This document will detail the TAS’s experience with automotive devices in the frame of launcher applications (Ariane-6 & VEGA). Main findings in constructional analysis (more than 90 constructional analysis done), incoming visual and Fischerscope and comparison with “Enhanced Plastic” Parts and Other COTS will be described. Extension of Constructional Analysis Table of ECSS-Q-ST-60-13C for RoHS application (e.g, solderability), and for active parts will be proposed. Experience with Manufacturer support for Reliability Data & PPAP report on AEC devices. Procurement lessons learnt with big suppliers (Arrow, Mouser, Digikey, Avnet, etc..) for traceability, lot homogeneity, packaging, storage, incoming, counterfeit, export license, etc. will be
also described.
Comparison of the different tests & process done between COTS, AECQ, CECC & ESCC qualified products…
Vishay product range on Precision Resistors & Tantalum Capacitors >>>from COTS to ESCC products
This paper will present the assessment of automotive qualified components for Space applications being performed in the frame of ESA Contract 4000126343/19/NL/hh. The proposed work to be performed includes a full thermomechanical and endurance evaluation (2000h life test, 500 cycles -55ºC to +125ºC thermal cycling, HAST or THB) along with constructional analysis and measurements of Tg (glass transition temperature) and outgassing. These tests will be done on three different lots separated by years of lot date codes on three selected AEC-Q candidates (total 9 lots). This testing will allow to confirm manufacturing stability (die mask, assembly techniques, moulding material, etc….) and process variability over time. The three candidates are selected from non-radiation sensitive devices of an “AEC Space PPL” List already compiled from the comparison of what is offered as AEC qualified (AEC QPL list with >200K items) and what is more demanded for Space (Space PPL list from ESCC QPL/QML/PPL, NASA NPSL/GSFC PPL, etc.. with 1500 items).
Eutelsat interest in COTS digital components mainly resides in the possibility to drastically increase processing capabilities while maintain SWaP performance at an affordable level for a commercial GEO Satellite mission.
Whatever the communication mission, whatever the frequency band and associated coverages, the digital processing will bring important benefits in terms of being able to flexibly allocate the spacecraft resource to respond to evolutions of the market needs.
Additionally, more generic payload “building blocks” will permit to lower the procurement time while permitting to decrease industrial cost associated to manufacturing, test, integration on satellite, ranging from one-time programming on ground to full SDR (Software Defined Radio) architectures with full on-board reprogramming!
The radiation environment encountered at high-energy accelerators is composed of a mixed field expected made of charged and neutral hadrons (protons, pions, kaons and neutrons), photons, electrons and muons, ranging from very low (thermal) energies up to the TeV range. Electronic components and systems exposed to a mixed radiation field can suffer from Single Event Effects (SEEs), damage from Total Ionizing Dose (TID) and Displacement Damage (DD).
SmallSats use predominantly commercial electronics and specialized custom miniaturized subsystems out of the primary need to fit volumetric constraints and meet tough power efficiency targets. Using commercial electronics poses a major challenge as the radiation performance of commercial electronics is generally unknown and long-term reliability at elevated temperatures is not guaranteed.
To make matters worse, compressed development schedules and customarily low budgets makes a thorough analysis of each part and circuit impossible. Yet, the combination of educated part selection approaches, part and circuit level mitigations, architectural considerations and operational changes can achieve a high level of reliability even if the individual components don’t meet the typical space grade pedigree. Such mitigation approaches are only cost effective if employed early in the concept and design phase before even minor design changes have the potential to trigger system wide redesigns. For this reason, JPL has developed design and part selection guidelines that reduce the overall part test program.
With the growing consideration of COTS EEE components for space applications, SEE radiation testing will be a challenge. Due to the dense, complex circuits in Flip-Chip, hybrids or plastic packages with Cu bond wires, the opening of such packages is either impossible or difficult, with the risk to modify the device response. This limits the possibility to perform traditional SEE testing with standard heavy ions (<10MeV).
Alternative SEE testing strategies have to be used employing high energy protons or more energetic heavy-ion beams with a proper compromise between LET and range.
The presentation will provide an overview of the use and availability of the testing facilities in Europe offering high energy protons (200 MeV) and heavy-ion beams: ranging from the high energy Heavy Ions (HE) to the Very-High Energy, (VHE) and Ultra-High Energy (UHE).
The European Space Sector can no longer avoid the need to plan and implement a managed transition to lead-free electronics. This stimulus comes from two fronts: Regulatory and Market pressures.
In the Regulatory front while the Space Sector was out of scope of the RoHS Directive, a new front has recently opened with REACH.
The Sector is also subjected to increasing Market pressures. Due to the overall transition of the Electronics Industry worldwide to a Pb-free realm, the Space Industry is more and more confronted with a situation where they cannot avoid using EEE parts with Pb-free coatings, notably COTS, and they need to manage the associated risks