We describe the space observatory architecture and mission design of the Single Aperture Large Telescope for Universe Studies (SALTUS) mission, a National Aeronautics and Space Administration (NASA) Astrophysics Probe Explorer concept. SALTUS will address key far-infrared science using a 14-m diameter <45 K primary reflector (M1) and will provide unprecedented levels of spectral sensitivity for planet, solar system, and galactic evolution studies and cosmic origins. Drawing from Northrop Grumman’s extensive NASA mission heritage, the observatory flight system is based on the LEOStar-3 spacecraft platform to carry the SALTUS Payload. The Payload is comprised of the inflation control system, sunshield module (SM), cold corrector module (CCM), warm instrument electronics module, and primary reflector module (PRM). The 14-m M1 is an off-axis inflatable membrane radiatively cooled by a two-layer sunshield (∼1000 m2 per layer). The CCM corrects for residual aberration from M1 and delivers a focused beam to two instruments—the High-Resolution Receiver (HiRX) and SAFARI-Lite. The CCM and PRM reside atop a truss-based composite deck that also provides a platform for the attitude control system. The SALTUS 5-year mission lifetime is driven by a two-consumable architecture: the propellant system and the inflation control system. The core interface module (CIM), a multi-faceted composite truss structure, provides a load path with high stiffness, mechanical attachment, and thermal separation between the Payload and spacecraft. The SM attaches outside the CIM with its aft end integrating directly to the bus. The spacecraft maintains an attitude off M1’s boresight with respect to the Sun line to facilitate the <45 K thermal environment. SALTUS will reside in a Sun–Earth halo L2 orbit with a maximum Earth slant range of 1.8 million km, thereby reducing orbit transfer delta-v. The instantaneous field of regard provides two continuous 20 deg viewing zones around the ecliptic poles, resulting in full sky coverage in 6 months.

中文翻译：

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SALTUS 探测器级太空任务：天文台架构和任务设计


我们描述了用于宇宙研究的单孔径大型望远镜 (SALTUS) 任务的空间天文台架构和任务设计，这是美国国家航空航天局 (NASA) 天体物理探测器探索者概念。 SALTUS 将使用直径 14 米 <45 K 主反射器 (M1) 解决关键的远红外科学问题，并将为行星、太阳系和银河演化研究以及宇宙起源提供前所未有的光谱灵敏度。该天文台飞行系统借鉴了诺斯罗普·格鲁曼公司广泛的 NASA 任务传统，基于 LEOStar-3 航天器平台来承载 SALTUS 有效载荷。有效负载由充气控制系统、遮阳板模块（SM）、冷校正器模块（CCM）、暖仪表电子模块和主反射器模块（PRM）组成。 14 米 M1 是一种离轴充气膜，通过两层遮阳罩（每层约 1000 平方米）进行辐射冷却。 CCM 校正 M1 的残余像差，并将聚焦光束传送到两台仪器 - 高分辨率接收器 (HiRX) 和 SAFARI-Lite。 CCM 和 PRM 位于基于桁架的复合甲板顶部，该甲板还为姿态控制系统提供平台。 SALTUS 5 年任务寿命由两种消耗品架构驱动：推进剂系统和充气控制系统。核心接口模块（CIM）是一种多面复合桁架结构，在有效载荷和航天器之间提供具有高刚度、机械附着和热隔离的负载路径。 SM 连接在 CIM 外部，其后端直接集成到总线。航天器相对于太阳线保持偏离 M1 视轴的姿态，以适应 <45 K 的热环境。 SALTUS将驻留在日地晕L2轨道上，最大地球倾斜范围为180万公里，从而减少轨道转移delta-v。瞬时视场提供黄道周围两个连续的 20 度观察区，从而在 6 个月内实现全天空覆盖。