This PDF file contains the front matter associated with SPIE Proceedings Volume 9978, including the Title Page, Copyright information, Table of Contents, and Conference Committee listing.

In this paper, we present a study conducted by the National Academies of Sciences, Engineering, and Medicine. The study focused on the scientific potential and technological promise of CubeSats. We will first review the growth of the CubeSat platform from an education-focused technology toward a platform of importance for technology development, science, and commercial use, both in the United States and internationally. The use has especially exploded in recent years. For example, of the over 400 CubeSats launched since 2000, more than 80% of all science-focused ones have been launched just in the past four years. Similarly, more than 80% of peer-reviewed papers describing new science based on CubeSat data have been published in the past five years. We will then assess the technological and science promise of CubeSats across space science disciplines, and discuss a subset of priority science goals that can be achieved given the current state of CubeSat capabilities. Many of these goals address targeted science, often in coordination with other spacecraft, or by using sacrificial or high-risk orbits that lead to the demise of the satellite after critical data have been collected. Other goals relate to the use of CubeSats as constellations or swarms, deploying tens to hundreds of CubeSats that function as one distributed array of measurements. Finally, we will summarize our conclusions and recommendations from this study; especially those focused on near-term investment that could improve the capabilities of CubeSats toward increased science and technological return and enable the science communities’ use of CubeSats.

MISTiCTM Winds is an approach to improve short-term weather forecasting based on a miniature high resolution, wide field, thermal emission spectrometry instrument that will provide global tropospheric vertical profiles of atmospheric temperature and humidity at high (3-4 km) horizontal and vertical ( 1 km) spatial resolution. MISTiC’s extraordinarily small size, payload mass of less than 15 kg, and minimal cooling requirements can be accommodated aboard a 27U-class CubeSat or an ESPA-Class micro-satellite. Low fabrication and launch costs enable a LEO sunsynchronous sounding constellation that would collectively provide frequent IR vertical profiles and vertically resolved atmospheric motion vector wind observations in the troposphere. These observations are highly complementary to present and emerging environmental observing systems, and would provide a combination of high vertical and horizontal resolution not provided by any other environmental observing system currently in operation. The spectral measurements that would be provided by MISTiC Winds are similar to those of NASA’s AIRS that was built by BAE Systems and operates aboard the AQUA satellite. These new observations, when assimilated into high resolution numerical weather models, would revolutionize short-term and severe weather forecasting, save lives, and support key economic decisions in the energy, air transport, and agriculture arenas–at much lower cost than providing these observations from geostationary orbit. In addition, this observation capability would be a critical tool for the study of transport processes for water vapor, clouds, pollution, and aerosols. Key remaining technical risks are being reduced through laboratory and airborne testing under NASA’s Instrument Incubator Program.

Global measurements of vertically resolved atmospheric wind profiles offer the potential for improved weather forecasts and superior predictions of atmospheric wind patterns. Harris’ HyperCube constellation of twelve 6U hyperspectral CubeSats can provide measurements of global tropospheric wind profiles from space at very low cost. It is a commercially funded enterprise in which the data from the satellites is provided to users on a subscription basis. This requires that the design of each satellite be optimized for minimum cost, yet with a reasonably long service life. This paper will focus on the design, operations, and projected performance of the HyperCube system.

The CubeSat Infrared Atmospheric Sounder (CIRAS) will measure upwelling infrared radiation of the Earth in the MWIR region of the spectrum from space on a CubeSat. The observed radiances have information of potential value to weather forecasting agencies and can be used to retrieve lower tropospheric temperature and water vapor globally for weather and climate science investigations. Multiple units can be flown to improve temporal coverage or in formation to provide new data products including 3D atmospheric motion vector winds. CIRAS incorporates key new instrument technologies including a 2D array of High Operating Temperature Barrier Infrared Detector (HOT-BIRD) material, selected for its high uniformity, low cost, low noise and higher operating temperatures than traditional materials. The detectors are hybridized to a commercial ROIC and commercial camera electronics. The second key technology is an MWIR Grating Spectrometer (MGS) designed to provide imaging spectroscopy for atmospheric sounding in a CubeSat volume. The MGS has no moving parts and includes an immersion grating to reduce the volume and reduce distortion. The third key technology is an infrared blackbody fabricated with black silicon to have very high emissivity in a flat plate construction. JPL will also develop the mechanical, electronic and thermal subsystems for CIRAS, while the spacecraft will be a commercially available CubeSat. The integrated system will be a complete 6U CubeSat capable of measuring temperature and water vapor profiles with good lower tropospheric sensitivity. The CIRAS is the first step towards the development of an Earth Observation Nanosatellite Infrared (EON-IR) capable of operational readiness to mitigate a potential loss of CrIS on JPSS or complement the current observing system with different orbit crossing times.

Three MIT / Lincoln Laboratory nanosatellite advanced technology missions flying microwave radiometers for high-resolution atmospheric sensing are in varying stages of development. Microwave instrumentation is particularly well suited for implementation on a very small satellite, as the sensor requirements for power, pointing, and spatial resolution (aperture size) can be accommodated by a nanosatellite platform. The first upcoming mission, the Microsized Microwave Atmospheric Satellite Version 2 (MicroMAS-2), will demonstrate temperature sounding in eight channels near 118 GHz, humidity sounding in three channels near 183 GHz, and cloud ice measurements in a single channel near 206 GHz. Two MicroMAS-2 3U flight units are in development, with the first to launch in early 2017. The Microwave Radiometer Technology Acceleration (MiRaTA) CubeSat will demonstrate multi-band atmospheric sounding and co-located GPS radio occultation for cross calibration. MiRaTA will launch as a secondary payload on the JPSS-1 mission as part of ELaNa-XIV. MiRaTA is designed for a one-year mission life and will fly a tri-band sounder (60, 183, and 206 GHz) and a GPS radio occultation (GPS-RO) sensor comprising a modified COTS receiver and antenna patch array. Building upon this work, the Earth Observing Nanosatellite-Microwave (EON-MW) mission is being formulated by MIT Lincoln Laboratory for NOAA as part of the Polar Follow-On (PFO) Program’s 2017 budget request. PFO plans to extend JPSS for two more missions and provides a means to mitigate the risk of a gap in continuity of weather observations. The PFO request aims to achieve robustness in the polar satellite system to ensure continuity of NOAA’s polar-orbiting weather observations. The baseline EON-MW design accommodates a scanning 22-channel, high-resolution microwave spectrometer on a 12U CubeSat platform to provide data continuity with the existing AMSU and ATMS microwave sounding systems. EON-MW will nominally be launched into a sun-synchronous orbit for a two to three year mitigation mission in 2020 that will also demonstrate advanced miniaturized microwave sounder technology that expands on the capabilities developed for MicroMAS-2 and MiRaTA. Key EON-MW planned features include a pair of compact single-reflector radiometers that permit the entire microwave sounding payload to be developed with a total mass of approximately 4 kg while maximizing antenna aperture for optimal spatial resolution. The spacecraft bus is approximately 16 kg, and the entire satellite (prior to solar array deployment) measures approximately 22x22x34 cm. Communications to ground are planned with a space-qualified X-band transceiver and a ground station to be nominally located at a high latitude. Average power consumption of the satellite is approximately 50 W. This presentation will provide an overview of the EON-MW mission, discuss key satellite and payload subsystems, describe risk reduction and mission planning, and present key attributes of the ground and data segments.

The TEMPEST-D in-space technology demonstration mission will reduce the risk, cost and development time of a future constellation of 6U-Class nanosatellites observing the temporal evolution of clouds to the onset of precipitation. TEMPEST-D provides passive millimeter-wave observations using a compact instrument that fits well within the 6U-Class nanosatellite architecture. TEMPEST millimeter-wave radiometers with five frequencies from 89 GHz to 182 GHz penetrate into the cloud to observe key changes as precipitation begins or as ice accumulates inside the storm. A full TEMPEST constellation mission would enable study of the conditions controlling the transition from non-precipitating to precipitating clouds using high-temporal resolution observations. Knowledge of cloud processes is essential to our understanding of climate change. Uncertainties in the representation of key processes that govern the formation and dissipation of clouds and, in turn, control the global water and energy budgets lead to substantially different predictions of future climate in current models. For the full TEMPEST constellation mission, five identical 6U-Class nanosatellites would be deployed in the same orbital plane with 5-minute spacing, initially at 450 km altitude and 51° inclination. A one-year mission would capture 3 million observations of precipitation, including at least 100,000 deep convective events. Passive drag-adjusting maneuvers would separate the five CubeSats in the same orbital plane, similar to those planned for NASA’s CYGNSS mission scheduled for launch in October 2016. TEMPEST-D was selected by NASA’s CubeSat Launch Initiative (CSLI) in February 2015 and TEMPEST-D manifested for a March 2018 launch on Firefly Space Systems Alpha.

We report on the design and demonstration of a CubeSat-scale spatial heterodyne spectrometer suitable for high-resolution imaging of molecular bands against the earth surface or limb. The demonstration instrument is tuned to a methane absorption band at 1637-1657 nm. The spectral resolution of 0.13 nm is sufficient to resolve individual methane lines, intervening CO₂ absorption, and background scattering. The all-transmissive design utilizes volume holographic gratings for high optical efficiency.

CICERO (Community Initiative for Continuous Earth Remote Observation) is a grassroots effort to deploy a nanosat-based cellular observing system to acquire global Earth and environmental data from low Earth orbit at extremely low cost. CICERO will place micro-sensors on nanosats (or cells) in large numbers for diverse remote sensing applications. Scores of cells will combine to form a global supersensor of enormous power. Produced by the dozen, these tiny craft will cost little to build and launch. The cellular model will improve measurement sensitivity by an order of magnitude at a fraction of today’s system costs. GeoOptics has developed an array of novel cellular observing technologies, from sensor and nanosat designs to unique on-orbit cell configurations, to maximize information return. The approach consolidates diverse sensing techniques into integrated sensors to yield a breadth of products. CICERO will offer frequent launches to expedite deployment of new sensors.

Soft X-ray emission from ~0.1 to 10 keV (~1-100 Å) provides unique diagnostics for high-temperature plasmas, but observations of the Sun in this energy range that are both spectrally and spatially resolved have been nearly non-existent. The Multi-Order X-ray Spectral Imager (MOXSI) is an instrument concept for a novel, slitless X-ray imaging spectrograph that will make crucial new measurements in this observationally-important wavelength range yet still fit within the limited resource constraints of a CubeSat. MOXSI utilizes a custom pinhole camera with a COTS, back-thinned CMOS sensor combined with a Chandra-heritage X-ray transmission diffraction grating to provide spatially-resolved, full-Sun imaging spectroscopy from ~1 to ~55 Å (~0.2-10 keV) with ~25 arcsec and ~0.25 Å FWHM spatial and spectral resolutions, respectively, and cadence of ~few tens of sec. MOXSI produces images akin to an “overlappograph,” with the 0th-order and dispersed images overlaid on the same detector; the dispersion direction is specifically oriented orthogonal to the latitudinal bands of solar activity to minimize source confusion. Additional pinhole apertures with custom entrance filters provide undispersed broadband filtergram images for additional source information. To mitigate motion-induced smearing, an on-board, real-time motion compensation system co-adds a series of frames for each integration period. MOXSI is one of the instruments of the proposed CubeSat Imaging X-ray Solar Spectrometer (CubIXSS) mission concept, which will improve our physical understanding of thermal plasma processes and impulsive energy release in the solar corona, from quiet Sun to solar flares, and the impact of solar X-rays on Earth’s upper atmosphere.

Lunar Ice Cube, a science requirements-driven deep space exploration 6U cubesat mission was select-ed for a NASA HEOMD NextSTEP slot on the EM1 launch. We are developing a compact broadband IR instrument for a high priority science application: un-derstanding volatile origin, distribution, and ongoing processes in the inner solar system. JPL’s Lunar Flash-light, and Arizona State University’s LunaH-Map, both also EM1 lunar orbiters, will provide complimentary observations to be used in understanding volatile dynamics on the Moon.

The CubeSat mission with the demonstrator of miniaturized X-ray telescope is presented. The paper presents one of the mission objectives of using the instrument for remote sensing of the Terrestrial Gamma-ray Flashes (TGFs). TGFs are intense sources of gamma-rays associated with lightning bolt activity and tropical thunderstorms. The measurement of TGFs exists and was measured by sounding rockets, high altitude balloons or several satellite missions. Past satellite missions were equipped with different detectors working from 10 keV up to 10 MeV. The RHESSI mission spectrum measurement of TGFs shows the maximum counts per second around 75 keV. The used detectors were in general big in volume and cannot be utilized by the CubeSat mission. The presented CubeSat is equipped with miniaturized X-ray telescope using the Timepix non-cooled pixel detector. The detector works between 3 and 60 keV in counting mode (dosimetry) or in spectrum mode with resolution 5 keV. The wide-field X-ray "Lobster-eye" optics/collimator (depending on energy) is used with a view angle of 3 degrees for the source location definition. The UV detectors with FOV 30 degrees and 1.5 degrees are added parallel with the optic as a part of the telescope. The telescope is equipped with software distinguishing between the photons and other particles. Using this software the TGF's detection is possible also in the field of South Atlantic anomaly. For the total ionization dose, the additional detector is used based on Silicone (12-60 keV) and CdTe (20 keV - 1 MeV). The presented instruments are the demonstrators suitable also for the astrophysical, sun and moon observation. The paper shows the details of TGF's observation modes, detectors details, data processing and handling system and mission. The CubeSat launch is planned to summer 2016.

The Compact Infrared Radiometer in Space (CIRiS) is a thermal infrared radiometric imaging instrument under development by Ball Aerospace for a Low Earth Orbit mission on a CubeSat spacecraft. Funded by the NASA Earth Science Technology Office’s In-Space Validation of Earth Science Technology (InVEST) program, the mission objective is technology demonstration for improved on-orbit radiometric calibration. The CIRiS calibration approach uses a scene select mirror to direct three calibration views to the focal plane array and to transfer the resulting calibrated response to earth images. The views to deep space and two blackbody sources, including one at a selectable temperature, provide multiple options for calibration optimization. Two new technologies, carbon nanotube blackbody sources and microbolometer focal plane arrays with reduced pixel sizes, enable improved radiometric performance within the constrained 6U CubeSat volume. The CIRiS instrument’s modular design facilitates subsystem modifications as required by future mission requirements. CubeSat constellations of CIRiS and derivative instruments offer an affordable approach to achieving revisit times as short as one day for diverse applications including water resource and drought management, cloud, aerosol, and dust studies, and land use and vegetation monitoring. Launch is planned for 2018.

Recent years have seen a rise in the development of concepts for constellations of SmallSats or Cubesats for Earth Observation remote sensing. These constellations focus on visible RGB imagery or multi-band imagery from a handful of wide-bands in the visible or near infrared wavelengths. Mid-wave infrared (MWIR) data provides a unique measurement, able to be operated both for day and night imaging. Recent developments in infrared detectors and the miniaturization of cryocooler technology enable this instrument be packaged in a Cubesat form-factor. Data products derived from the MWIR measurement have been shown to be beneficial in agricultural decision making process, specifically in irrigation and water use. Planetary Resources is developing a MWIR instrument operating across the 3-5um wavelength for the purpose of prospecting near-Earth asteroids. In turning the gaze of the sensors to nadir from low-Earth orbit, a unique dataset is created that is currently lacking from existing commercial Earth observation platforms. This paper presents the MWIR instrument, its measurement from low-Earth orbit and its potential for near-Earth asteroid exploration.

We present the Compact Holographic Aberration-corrected Platform (CHAP) instrument, designed and developed at Planetary Resources Development Corporation. By combining a dispersive element with the secondary of a telescope, we are able to produce a relatively long focal length with moderate dispersion at the focal plane. This design enables us to build a capable hyperspectral imaging instrument within the size constraints of the Cubesat form-factor. The advantages of our design revolves around its simplicity: there are only two optical elements, producing both a white light and diffracted image. With the use of a replicated grating, we can produce a long focal length hyperspectral imager at a price point far below other spaceflight instruments. The design is scalable for larger platforms and since it has no transmitting optics and only two reflective surfaces could be designed to function at any desired wavelength. Our system will be capable of spectral imaging across the 400 to 900 nm spectral range for use in small body surveys.

The SeaHawk 3U CubeSat program is funded by the Gordon and Betty Moore Foundation of San Francisco, and managed by John Morrison of the University of North Carolina-Wilmington (UNC-W). Cloudland Instruments is developing HawkEye for SeaHawk. HawkEye is a multispectral ocean color imager of SeaWiFS quality with 120 meter nadir resolution from an orbit altitude of 540 km to provide observation of sub-mesoscale variability for insights into poorly understood mixing dynamics. 120 meter imagery improves ability, relative to SeaWiFS 1km resolution, to monitor fjords, estuaries, coral reefs and other near-shore environments where anthropogenic stresses are often most acute and where there are considerable security and commercial interests. The optics, filters, and arrays comprise a cube 10 cm on a side to fit a 3U CubeSat manufactured by ClydeSpace of Glasgow Scotland, and provide a 350 km swath cross-track.

Blue Canyon Technologies (BCT) has developed a family of high-performance, turn-key spacecraft platforms (3U, 6U, and 12U) that provide all the necessary features to support remote sensing. The spacecraft core is BCT’s powerful XB1 avionics. The XB1 (currently baselined in multiple spacecraft for various government and commercial customers, such as TEMPEST-D, NASA Invest, and PlanetiQ constellation) provides all C and DH, ADCS, EPS, and Software functionality in a 1U package, which maximizes available volume for the payload and propulsion. The ability to orient the XB-1 avionics cube in a number of directions within the spacecraft, provides the user with a wide range of mission configurations and flight orientations. The XB1 ADCS utilizes dual star trackers (with integrated stray-light baffles), which provide the highest-precision pointing available for CubeSats. The high-precision pointing and precision GPS and time-keeping maximizes payload data collection quality, and allows body-pointing of high-data-rate RF or laser-comm downlink systems. BCT’s X-band RF downlink system can provide 50Mbps, and licensed third-part laser comm provides over 2Gbps. BCT’s highly-configurable solar panel deployment system (and optional solar array drive) provides up to 85W of spacecraft power. The XB1 EPS performs all charge control, and provides switched, regulated voltages to the payload. Battery capacity can be as high as 75 Watt-hours. The sophisticated command and telemetry system supports 1000s of stored commands, macro command lists, multiple telemetry maps, and a table-driven scripting language to easily customize fault detection/response and autonomy without the need for code loads. The platform can accommodate propulsion as well.

The increasing availability of small satellites such as CubeSats have improved low cost access to space. New scientific measurements may be made, and new concepts may be tested for larger scale missions in the future. Particle detection instruments in conventional size spacecraft have to meet significant constraints on mass, power and volume. These constraints are more substantial in the CubeSat platform. Microchannel plate (MCP) electron multipliers are frequently used in particle detection instruments because of their high gain, low mass, and thin planar configuration. However, non-planar MCPs can be used to improve instrument performance and make better use of available volume by adopting a shape that is compatible with the natural instrument geometry. Non-planar MCPs have been made in this work using a novel method, in which a glass microchannel substrate is coated with thin films that provide the necessary resistive and secondary electron emissive properties. The glass substrates were first slumped at a high temperature to a mandrel of the desired shape, after which the thin films were applied. The MCPs were cylindrically curved, with radii of curvature of 75 mm and 20 mm, and with angular spans of 90 degrees and 180 degrees respectively. The azimuthal gain and resistance uniformity was measured and will be presented.

We report the development and initial testing of the Lockheed Martin first-article, single-stage, compact, coaxial, Fast Cooldown Pulse Tube Microcryocooler (FC-PTM). The new cryocooler supports cooling requirements for emerging large, high operating temperature (105-150K) infrared focal plane array sensors with nominal cooling loads of ~300 mW @105K @293K ambient. This is a sequel development that builds on our inline and coaxial pulse tube microcryocoolers reported at CEC 2013⁷, ICC18^8,9, and CEC2015¹⁰. The new FC-PTM and the prior units all share our long life space technology attributes, which typically have 10 year life requirements¹. The new prototype microcryocooler builds on the previous development by incorporating cold head design improvements in two key areas: 1) reduced cool-down time and 2) novel repackaging that greatly reduces envelope. The new coldhead and Dewar were significantly redesigned from the earlier versions in order to achieve a cooldown time of 2-3 minutes-- a projected requirement for tactical applications. A design approach was devised to reduce the cold head length from 115mm to 55mm, while at the same time reducing cooldown time. We present new FC-PTM performance test measurements with comparisons to our previous pulse-tube microcryocooler measurements and design predictions. The FC-PTM exhibits attractive small size, volume, weight, power and cost (SWaP-C) features with sufficient cooling capacity over required ambient conditions that apply to an increasing variety of space and tactical applications.

CubeSats are a good opportunity to test new technologies and materials on orbit. These innovations can be later used for improving of properties and life length of Cubesat or other satellites as well. VZLUSAT-1 is a small satellite from the CubeSat family, which will carry a wide scale of payloads with different purposes. The poster is focused on measuring of degradation and properties measurement of new radiation hardened composite material in orbit due to space environment. Material properties changes can be studied by many methods and in many disciplines. One payload measures mechanical changes in dependence on Young's modulus of elasticity which is got from non-destructive testing by mechanical vibrations. The natural frequencies we get using Fast Fourier Transform. The material is tested also by several thermometers which measure heat distribution through the composite, as well as reflectivity in dependence on different coatings. The satellite also will measure the material radiation shielding properties. There are PIN diodes which measure the relative shielding efficiency of composite and how it will change in time in space environment. Last one of material space testing is measurement of outgassing from tested composite material. It could be very dangerous for other parts of satellite, like detectors, when anything was outgassing, for example water steam. There are several humidity sensors which are sensitive to steam and other gases and measures temperatures as well.