The Ultra-Compact Imaging Spectrometer Moon (UCIS-Moon) instrument is a pushbroom shortwave infrared (SWIR) imaging spectrometer prototype developed at NASA’s Jet Propulsion Laboratory (JPL), California Institute of Technology under the Development and Advancement of Lunar Instrumentation (DALI) program. It is designed for integration with a lander or rover for lunar surface science missions. Operating over a 0.6 to 3.6 micron spectral range with 10 nm sampling and a 36 degree field of view, UCIS-Moon is capable of detecting spectral absorptions from common lunar materials, OH species, molecular H2O, water ice, organics, and placing mineral identifications within an established geologic context at the cm to m scale. We discuss instrument assembly, alignment, and measured laboratory optical performance, which meets or exceeds the high-uniformity and high-resolution requirements while achieving a wide spectral range, field of view, and environmental tolerance, with limited mass and power resources. As such, the UCIS-Moon imaging spectrometer is well-suited to address key science questions about lunar geology, the abundance, sources, and sinks of volatiles at the Moon, and the distribution of possible in situ resources for future human exploration.
The Compact Wide Swath Imaging Spectrometer II (CWIS-II) is an imaging spectrometer built, tested, calibrated, and delivered for the University of Zurich (UZH). CWIS-II will be integrated into an aircraft for Earth science research, algorithm development, and satellite calibration and validation. CWIS-II’s two-mirror telescope and Dyson-type spectrometer are optically fast (F/1.8), span a wide swath (40.2-degree field of view over 1240 spatial pixels), record data at 216 frames per second, and operate over the 380-2500 nm solar-reflected spectrum with 7.4 nm spectral sampling. This work describes the CWIS-II instrument configuration, optical alignment process, and present final laboratory spectral and spatial performance.
The Active Thermal Architecture (ATA) is an advanced sub-1U Active Thermal Control technology (ATC) for high power payload support in 6U CubeSat form factors and above. The design utilizes a two-stage, single-phase mechanically pumped fluid loop coupled through a two-axis flexible rotary fluid hinge, to reject thermal power to a deployable tracking radiator. A COTS Ricor K508N cryocooler forms the second stage and provides cryogenic cooling to a custom Kevlar detector mount through a TMT pyrolytic graphene thermal strap. Passive vibration isolation and damping technologies prevent the transfer of jitter to the satellite systems. The ATA design utilizes state-of-the-art 3D fabrication techniques such as Ultrasonic Additive Manufacturing (UAM) to directly embed the working fluid channels into the HX, radiator, and CubeSat chassis allowing for the miniaturization and simplification of the ATA system into an integrated thermal control solution. This paper will focus on the design and ground-based characterization and qualification of the ATA system and provide performance metrics for its use as a thermal support subsystem for advanced infrared electro-optical CubeSat payloads. The ATA project is funded through a NASA Small Satellite Technology Program (SSTP) and is a partnership between the Center for Space Engineering at Utah State University and the Jet Propulsions Laboratory. The ATA active thermal control system has been raised to a TRL of 6 and hopes to provide payload support to advanced missions such as the SABER-Lite and JPL CIRAS projects.
The Ultra-Compact Imaging Spectrometer Moon (UCIS-Moon) instrument is an imaging spectrometer designed for integration with a lander or rover for lunar surface science missions. Operating over a 600-3600 nm spectral range with 10 nm sampling and 1.15 mrad IFOV, UCIS-Moon is capable of detecting spectral absorptions from common lunar minerals, OH species, molecular H2O, water ice, organics, and placing mineral identifications within an established geologic context at the cm to m scale. We present an instrument design capable of surviving the harsh lunar environment in the daytime with temperatures as high as 370 K, while providing high-quality spectral data.
The need for advanced cooled electro-optical instrumentation in remote observations of the atmosphere is well known and demonstrated by SABER on the TIMED mission. The relatively new use of small satellites in remote earth observing missions as, well as the challenges, are epitomized by the upcoming NOAA EON-IR 12U CubeSat missions. These advanced CubeSat missions, which hope to accomplish scientific objectives on the same scale as larger more traditional satellites, require advanced miniaturized cryocoolers and active methods for thermal management and power control. The active CryoCubeSat project (ACCS) is a demonstration of such a technology. Utilizing Ultrasonic Additive Manufacturing (UAM) techniques, a Mechanical Pumped Fluid Loop (MPFL), and miniature pumps and cryocoolers to create a closed loop fluid-based heat interchange system. The ACCS project creates a two-stage thermal control system targeting 6U CubeSat platforms. The first stage is composed of a miniature Ricor K508N cryocooler while the second is formed by a UAM fabricated heat exchanger MPFL system powered by a micro TCS M510 pump. The working fluid is exchanged between a built-in chassis heat exchanger and a deployable tracking radiator. This work details the theory design and testing of a relevant ground-based prototype and the analysis and modeling of the results as well as the development of a design tool to help in customized active thermal control designs for small satellites. Ultimately, the ACCS project hopes to enable a new generation of advanced CubeSat atmospheric observing missions.
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