Engineering (IREASE) 2017, 10, 50 .

AMA Style

Fabrizio Stesina, Sabrina Corpino, Lorenzo Feruglio. An In-The-Loop Simulator for the Verification of Small Space Platforms. International Review of Aerospace Engineering (IREASE). 2017; 10 (2):50.

Chicago/Turabian Style

Fabrizio Stesina; Sabrina Corpino; Lorenzo Feruglio. 2017. "An In-The-Loop Simulator for the Verification of Small Space Platforms." International Review of Aerospace Engineering (IREASE) 10, no. 2: 50.

Journal article
Published: 01 November 2016 in Acta Astronautica
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The paper deals with the conceptual design of a space tug to be used in support to Earth satellites transfer manoeuvres. Usually Earth satellites are released in a non-definitive low orbit, depending on the adopted launcher, and they need to be equipped with an adequate propulsion system able to perform the transfer to their final operational location. In order to reduce the mass at launch of the satellite system, an element pre-deployed on orbit, i.e. the space tug, can be exploited to perform the transfer manoeuvres; this allows simplifying the propulsion requirements for the satellite, with a consequent decrease of mass and volume, in favour of larger payloads. The space tug here presented is conceived to be used for the transfer of a few satellites from low to high orbits, and vice versa, if needed. To support these manoeuvres, dedicated refuelling operations are envisaged. The paper starts from on overview of the mission scenario, the concept of operations and the related architecture elements. Then it focuses on the detailed definition of the space tug, from the requirements' assessment up to the budgets' development, through an iterative and recursive design process. The overall mission scenario has been derived from a set of trade-off analyses that have been performed to choose the mission architecture and operations that better satisfy stakeholder expectations: the most important features of these analyses and their results are described within the paper. Eventually, in the last part of the work main conclusions are drawn on the selected mission scenario and space tug and further utilizations of this innovative system in the frame of future space exploration are discussed. Specifically, an enhanced version of the space tug that has been described in the paper could be used to support on orbit assembly of large spacecraft for distant and long exploration missions. The Space Tug development is an activity carried on in the frame of the SAPERE project (Space Advanced Project Excellence in Research and Enterprise), supported by Italian Ministry of Research and University (MIUR), and specifically in its STRONG sub-project (Systems Technology and Research National Global Operations) and related to the theme of space exploration and access to spac

ACS Style

Sara Cresto Aleina; Nicole Viola; Fabrizio Stesina; Maria Antonietta Viscio; Simona Ferraris. Reusable space tug concept and mission. Acta Astronautica 2016, 128, 21 -32.

AMA Style

Sara Cresto Aleina, Nicole Viola, Fabrizio Stesina, Maria Antonietta Viscio, Simona Ferraris. Reusable space tug concept and mission. Acta Astronautica. 2016; 128 ():21-32.

Chicago/Turabian Style

Sara Cresto Aleina; Nicole Viola; Fabrizio Stesina; Maria Antonietta Viscio; Simona Ferraris. 2016. "Reusable space tug concept and mission." Acta Astronautica 128, no. : 21-32.

Journal article
Published: 11 December 2014 in IEEE Transactions on Aerospace and Electronic Systems
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This paper describes the hardware-in-the-loop (HIL) simulation methodology used for the verification of functional requirements of e-st @r-I CubeSat. The satellite's behavior is investigated via HIL simulation, and the results obtained are consistent with the expected values in any operative conditions. It is proven that HIL simulation is a valuable means for supporting the verification process of small satellites and may help reduce the time and cost of the development phase and increase mission reliability.

ACS Style

Sabrina Corpino; Fabrizio Stesina. Verification of a CubeSat via hardware-in-the-loop simulation. IEEE Transactions on Aerospace and Electronic Systems 2014, 50, 2807 -2818.

AMA Style

Sabrina Corpino, Fabrizio Stesina. Verification of a CubeSat via hardware-in-the-loop simulation. IEEE Transactions on Aerospace and Electronic Systems. 2014; 50 (4):2807-2818.

Chicago/Turabian Style

Sabrina Corpino; Fabrizio Stesina. 2014. "Verification of a CubeSat via hardware-in-the-loop simulation." IEEE Transactions on Aerospace and Electronic Systems 50, no. 4: 2807-2818.

Journal article
Published: 01 November 2014 in Acta Astronautica
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ACS Style

Maria Antonietta Viscio; Nicole Viola; Sabrina Corpino; Fabrizio Stesina; Silvano Fineschi; Federico Fumenti; Christian Circi. Interplanetary CubeSats system for space weather evaluations and technology demonstration. Acta Astronautica 2014, 104, 516 -525.

AMA Style

Maria Antonietta Viscio, Nicole Viola, Sabrina Corpino, Fabrizio Stesina, Silvano Fineschi, Federico Fumenti, Christian Circi. Interplanetary CubeSats system for space weather evaluations and technology demonstration. Acta Astronautica. 2014; 104 (2):516-525.

Chicago/Turabian Style

Maria Antonietta Viscio; Nicole Viola; Sabrina Corpino; Fabrizio Stesina; Silvano Fineschi; Federico Fumenti; Christian Circi. 2014. "Interplanetary CubeSats system for space weather evaluations and technology demonstration." Acta Astronautica 104, no. 2: 516-525.

Conference paper
Published: 16 May 2005 in AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference
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The present paper deals with the feasibility study of an orbital and re-entry mission of a Very Low Cost hYpersonic Demonstrator (VeLCHyD), considering a low Earth orbit (about 600 km of altitude) and an affordable demonstrator, characterised by reduced size and weight. The launcher, that has been taken into account for the mission, is Dnepr, operated by Kosmotras. The onboard systems have been defined to let VeLCHyD able to perform the re-entry trajectory to allow for safe re-entry and for approaching the correct landing site. VeLCHyD structural layout have been designed to guarantee the capability of carrying reentry loads. VeLCHyD external configuration is quite simple and thus cheap to be manufactured. As the results of the feasibility study seem to be good, we believe that a new activity, characterised by a favourable benefit to cost ratio, could start

ACS Style

Sergio Chiesa; Sabrina Corpino; Krzysztof Plucinski; Fabrizio Stesina; Nicole Viola. VeLChYD - Very Low Cost Hypersonic Demonstrator for a Complete Orbital Reentry Mission. AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference 2005, 1 .

AMA Style

Sergio Chiesa, Sabrina Corpino, Krzysztof Plucinski, Fabrizio Stesina, Nicole Viola. VeLChYD - Very Low Cost Hypersonic Demonstrator for a Complete Orbital Reentry Mission. AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference. 2005; ():1.

Chicago/Turabian Style

Sergio Chiesa; Sabrina Corpino; Krzysztof Plucinski; Fabrizio Stesina; Nicole Viola. 2005. "VeLChYD - Very Low Cost Hypersonic Demonstrator for a Complete Orbital Reentry Mission." AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference , no. : 1.

Thesis
Published: 01 September 2021
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ACS Style

Fabrizio Stesina. Design and verification of Guidance, Navigation and Control systems for space applications. 2021, 1 .

AMA Style

Fabrizio Stesina. Design and verification of Guidance, Navigation and Control systems for space applications. . 2021; ():1.

Chicago/Turabian Style

Fabrizio Stesina. 2021. "Design and verification of Guidance, Navigation and Control systems for space applications." , no. : 1.