Design and development of the PRIMAger instrument for PRIMA

Abstract

PRIMA (PRobe far-Infrared Mission for Astrophysics) is an infrared space observatory designed to operate over the next decade. Equipped with a 1.8 m telescope actively cooled to 4.5 K, the project is currently in the concept study phase as part of the NASA Probe Explorers program. PRIMA will carry two instruments: FIRESS and PRIMAger. PRIMAger will offer two observation modes: hyperspectral imaging and polarimetric imaging. Both channels will use ultra-sensitive kinetic inductance detector (KID) arrays, covering wavelengths from mid-infrared to far-infrared. A European consortium will develop the cold unit of the PRIMAger instrument while the Readout Electronics and Continuous Adiabatic Demagnetization Refrigerator (CADR) will be provided by Goddard Space Flight Center (GSFC) and shared between the 2 instruments. The hyperspectral mode will cover the 24-84 μm range with a spectral resolution of R ≥ 8, ensured by a linear variable filter placed in front of the detector. The polarimetric mode will provide polarimetric imaging in four broad bands from 92 to 235 μm, using KIDs with three polarization orientations. The main structure of the instrument is the optomechanical assembly, cooled at 1K. It supports at first the two focal plane array assemblies incorporating 0.125K detector stages. In addition, the main structure is providing the interfaces for the 0.125K thermal link, the readout cables and the filters. This paper presents the technical requirements and expected performance of the instrument, as well as the associated design of the sub-systems ensuring compliance. A major challenge will be in-flight performance verification. We will also detail the development strategy, including the planned verification and test program.

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BibTeX RIS

BibTeX

@misc{costille2026design,
  title = {{Design and development of the PRIMAger instrument for PRIMA}},
  author = {Anne Costille and Fabrice Madec and Johan Floriot and Tony Pamplona and Thomas Prouvé and Laure Ciesla and Marc Sauvage and Willem Jellema and Lorenza Ferrari and Jochem Baselmans and Florent Canourgues and Renaud Goullioud and Carole Tucker and C. Darren Dowell},
  howpublished = {arXiv},
  year = {2026},
  month = oct,
  doi = {10.48550/arxiv.2610.06278},
  eprint = {2610.06278},
  archivePrefix = {arXiv},
  url = {https://arxiv.org/abs/2610.06278},
}

RIS

TY  - UNPB
TI  - Design and development of the PRIMAger instrument for PRIMA
AU  - Anne Costille
AU  - Fabrice Madec
AU  - Johan Floriot
AU  - Tony Pamplona
AU  - Thomas Prouv{é}
AU  - Laure Ciesla
AU  - Marc Sauvage
AU  - Willem Jellema
AU  - Lorenza Ferrari
AU  - Jochem Baselmans
AU  - Florent Canourgues
AU  - Renaud Goullioud
AU  - Carole Tucker
AU  - C. Darren Dowell
PY  - 2026
DA  - 2026/10/05
PB  - arXiv
DO  - 10.48550/arxiv.2610.06278
UR  - https://arxiv.org/abs/2610.06278
AB  - PRIMA (PRobe far-Infrared Mission for Astrophysics) is an infrared space observatory designed to operate over the next decade. Equipped with a 1.8 m telescope actively cooled to 4.5 K, the project is currently in the concept study phase as part of the NASA Probe Explorers program. PRIMA will carry two instruments: FIRESS and PRIMAger. PRIMAger will offer two observation modes: hyperspectral imaging and polarimetric imaging. Both channels will use ultra-sensitive kinetic inductance detector (KID) arrays, covering wavelengths from mid-infrared to far-infrared. A European consortium will develop the cold unit of the PRIMAger instrument while the Readout Electronics and Continuous Adiabatic Demagnetization Refrigerator (CADR) will be provided by Goddard Space Flight Center (GSFC) and shared between the 2 instruments. The hyperspectral mode will cover the 24-84 μm range with a spectral resolution of R ≥ 8, ensured by a linear variable filter placed in front of the detector. The polarimetric mode will provide polarimetric imaging in four broad bands from 92 to 235 μm, using KIDs with three polarization orientations. The main structure of the instrument is the optomechanical assembly, cooled at 1K. It supports at first the two focal plane array assemblies incorporating 0.125K detector stages. In addition, the main structure is providing the interfaces for the 0.125K thermal link, the readout cables and the filters. This paper presents the technical requirements and expected performance of the instrument, as well as the associated design of the sub-systems ensuring compliance. A major challenge will be in-flight performance verification. We will also detail the development strategy, including the planned verification and test program.
ER  -

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