Proc. SPIE. 10769, CubeSats and NanoSats for Remote Sensing II
KEYWORDS: Staring arrays, Imaging systems, Spectroscopy, Control systems, Infrared spectroscopy, Data archive systems, Telecommunications, Space operations, Solar processes, Absorption
Cubesats operating in deep space face challenges Earth-orbiting cubesats do not. 15 deep space cubesat 'prototypes' will be launched over the next two years including the two MarCO cubesats, the 2018 demonstration of dual communication system at Mars, and the 13 diverse cubesats being deployed from the SLS EM1 mission within the next two years. Three of the EM1 cubesat missions, including the first deep space cubesat 'cluster', will be lunar orbiters with remote sensing instruments for lunar surface/regolith measurements. These include: Lunar Ice Cube, with its 1-4 micron broadband IR spectrometer, BIRCHES, to determine volatile distribution as a function of time of day; Lunar Flashlight, to confirm the presence of surface ice at the lunar poles, utilizing an active source (laser), and looking for absorption features in the returning signal; and LunaH-Map to characterize ice at or below the surface at the poles with a compact neutron spectrometer. In addition, the BIRCHES instrument on Lunar Ice Cube will provide the first demonstration of a microcryocooler (AIM/IRIS) in deep space. Although not originally required to do so, all will be delivering science data to the Planetary Data System, the first formal archiving effort for cubesats. 4 of the 20 recently NASA-sponsored (PSDS3) study groups for deep space cubesat/smallsat mission concepts were lunar mission concepts, most involving 12U cubesats. NASA SIMPLEX 2/SALMON 3 AO will create ongoing opportunities for low-cost missions as 'rides' on government space program or private sector vehicles as these become available.
The Thermal Infrared Sensor-2 (TIRS-2) aboard Landsat 9 will continue Landsat’s four decade-long legacy of providing moderate resolution thermal imagery from low earth orbit (at 705 km) for environmental applications. Like the Thermal Infrared Sensor aboard Landsat 8, it is a pushbroom sensor with a cross-track field of view of 15° and provides two spectral channels at 10.8 and 12 μm. To ensure radiometric, spatial, and spectral performance, a comprehensive pre-launch testing program is being conducted at NASA Goddard Space Flight Center at the component, subsystem, and instrument level. This paper will focus on the results from the subsystem level testing where the instrument is almost completely assembled. This phase of testing is specifically designed to assess imaging performance including focus and stray light rejection, but is also used to provide a preliminary assessments of spatial and spectral performance. The calibration ground support equipment provides a flexible blackbody illumination source and optics to conduct these tests. The spectral response test setup has its own illumination source outside the chamber that propagates through the calibration ground support equipment in an optical configuration designed for this purpose. This test configuration with the calibration ground support equipment and TIRS-2 subsystem in the thermal vacuum chamber enables a large range of illumination angles for stray light measurements. The results show that TIRS-2 performance is expected to meet all of its performance requirements with few waivers and deviations.
The Ralph instrument on the New Horizons mission consists of a telescope that feeds two focal planes: the Multi-spectral Visible Imaging Camera (MVIC), a visible, near-IR imager and the Linear Etalon Imaging Spectral Array (LEISA), a short-wavelength IR spectral imager. During the encounter with the Pluto system in 2015, Ralph operated as expected collecting numerous high spatial resolution images of the main components of the system, Pluto and Charon, as well as the four much smaller objects Hydra, Kerberos, Nix and Styx. New Horizons, launched on January 19, 2006, is the first mission to explore Kuiper Belt Objects (KBOs).
The Thermal Infrared Sensor (TIRS) on board Landsat 8 has exhibited a number of anomalous characteristics that have made it difficult to calibrate. These anomalies include differences in the radiometric appearance across the blackbody pre- and post-launch, variations in the cross calibration ratios between detectors that overlap on adjacent arrays (resulting in banding) and bias errors in the absolute calibration that can change spatially/temporally. Several updates to the TIRS calibration procedures were made in the months after launch to attempt to mitigate the impact of these anomalies on flat fielding (cosmetic removal of banding and striping) and mean level bias correction. As a result, banding and striping variations have been reduced but not eliminated and residual bias errors in band 10 should be less than 2 degrees for most targets but can be significantly more in some cases and are often larger in band 11. These corrections have all been essentially ad hoc without understanding or properly accounting for the source of the anomalies, which were, at the time unknown. This paper addresses the procedures that have been undertaken to; better characterize the nature of these anomalies, attempt to identify the source(s) of the anomalies, quantify the phenomenon responsible for them, and develop correction procedures to more effectively remove the impacts on the radiometric products. Our current understanding points to all of the anomalies being the result of internal reflections of energy from outside the target detector’s field-of-view, and often outside the telescope field-of-view, onto the target detector. This paper discusses how various members of the Landsat calibration team discovered the clues that led to how; these “ghosts” were identified, they are now being characterized, and their impact can hopefully eventually be corrected. This includes use of lunar scans to generate initial maps of influence regions, use of long path overlap ratios to explore sources of change and use of variations in bias calculated from truth sites to quantify influences from the surround on absolute bias errors.
The Thermal Infrared Sensor (TIRS) has completed over one year in Earth orbit following its launch onboard Landsat 8 in February 2013. During that time, TIRS has undergone initial on-orbit checkout and commissioning and has transitioned to an operational Landsat payload obtaining 500+ Earth scenes a day. The instrument was radiometrically calibrated during pre-flight characterization testing. A relative adjustment was made to the calibration during the on-orbit checkout of the instrument based on data from the onboard calibration sources to account for instrument changes that occurred through launch. The accuracy of the relative and absolute radiometric calibration depends in part on the stability of the instrument response over time. To monitor stability, TIRS routinely views its onboard calibration sources, which include a variable temperature blackbody and a port that allows the instrument to view deep space. The onboard calibration is validated by in situ measurements of large water bodies by instrumented buoys. In addition, the spacecraft is periodically slewed to image the moon across the field of view of TIRS. The moon provides a high contrast source which allows for studies of stray light and ghosting to be performed. These on-orbit methods provide the means to characterize the TIRS instrument performance post-launch. Analyses of these datasets over the first year on orbit indicate that while, internally, the instrument itself is far exceeding the noise and stability requirements, both bands were mis-calibrated by at least 2K (@300K) and had higher than expected variability in the in situ validation data. This is likely due to stray light which is also causing banding in Earth scenes. An initial bias correction was made on February 2014 and various approaches are being explored to correct the ghosting issues associated with the stray light.
KEYWORDS: Infrared sensors, Landsat, Sensors, Calibration, Space telescopes, Black bodies, Signal detection, Quantum well infrared photodetectors, Earth observing sensors, Temperature metrology
The Thermal Infrared Sensor (TIRS) on board Landsat 8 continues thermal band measurements of the Earth for the Landsat program. TIRS improves on previous Landsat designs by making use of a pushbroom sensor layout to collect data from the Earth in two spectral channels. The radiometric performance requirements of each detector were set to ensure the proper radiometric integrity of the instrument. The performance of TIRS was characterized during pre-flight thermal-vacuum testing. Calibration methods and algorithms were developed to translate the raw signal from the detectors into an accurate at-aperture spectral radiance. The TIRS instrument has the ability to view an on-board variable-temperature blackbody and a deep space view port for calibration purposes while operating on-orbit.
After TIRS was successfully activated on-orbit, checks were performed on the instrument data to determine its image quality. These checkouts included an assessment of the on-board blackbody and deep space views as well as normal Earth scene collects. The calibration parameters that were determined pre-launch were updated by utilizing data from these preliminary on-orbit assessments. The TIRS on-orbit radiometric performance was then characterized using the updated calibration parameters. Although the characterization of the instrument is continually assessed over the lifetime of the mission, the preliminary results indicate that TIRS is meeting the noise and stability requirements while the pixel-to-pixel uniformity performance and the absolute radiometric performance require further study.
The Climate Absolute Radiance and Refractivity Observatory (CLARREO) mission key goals include enabling
observation of high accuracy long-term climate change trends, use of these observations to test and improve climate
forecasts, and calibration of operational and research sensors. The spaceborne instrument suites include a reflected solar
(RS) spectroradiometer, emitted infrared spectroradiometer, and radio occultation receivers. The requirement for the RS
instrument is that derived reflectance must be traceable to SI standards with an absolute uncertainty of <0.3% and the
error budget that achieves this requirement is described in previous work. This work describes the Solar/Lunar Absolute
Reflectance Imaging Spectroradiometer (SOLARIS), a calibration demonstration system for RS instrument, and presents
initial calibration and characterization methods and results. SOLARIS is an Offner spectrometer with two separate focal
planes each with its own entrance aperture and grating covering spectral ranges of 320-640, 600-2300 nm over a full
field-of-view of 10 degrees with 0.27 milliradian sampling. Results from laboratory measurements including use of
integrating spheres, transfer radiometers and spectral standards combined with field-based solar and lunar acquisitions
are presented.
The Thermal Infrared Sensor (TIRS) on board the Landsat Data Continuity Mission (LDCM) is a two-channel,
push-broom imager that will continue Landsat thermal band measurements of the Earth. The core of the instrument
consists of three Quantum Well Infrared Photodetector (QWIP) arrays whose data are combined to
effectively produce a linear array of 1850 pixels for each band with a spatial resolution of approximately 100
meters and a swath width of 185 kilometers. In this push-broom configuration, each pixel may have a slightly
different band shape. An on-board blackbody calibrator is used to correct each pixel. However, depending
on the scene being observed, striping and other artifacts may still be present in the final data product. The
science-focused mission of LDCM requires that these residual effects be understood.
The analysis presented here assisted in the selection of the three flight QWIP arrays. Each pixel was scrutinized
in terms of its compliance with TIRS spectral requirements. This investigation utilized laboratory spectral measurements
of the arrays and filters along with radiometric modeling of the TIRS instrument and environment.
These models included standard radiometry equations along with complex physics-based models such as the
MODerate spectral resolution TRANsmittance (MODTRAN) and Digital Imaging and Remote Sensing Image
Generation (DIRSIG) tools. The laboratory measurements and physics models were used to determine the extent
of striping and other spectral artifacts that might be present in the final TIRS data product. The results
demonstrate that artifacts caused by the residual pixel-to-pixel spectral non-uniformity are small enough that
the data can be expected to meet the TIRS radiometric and image quality requirements.
The Landsat Data Continuity Mission (LDCM), a partnership between the National Aeronautics and Space Administration
(NASA) and the Department of Interior (DOI) / United States Geological Survey (USGS), is scheduled for launch in
December, 2012. It will be the eighth mission in the Landsat series. The LDCM instrument payload will consist of the
Operational Land Imager (OLI), provided by Ball Aerospace and Technology Corporation (BATC) under contract to NASA
and the Thermal Infrared Sensor (TIRS), provided by NASA's Goddard Space Flight Center (GSFC). This paper outlines the
present development status of the two instruments.
The Landsat Data Continuity Mission consists of a two-sensor platform with the Operational Land Imager and Thermal
Infrared Sensor (TIRS). Much of the success of the Landsat program is the emphasis placed on knowledge of the
calibration of the sensors relying on a combination of laboratory, onboard, and vicarious calibration methods. Rigorous
attention to NIST-traceability of the radiometric calibration, knowledge of out-of-band spectral response, and
characterizing and minimizing stray light should provide sensors that meet the quality of Landsat heritage. Described
here are the methods and facilities planned for the calibration of TIRS which is a pushbroom sensor with two spectral
bands (10.8 and 12 micrometer) and the spatial resolution 100 m with 185-km swath width. Testing takes place in a
vacuum test chamber at NASA GSFC using a recently-developed calibration system based on a 16-aperture black body
source to simulate spatial and radiometric sources. A two-axis steering mirror moves the source across the TIRS field
while filling the aperture. A flood source fills the full field without requiring movement of beam providing a means to
evaluate detector-to-detector response effects. Spectral response of the sensor will be determined using a monochromator
source coupled to the calibration system. Knowledge of the source output will be through NIST-traceable thermometers
integrated to the blackbody. The description of the calibration system, calibration methodology, and the error budget for
the calibration system shows that the required 2% radiometric accuracy for scene temperatures between 260 and 330 K
is well within the capabilities of the system.
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