The instrument control unit of the PLATO payload: design consolidation following the preliminary design review by ESA

2020 ◽  
Author(s):  
Rosario Cosentino ◽  
Mauro Focardi ◽  
Stefano Pezzuto ◽  
Giovanni Giusi ◽  
Emanuele Galli ◽  
...  
Keyword(s):  
Control Unit ◽  
Preliminary Design ◽  
Design Review ◽  
Instrument Control

scholarly journals ARINC653 Channel Robustness Verification Using LeonViP-MC, a LEON4 Multicore Virtual Platform

Electronics ◽  
2021 ◽  
Vol 10 (10) ◽  
pp. 1179
Author(s):  
Jonatan Sánchez ◽  
Antonio da Silva ◽  
Pablo Parra ◽  
Óscar R. Polo ◽  
Agustín Martínez Hellín ◽  
...  
Keyword(s):  
Fault Tolerance ◽  
Architectural Design ◽  
Fault Injection ◽  
Control Unit ◽  
Tolerance Mechanisms ◽  
Efficient Data ◽  
Instrument Control ◽  
Virtual Platform ◽  
Hardware Platforms ◽  
The University

Multicore hardware platforms are being incorporated into spacecraft on-board systems to achieve faster and more efficient data processing. However, such systems lead to increased complexity in software development and represent a considerable challenge, especially concerning the runtime verification of fault-tolerance requirements. To address the ever-challenging verification of this kind of requirement, we introduce a LEON4 multicore virtual platform called LeonViP-MC. LeonViP-MC is an evolution of a previous development called Leon2ViP, carried out by the Space Research Group of the University of Alcalá (SRG-UAH), which has been successfully used in the development and testing of the flight software of the instrument control unit (ICU) of the energetic particle detector (EPD) on board the Solar Orbiter. This paper describes the LeonViP-MC architectural design decisions oriented towards fault-injection campaigns to verify software fault-tolerance mechanisms. To validate the simulator, we developed an ARINC653 communications channel that incorporates fault-tolerance mechanisms and is currently being used to develop a hypervisor level for the GR740 platform.

The Coronal Solar Magnetism Observatory

2017 ◽  
Vol 13 (S335) ◽  
pp. 359-361 ◽  
Author(s):  
Michael J. Thompson ◽  
Steven Tomczyk ◽  
Sarah E. Gibson ◽  
Scott W. McIntosh ◽  
Enrico Landi
Keyword(s):  
Solar Observatory ◽  
Field Of View ◽  
Preliminary Design ◽  
Research Facility ◽  
Plasma Properties ◽  
Design Review ◽  
Mauna Loa ◽  
Solar Magnetism ◽  
New Facility ◽  
Inner Parts

AbstractThe Coronal Solar Magnetism Observatory (CoSMO) is a proposed new facility led by the High Altitude Observatory and a consortium of partners to measure magnetic field and plasma properties in a large (one degree) field of view extending down to the inner parts of the solar corona. CoSMO is intended as a research facility that will advance the understanding and prediction of space weather. The instrumentation elements of CoSMO are: a white-light coronagraph (KCor), already operational at the Mauna Loa Solar Observatory (MLSO); the Chromosphere and Prominence Magnetometer (ChroMag), due for deployment to MLSO next year; and the CoSMO Large Coronagraph (LC) which has completed Preliminary Design Review.

The instrument control unit of SPICA SAFARI: a macro-unit to host all the digital control functionalities of the spectrometer

2012 ◽  
Author(s):  
Anna Maria Di Giorgio ◽  
David Biondi ◽  
Bortolino Saggin ◽  
Irina Shatalina ◽  
Maurizio Viterbini ◽  
...  
Keyword(s):  
Digital Control ◽  
Control Unit ◽  
Instrument Control

scholarly journals Development of Embedded Boot Software for a Satellite Instrument Control Unit: Lessons Learned

2019 ◽  
Vol 2019 ◽  
pp. 1-8
Author(s):  
Jesús Fernández-Conde ◽  
Jaime Gómez-Saez-de-Tejada ◽  
David Pérez-Lizán ◽  
Rafael Toledo-Moreo
Keyword(s):  
Real Time ◽  
European Space Agency ◽  
Control Unit ◽  
Lessons Learned ◽  
System Failure ◽  
Application Software ◽  
Satellite Mission ◽  
Space Agency ◽  
Expected Performance ◽  
Instrument Control

A satellite spacecraft is generally composed of a central Control and Data Management Unit (CDMU) and several instruments, each one locally controlled by its Instrument Control Unit (ICU). Inside each ICU, the embedded boot software (BSW) is the very first piece of software executed after power-up or reset. The ICU BSW is a nonpatchable, stand-alone, real-time software package that initializes the ICU HW, performs self-tests, and waits for CDMU commands to maintain on-board memory and ultimately start a patchable application software (ASW), which is responsible for execution of the nominal tasks assigned to the ICU (control of the satellite instrument being the most important one). The BSW is a relatively small but critical software item, since an unexpected behaviour can cause or contribute to a system failure resulting in fatal consequences such as the satellite mission loss. The development of this kind of embedded software is special in many senses, primarily due to its criticality, real-time expected performance, and the constrained size of program and data memories. This paper presents the lessons learned in the development and HW/SW integration phases of a satellite ICU BSW designed for a European Space Agency mission.

The instrument control unit of the ESA-PLATO 2.0 mission

2016 ◽  
Author(s):  
M. Focardi ◽  
S. Pezzuto ◽  
R. Cosentino ◽  
G. Giusi ◽  
M. Pancrazzi ◽  
...  
Keyword(s):  
Control Unit ◽  
Instrument Control

Conceptual design of the X-IFU Instrument Control Unit on board the ESA Athena mission

2016 ◽  
Author(s):  
L. Corcione ◽  
S. Ligori ◽  
V. Capobianco ◽  
D. Bonino ◽  
L. Valenziano ◽  
...  
Keyword(s):  
Conceptual Design ◽  
Control Unit ◽  
Instrument Control
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