Io volcano observer (IVO) integrated approach to optimizing system design for radiation challenges

Adams, Elena; Hibbard, Kenneth; Turtle, Elizabeth; Reynolds, Edward; Anderson, Brian; Paranicas, Chris; Rogers, Gabe; McAdams, James; Roth, David; Christensen, Phil; McEwen, Alfred; Wieser, Martin; Thomas, Nicolas; Wurz, Peter; Janesick, James (2012). Io volcano observer (IVO) integrated approach to optimizing system design for radiation challenges. In: IEEE Aerospace Conference Proceedings (pp. 1-13). IEEE 10.1109/AERO.2012.6187177

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One of the major challenges for a mission to the Jovian system is the radiation tolerance of the spacecraft (S/C) and the payload. Moreover, being able to achieve science observations with high signal to noise ratios (SNR), while passing through the high flux radiation zones, requires additional ingenuity on the part of the instrument provider. Consequently, the radiation mitigation is closely intertwined with the payload, spacecraft and trajectory design, and requires a systems-level approach. This paper presents a design for the Io Volcano Observer (IVO), a Discovery mission concept that makes multiple close encounters with Io while orbiting Jupiter. The mission aims to answer key outstanding questions about Io, especially the nature of its intense active volcanism and the internal processes that drive it. The payload includes narrow-angle and wide-angle cameras (NAC and WAC), dual fluxgate magnetometers (FGM), a thermal mapper (ThM), dual ion and neutral mass spectrometers (INMS), and dual plasma ion analyzers (PIA). The radiation mitigation is implemented by drawing upon experiences from designs and studies for missions such as the Radiation Belt Storm Probes (RBSP) and Jupiter Europa Orbiter (JEO). At the core of the radiation mitigation is IVO's inclined and highly elliptical orbit, which leads to rapid passes through the most intense radiation near Io, minimizing the total ionizing dose (177 krads behind 100 mils of Aluminum with radiation design margin (RDM) of 2 after 7 encounters). The payload and the spacecraft are designed specifically to accommodate the fast flyby velocities (e.g. the spacecraft is radioisotope powered, remaining small and agile without any flexible appendages). The science instruments, which collect the majority of the high-priority data when close to Io and thus near the peak flux, also have to mitigate transient noise in their detectors. The cameras use a combination of shielding and CMOS detectors with extremely fast readout to mi- imize noise. INMS microchannel plate detectors and PIA channel electron multipliers require additional shielding. The FGM is not sensitive to noise induced by energetic particles and the ThM microbolometer detector is nearly insensitive. Detailed SNR calculations are presented. To facilitate targeting agility, all of the spacecraft components are shielded separately since this approach is more mass efficient than using a radiation vault. IVO uses proven radiation-hardened parts (rated at 100 krad behind equivalent shielding of 280 mils of Aluminum with RDM of 2) and is expected to have ample mass margin to increase shielding if needed.

Item Type:

Conference or Workshop Item (Paper)

Division/Institute:

08 Faculty of Science > Physics Institute > Space Research and Planetary Sciences

UniBE Contributor:

Thomas, Nicolas and Wurz, Peter

Subjects:

500 Science > 520 Astronomy
600 Technology > 620 Engineering

ISSN:

1095-323X

ISBN:

978-1-4577-0556-4

Publisher:

IEEE

Language:

English

Submitter:

Factscience Import

Date Deposited:

04 Oct 2013 14:44

Last Modified:

08 Jun 2016 10:38

Publisher DOI:

10.1109/AERO.2012.6187177

BORIS DOI:

10.7892/boris.18138

URI:

https://boris.unibe.ch/id/eprint/18138 (FactScience: 226001)

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