发表机构
Aix Marseille Univ, CNRS, CNES, LAM; Univ. Grenoble Alpes, CEA/IRIG/DSBT; Université Paris-Saclay, Université Paris Cité, CEA, CNRS, AIM; SRON Space Research Organization Netherlands; Jet Propulsion Laboratory, California Institute of Technology; Ctr. National d'Études Spatiales; Celtic Terahertz Technology; Delft University of Technology（艾克斯-马赛大学; 格勒诺布尔阿尔卑斯大学; 巴黎萨克雷大学; 荷兰空间研究所; 加州理工学院喷气推进实验室; 法国国家太空研究中心; 凯尔特太赫兹技术公司; 代尔夫特理工大学）
机构由 AI 辅助整理，请以论文原文为准。AI 中文总结
本文介绍PRIMA任务中PRIMAger仪器的设计，涵盖高光谱与偏振两种观测模式、KID探测器阵列及关键技术指标，并阐述子系统的设计与在轨验证策略。
AI 中文摘要
PRIMA（天体物理学远红外探测任务）是一台红外空间天文台，设计用于在未来十年内运行。该项目配备一台主动冷却至4.5 K的1.8米望远镜，目前正处于NASA探测器探索者计划的概念研究阶段。PRIMA将搭载两台仪器：FIRESS和PRIMAger。PRIMAger将提供两种观测模式：高光谱成像和偏振成像。两个通道都将使用超灵敏的动力学电感探测器（KID）阵列，覆盖从远红外到中红外的波长范围。一个欧洲联合体将开发PRIMAger仪器的冷单元，而读出电子设备和连续绝热退磁制冷机（CADR）将由戈达德太空飞行中心（GSFC）提供，并在两台仪器之间共享。高光谱模式将覆盖24-84 $\mu$m波段，光谱分辨率R $\ge$ 8，由放置在探测器前方的线性可变滤波器保证。偏振模式将在92至235 $\mu$m的四个宽带内提供偏振成像，使用具有三种偏振方向的KID。仪器的主要结构是光机组件，在1K温度下冷却。它首先支撑两个包含0.125K探测器级的焦平面阵列组件。此外，主结构还为0.125K热连接、读出电缆和滤波器提供接口。本文介绍了仪器的技术要求和预期性能，以及确保符合要求的各子系统的相关设计。一个主要挑战将是在轨性能验证。我们还将详细介绍开发策略，包括计划的验证和测试程序。
英文摘要
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 $μ$m range with a spectral resolution of R $\ge$ 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 $μ$m, 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.
Journal refSpace Telescopes and Instrumentation 2026: Optical, Infrared, and Millimeter Wave, Jul 2026, Copenhagen, France. pp.92
