[paper] Radiation testing of a 6-axis MEMS inertial navigation unit

Radiation testing of a commercial 6-axis MEMS inertial navigation unit at ENEA Frascati proton linear accelerator

G. Bazzano^a,b, A. Ampollini^a, F. Cardelli^a, F. Fortini^a, P. Nenzi^a, G.B. Palmerini^b, L. Picardi^a, 

L. Piersanti^a, C. Ronsivalle^a, V. Surrenti^a, E. Trinca^a, M. Vadrucci^a, M. Sabatini^c

Advances in Space Research (2020)

DOI: 10.1016/j.asr.2020.11.031

^aENEA, Via Enrico Fermi 45, Frascati, Italy

^bScuola di Ingegneria Aerospaziale, La Sapienza Università di Roma, Italy

^cDipartimento di Ingegneria Astronautica, Elettrica ed Energetica, La Sapienza Università di Roma, Italy 

Abstract: We present the first results of a novel collaboration activity between ENEA Frascati Particle Accelerator Laboratory and University La Sapienza Guidance and Navigation Laboratory in the field of Radiation Hardness Assurance (RHA) for space applications. The aim of this research is twofold: (a) demonstrating the possibility to use the TOP-IMPLART proton accelerator for radiation hardness assurance testing, developing ad hoc dosimetric and operational procedures for RHA irradiations; (b) investigating system level radiation testing strategies for Commercial Off The Shelf (COTS) components of interest for SmallSats space missions, with focus on devices and sensors of interest for guidance, navigation and control, through simultaneous exploration of Total Ionizing Dose (TID), Displacement Damage (DD) dose and Single-Event Effects (SEE) with proton beams. A commercial 6-axis integrated Micro Electro-Mechanical Systems (MEMS) inertial navigation system (accelerometer, gyroscope) was selected as first Device Under Test (DUT). The results of experimental tests aimed to define an operational procedure and the characterization of radiation effects on the component are reported, highlighting the consequence of the device performance degradation in terms of the overall navigation system accuracy. Doses up to 50 krad(Si) were probed and cross sections for Single-Event Functional Interrupt (SEFI) evaluated at a proton energy of 30 MeV. 

Fig: Polyedric support for MEMS accelerometer characterization