KEYWORDS: Operating systems, Spectroscopy, Data acquisition, Data processing, Telescopes, Infrared spectroscopy, Control systems, Computer architecture, Process control, Data communications
The ARIEL Instrument Control Unit (ICU) implements the monitoring, control, and commanding of both the ARIEL IR Spectrometer (AIRS) and Telescope Control Unit (TCU). It acquires the AIRS scientific data provided by the AIRS detector control units and implements the onboard pre-processing and downlink to the satellite Mass Memory. Based on a preliminary Technical Specification, a high-level preliminary software architecture has been produced. In this paper we provide the ARIEL ICU Application SW layers description and some examples of the static and dynamic diagrams that will be included in the final architecture
PLAnetary Transits and Oscillations of stars (PLATO) is a medium-class mission selected by ESA in the framework of the Cosmic Vision programme. The PLATO Instrument Control ICU is responsible for the management of the scientific payload, the communication with the SVM, and the lossless compression of scientific data before the download to the satellite Mass memory. The ICU requirements have been finalized for the Preliminary Design Review. The resulting technical specification has been used to design a Model Based Software architecture. The first two versions of the PLATO ICU SW have been released and fully validated on the target platform. This paper provides the details of the solutions adopted to cover all implemented services.
PLATO (PLAnetary Transits and Oscillations of stars) is the third medium-class mission (M3), selected by the European Space Agency (ESA) in 2014 and adopted in 2017 for the Cosmic Vision 2015-2025 scientific program. The launch is scheduled in 2026 from the French Guiana (Kourou) for a nominal in-orbit lifetime of 4 years plus up to 4 years of possible extension. The main purpose of the mission is the discovery and preliminary characterization of many different types of exoplanets down to rocky terrestrial planets orbiting around bright solar-type stars. The PLATO spacecraft will operate from a halo orbit around L2 (the Sun-Earth 2nd Lagrangian Point), a virtual point in space, 1.5 million km beyond Earth as seen from the Sun and its Payload will consist of 26 small telescopes (24 normal and 2 fast), pointing at the same target stars, that provide images every 25 seconds with the normal camera and every 2.5 seconds for the two fast cameras, operating in a close loop with the AOCS (S/C Attitude and Orbit Control System). Each camera (consisting of a telescope, the Focal Plane Assembly and its Front-End Electronics) will host four CCDs producing 20.3 megapixels images adding up to 81.4 megapixels per normal camera and 2.11 gigapixels for the overall Payload (P/L). This huge amount of data cannot be transmitted to the ground and need to be processed on-board by the P/L Data Processing System (DPS) made up of various processing electronic units. The DPS of the PLATO instrument comprises the Normal and Fast DPUs (Data Processing Units) and a single ICU (Instrument Control Unit), in charge of HW and SW lossless data compression and managing the P/L through a SpaceWire (SpW) network. In this paper we will review the status of the Instrument Control Unit (ICU) after its Critical Design Review (CDR) process, performed by ESA and PMC (PLATO Mission Consortium), the results of the performance test preliminary run on the Engineering Model (EM), waiting for the following Engineering and Qualification Model (EQM) and Proto-Flight Model (PFM), and the status of the early models development (Engineering Models 1 and 2, Mass and Thermal Dummy - MTD) that, along with the Boot SW (BSW) burning in PROM readiness, will enable the EQM manufacturing.
KEYWORDS: Process control, Data processing, Computer architecture, Control systems, Network architectures, Amplifiers, Operating systems, Space operations
In this paper we describe the activities towards the design of a common framework for the Instrument Control and Data Processing Units for the three scientific payload instruments on board the joint ESA-JAXA SPICA mission, currently at the end of its phase A study. In this context, we started a program to assess modular architectures based on the use of a quad-core fault-tolerant LEON4 SPARC V8 processor on a SpaceWire network. We will describe the results of our initial tests using both Asymmetric Multi processing (AMP) and Symmetric Multi Processing (SMP) configurations. In addition, the possibility to adopt the RTEMS real time operating system, already space qualified on single core processors, will be evaluated both in terms of latency performances and of dynamical allocation of the resources. Finally, we will present the outline of the way forward for the next phases of the SPICA project.
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