CARBO is a wide field of view imaging spectrometer for measuring CO, CO2, CH4 and solar-induced chlorophyll fluorescence (SIF). The key technological feature is an immersion grating that increases dispersion and reduces anamorphism for given design constraints, thus providing a more efficient sampling across the spectral band. Another novel design feature is polarization demultiplexing that provides additional information and improves grating efficiency. We present first data and atmospheric test results for a prototype of the 1598-1659 nm spectral band (used for CO2 and CH4 measurements).
UV-SCOPE is a mission concept to determine the causes of atmospheric mass loss in exoplanets, investigate the mechanisms driving aerosol formation in hot Jupiters, and study the influence of the stellar environment on atmospheric evolution and habitability. As part of these investigations, the mission will generate a broad-purpose legacy database of time-domain ultraviolet (UV) spectra for nearly 200 stars and planets. The observatory consists of a 60 cm, f/10 telescope paired to a long-slit spectrograph, yielding simultaneous, almost continuous coverage between 1203 Å and 4000 Å, with resolutions ranging from 6000 to 240. The efficient instrument provides throughputs < 4% (far-UV; FUV) and < 15% (near-UV; NUV), comparable to HST/COS and much better than HST/STIS, over the same spectral range. A key design feature is the LiF prism, which serves as a dispersive element and provides high throughput even after accounting for radiation degradation. The use of two delta-doped Electron-Multiplying CCD detectors with UV-optimized, single-layer anti-reflection coatings provides high quantum efficiency and low detector noise. From the Earth-Sun second Lagrangian point, UV-SCOPE will continuously observe planetary transits and stellar variability in the full FUV-to-NUV range, with negligible astrophysical background. All these features make UV-SCOPE the ideal instrument to study exoplanetary atmospheres and the impact of host stars on their planets. UV-SCOPE was proposed to NASA as a Medium Explorer (MidEx) mission for the 2021 Announcement of Opportunity. If approved, the observatory will be developed over a 5-year period. Its primary science mission takes 34 months to complete. The spacecraft carries enough fuel for 6 years of operations.
We present the current development of the Carbon Balance Observatory (CARBO). CARBO is a wide-swath mapping, low Earth orbit (LEO) new generation of instruments that expands on the ground-breaking CO2 and Solar Induced Fluorescence (SIF) measurements pioneered by the Orbiting Carbon Observatory (OCO-2/3) by adding CH4 and CO detection. The instrument’s spatial coverage is delivered at 2 km by 2 km resolution with a field-of-view of 10° to 15° from LEO for a ~200 km wide swath. It achieves roughly 20x better spatial coverage than the OCO-2 instrument, and 3x better Solar Induced Chlorophyll Fluorescence (SIF) detection sensitivity, in a smaller package. CARBO will measure CO2 at <1.5 ppm, CH4 at <7 ppb, CO at <5 ppb and SIF < 20%. The measurement of CO2/CH4/CO/SIF at these concentrations will significantly increase our ability to disentangle carbon fluxes into their constituent components. CARBO utilizes innovative immersion grating technology and enables high resolving power spectroscopy (roughly 20,000) in a smaller and lighter package that is more cost effective than current space-based CO2 remote sensing instruments. CARBO modules cover 4 different spectral ranges (from 740 nm to 2.3μm), where two channels will be built and field tested. CARBO’s modular architecture reduces implementation risk, accelerates access to space, and extends opportunities to a more diverse set of platforms and launch vehicles. CARBO significantly improves our understanding of the global carbon cycle. Here we discuss an overview of the design elements and focus on the expected radiometric performance of channels 1 (~760 nm) and 2 (~1600 nm).
The Lunar Flashlight (LF) mission will send a CubeSat to lunar orbit via NASA’s Space Launch System (SLS) test flight. The LF spacecraft will carry a novel instrument to quantify and map water ice harbored in the permanently shadowed craters of the lunar South Pole. The LF instrument, an active multi-band reflectometer which employs four high power diode lasers in the 1-2 μm infrared band, will measure the reflectance of the lunar surface near water ice absorption peaks. We present the detailed instrument design and system engineering required to deploy this instrument within very demanding CubeSat resource allocations.
Mapping and quantifying lunar water ice addresses one of NASA’s Strategic Knowledge Gaps to understand the lunar resource potential for future human exploration of the Moon. Lunar Flashlight is an innovative NASA CubeSat mission dedicated to mapping water ice in the permanently-shadowed and occasionally-sunlit regions in the vicinity of the lunar South Pole. Lunar Flashlight will acquire these measurements from lunar orbit using a multi-band laser reflectometer composed of an optical receiver aligned with four lasers emitting different wavelengths in the shortwave infrared spectral region between 1 μm and 2 μm. The receiver measures the laser radiance reflected from the lunar surface in each spectral band and continuum/absorption reflectance band ratios are then analyzed to quantify water ice concentration in the illuminated spot. The receiver utilizes a 70×70-mm, aluminum, off-axis paraboloidal mirror with a focal length of 70 mm, which collects the incoming light onto a single, 2 mm diameter InGaAs detector with a cutoff wavelength of 2.4 μm. We present the optical and mechanical designs of the receiver, including its optimization for rejection of solar stray-light from outside its intended field of view. This highly mass- and volume-constrained instrument payload will demonstrate several firsts, including being one of the first instruments onboard a CubeSat performing science measurements beyond low Earth orbit and the first planetary mission to use multi-band active reflectometry from orbit.
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