Thermal Analysis of the Solar Orbiter PHI Electronics Unit

Torralbo, Ignacio; Pérez-Grande, Isabel; Gasent-Blesa, J. L.; Piqueras, J.; Sanchis-Kilders, E.; Rodríguez, P.; López, A.J.

doi:10.1109/taes.2019.2911734

Cited by 6 publications

(3 citation statements)

References 17 publications

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“…Since then, the IDR/UPM institute has been very present in the aerospace sector, participating in a significant number of activities and missions. Some examples are the CPLM payload for the MINISAT mission [1], the thermal control of the OSIRIS instrument for ROSETTA [2], the thermal control of the balloon-borne telescope SUNRISE [3], the thermal analysis of the NOMAD payload in ExoMars [4,5], SO/PHI and EPDS in Solar Orbiter [6,7], or the MEDA sensors in Mars 2020 mission [8].…”

Section: Introductionmentioning

confidence: 99%

An example of Space Engineering Education in Spain: a master in space based on Project-Based Learning (PBL)

Cano¹,

Carrión²,

Millán³

et al. 2022

4th Symposium on Space Educational Activities

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This work describes the successful education experience for five years of space engineering education at the Universidad Politécnica de Madrid (UPM), Madrid, Spain. The MSc. in Space Systems (MUSE, Máster Universitario en Sistemas Espaciales) is a 2-year and 120-ECTS (European Credit Transfer and Accumulation System) master program organized by the Microgravity Institute ‘Ignacio Da Riva’ (IDR/UPM), a research institute of UPM with extensive experience in the space sector. The teaching methodology is oriented to Project Based Learning (PBL), taking advantage of the IDR/UPM Institute experience. The main purposes are to share the IDR/UPM knowledge with the students and promote their collaboration with several space scientific institutions, both national and international. In the present work, the most relevant characteristics of this master program are described, highlighting the importance of the student’s participation in actual missions. In addition, to offer practical cases in all aspects of satellite development, the IDR/UPM decided to create its own satellite development program, the UPMSats. The latest, the UPMSat-2, is an educational, scientific, and in-orbit technological demonstration microsatellite (50 kg-class) that was launched in September 2020 on-board a Vega launcher (VV-16 flight). MUSE students have participated in all phases of the mission, from design to integration, calibration, and testing, and (at present) in-orbit operation. The construction of a microsatellite, although it exceeds in time the academic duration of the master, has proven to be a very interesting and versatile tool for PBL education, since it provides practical cases at all levels of development. Furthermore, the continuity of the project encourages graduated students to continue their education with a Ph.D. and the collaboration of master and doctoral students. These reasons have made MUSE one of the most successful academic programs in space systems engineering in Spain, with high employment rates in the most prestigious space engineering institutions

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Section: Introductionmentioning

confidence: 99%

An example of Space Engineering Education in Spain: a master in space based on Project-Based Learning (PBL)

Cano¹,

Carrión²,

Millán³

et al. 2022

4th Symposium on Space Educational Activities

View full text Add to dashboard Cite

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“…A visualization of the error has been added to help understanding the nature of the minimization iterative process and the trajectory followed by the parameters of the model. Although this 4-node TMM may appear to be a non-realistic model, in fact it could represent a real reduced thermal mathematical model of some unit, as is the case of the PHI E-Unit presented in [65]. In addition, this model was used by [36] and showed itself to be good starting point for comparison.…”

Section: Chaptermentioning

confidence: 99%

“…SO/PHI O-Unit con las mantas térmicas instaladas[62].En el diseño de la unidad electrónica[15] también se ha aplicado el método presentado en esta tesis[64,65]. El RTMM de PHI E-Unit se ha ajustado respecto a su respectivo DTMM utilizando el método GIPI propuesto.…”

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Correlation of spacecraft termal mathematical models to reference data

Gimeno¹

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Model-to-test correlation is a frequent problem in spacecraft-thermal control design. The goal of correlation is to determine the values of the parameters of the thermal mathematical model (TMM) that allows reaching a good fit between the TMM results and test data. This way the uncertainty of the mathematical model is reduced. Quite often, this task is performed manually, mainly because a good engineering knowledge and experience is needed to reach a successful compromise, but the use of a mathematical tool could undoubtedly facilitate this work. The correlation process can therefore be considered as the selection of the model parameters that minimize the error of the model results with regard to the reference data. In this doctoral dissertation, a simple method (GIPI) is presented. The method is suitable to solve the TMM-to-test correlation problem, using Jacobian matrix formulation and Moore-Penrose pseudo-inverse, generalized to include several load cases. Aside, in simple cases, this method also allows for analytical solutions to be obtained, which helps to analyze some problems that appear when the Jacobian matrix is singular. To show the implementation of the method, two problems have been considered, one more academic, consisting of a simple 4-node model, and the other one a complex model, the TMM of the optical unit of PHI, one of the remote sensing instruments of the ESA mission Solar Orbiter. The method has given satisfactory reslts in both cases. The convergence of the method has been studied and compared with several methods and the time required by this method (GIPI) subtantially outperforms the other methods.

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