In space environment, satellites have to cope with irradiation of energetic particles (electrons, protons) which can lead to an accumulation of electric charges on devices and insulators and to the initiation of discharges and electric arcs. For several years, these electrostatic phenomena have been suspected of being responsible for a certain number of anomalies observed in flight. Electric discharges produce electromagnetic disturbances which can interfere with electronics, generate errors (Upsets) and seriously damage the most sensitive electronic components. These discharges can significantly degrade the physical properties of materials and lead to irreversible damage to embedded systems.

The objective of this PhD study here is to study the impact of high energy radiations on the electric spacecraft components and characterize the electrostatic discharges on different elements considered "at risk" with regard to this problem (printed circuits, connectors, cables). This study mainly requires experimental and instrumental work supported by physical analysis and numerical simulation activity. Following an initial phase that will consist in identifying, through analysis and/or numerical simulation, the critical space mission profiles with respect to electrostatic discharge risks, the next step will be to define the experimental methods enabling the characterization of electric discharges (duration, amplitude) under electrically representative conditions of in-flight situations.

A specific attention will be paid on the development of instruments allowing the least intrusive measurements possible. We propose to adapt a floating measurement technique implemented as part of a current PhD study and which makes it possible to characterize “surface” electrostatic discharges (occurring on the external skin of the satellite) with a minimal disruption. The next step will consist of creating and integrating the instrumentation on a table test bench then under vacuum and finally under a medium and/or high energy electron beam, which will in turn make it possible to check the performance of the instrumentation then to validate them under conditions representative of space environment.

This experimental phase therefore aims at locating and identifying the discharges produced under irradiation on realistic critical systems. Simple dielectric strength measurements would allow observing any degradation induced by the accumulation of discharges. Finally, we will be interested, in a more prospective manner, in the coupling of these internal electrostatic discharges on electronics on board satellites by instrumenting mock-ups connected to the source object of the discharge. 

This PhD work will thus allow us developing innovative testing methods closely aligned with the challenges of the space sector. It will benefit from the operational feedback of the CROCUS satellite, currently under development at ONERA, and will enable the conceptualization of measurements to be developed for future orbital missions.

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For more Information about the topics and the co-financial partner (found by the lab!); contact Directeur de thèse - Thierry.Paulmier@onera.fr

Then, prepare a resume, a recent transcript and a reference letter from your M2 supervisor/ engineering school director and you will be ready to apply online before March 13th, 2026 Midnight Paris time!