This study presents verification and validation methods for the power supply system of the Fine Guidance System experiment of the ARIEL satellite. Risk and reliability analyses were performed to assess the safety of the design. These include Derating alongside Part Stress Analysis, Worst Case Analysis and Failure Mode and Effects Analysis. Based on the results, recommendations for the power supply design are presented. Moreover, an active load compliant with the SpaceVPX standard was designed to efficiently verify the power supply. The proposed test system design is characterised by low cost, small dimensions and high accuracy. The required electronic modules were designed and tested, with the results discussed. Possibilities for further automation of test procedures and improvement of flaws and shortcomings in the developed electronic equipment are also discussed.
KEYWORDS: Field programmable gate arrays, Electronics, Data processing, Power supplies, Image processing, Infrared imaging, Space telescopes, Exoplanets, Infrared spectroscopy, Photometry
ARIEL is an ESA mission whose scientific goal is to investigate exoplanetary atmospheres. The payload is composed by two instruments: AIRS (ARIEL IR Spectrometer) and FGS (Fine Guidance System). The FGS detection chain is composed by two HgCdTe detectors and by the cold Front End Electronics (SIDECAR), kept at cryogenic temperatures, interfacing with the F-DCU (FGS Detector Control Unit) boards that we will describe thoroughly in this paper. The F-DCU are situated in the warm side of the payload in a box called FCU (FGS Control Unit) and contribute to the FGS VIS/NIR imaging and NIR spectroscopy. The F-DCU performs several tasks: drives the detectors, processes science data and housekeeping telemetries, manages the commands exchange between the FGS/DPU (Data Processing Unit) and the SIDECARs and provides high quality voltages to the detectors. This paper reports the F-DCU status, describing its architecture, the operation and the activities, past and future necessary for its development.
Within this paper, we describe architecture and functionality of the Fine Guidance Sensor (FGS), one of two instruments on-board ESA ARIEL mission. We present a conceptual design, development models, related challenges, and opportunities as seen at iPDR milestone.
The objective of this paper is to present a design of Data Processing Unit (DPU) and Power Supply Subsystem (PSU) that are designed in the frame of SWI instrument developed for ESA JUICE L-class mission. The DPU is a main controller of the instrument, providing a communication link with the spacecraft and several interfaces towards subsystems. The PSU consists of three units: Switch and House-Keeping, BIAS and DCDC providing essentially the power to SWI subsystems. The presented concept is a result of the design presented for the subsystems and instrument CDR.
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