Artemis I CubeSats Prepare for Launch on NASA’s Space Launch System
Artemis I CubeSats Prepare for Launch on NASA’s Space Launch System
Stephen D Creech↗
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Hybrid Upper Stage Provides a Safe, Green, and Cost-Efficient Solution for CubeSat Launches
Parabilis Space Technologies developed a hybrid upper stage that combines the benefits of traditional liquid and solid propulsion systems while reducing risk and cost. Hybrid technology is safe, green, and cost-efficient, making it versatile, especially for CubeSat launches, and Parabilis’ ACE configuration makes the system more compact. Parabilis received additional funding from NASA and the U.S. Air Force to develop this technology beyond the Phase I and II STTR accomplishments
SBIR/STTR↗
CubeSat Platform Enables an Inexpensive Space Telescope
Space telescopes have historically been expensive to plan, build, and launch. The Astrophysics Division of NASA’s Science Mission Directorate is now leveraging the development of small spacecraft known as CubeSats by universities and industry to enable capable and reliable platforms with well-focused goals, rapid development times, and affordable costs
technology↗
Iris Deep-Space Transponder for SLS EM-1 CubeSat Missions
Several key design upgrades have been recently made to the Iris Deep-Space Transponder baselined to be used on secondary payload missions of the upcoming Space Launch System Exploration Mission One (SLS EM-1). The Iris Transponder is a reconfigurable software-defined radio (SDR) designed for missions requiring interoperability with NASA's Deep Space Network (DSN) on X-band frequencies (7.2 GHz uplink, 8.4 GHz downlink). The transponder provides radiometric tracking support with the DSN to provide navigational products for precise orbit determination while performing standard uplink and downlink communications in a CubeSat/SmallSat-applicable package size. The recent hardware changes include a volume reduction of 30% from previous models, with the main transponder unit weighing less than 1.0 kg, while maintaining total ionizing dose (TID) radiation tolerance of >23 krads (Si) for deep-space missions. Lab tests indicate maximum downlink rates of up to 6.25 Msps can be supported by the transponder in conventional BPSK modulation, but most SLS EM-1 CubeSat missions are link-performance limited to less than 256 kbps. A prototype unit of the flight production units has been assembled and various performance and characterization tests are underway. This talk discusses the key design aspects and specifications of the Iris Transponder and presents preliminary results from early testing of the assembled transponder.
Kobayashi, M. Michael↗
Binary polarization-shift-keyed modulation for interplanetary CubeSat optical communications
Recent developments for laser communication on CubeSats across interplanetary distances will be presented. A binary polarization-shift-keyed modulation scheme using dual gain-switched diode lasers is developed and demonstrated within an end-to-end link testbed to achieve signal acquisition under extremely poor signal-to-noise conditions (-43.5 dB average signal-to-noise power ratio at a 1-MHz symbol rate) to simulate direct-to-Earth links, while simultaneously targeting a limited SWaP footprint (1.5U envelope). Additional system design and constraints for the compact laser transmitter will be discussed.
Kovalik, Joseph M.↗
Lessons Learned from a Deployment Mechanism for a Ka-band Deployable Antenna for CubeSats
The Ka-band parabolic deployable antenna (KaPDA) is a 0.5 meter diameter antenna which fits in a tiny, CubeSat compatible 10 cm by 10 cm by 16 cm volume. The design evolved from a rough concept in an R&D proposal to a fully flight qualified design, scheduled for launch in May of 2018, in a timeframe of just 4 years. This paper focuses on key lessons learned on maintaining precision through structural depth, use of fixtures and additive manufacturing for fabrication, the design of robust, deterministic mechanisms, and the dangers of friction and press fits
Thomson, Mark↗
Using telemetry to navigate the MarCO cubesats to Mars
The two MarCO “cubesat” spacecraft were launched alongside NASA’s InSight in May 2018, operating primarily as a technology demonstrator for small satellites in deep space, with a nominal (but experimental) mission to provide relay support for the primary spacecraft during entry, descent, and landing at Mars. Due to their small size and experimental nature, extensive use of telemetry beyond that commonly used by deep space missions was necessary to complete adequate orbit determination. In particular, telemetry was valuable in two areas: use of wheel speeds during thruster calibrations to improve knowledge of individual thruster force levels, and the use of propellant temperature and pressure data to correctly model small thrusting events on board the vehicle.
Martin-Mur, Tomas↗
Near earth asteroid scout CubeSat science data retrieval optimization using onboard data analysis
We present a collection of techniques designed for mitigating limited pointing stability for target acquisition, onboard image calibration and decision making, in a low bandwidth environment. These technologies will fly on the Near Earth Asteroid Scout (NEA Scout) interplanetary CubeSat mission in 2019. To support verification and validation, the flight software implementations of these algorithms have been run on New Horizons, Rosetta and terrestrially acquired data sets. These experiments validate the capability to detect the target, through noise and target location uncertainty.
Basset, Christophe↗
Deployable CubeSat Antennas for Deep Space and Earth Science Missions
New antenna technologies have unlocked a new class of missions using CubeSats for Earth Science or Deep Space operations. This class of small satellites have historically been mostly used as teaching tools allowing students to design and test small satellites and develop space experiments. With the rise of new game-changing antenna technologies, overcoming their small size and need for high gain, they can now be used beyond Low Earth Orbit (LEO). Over the past 5 years, technologists at the Jet Propulsion Laboratory have designed, tested and successfully flown these innovative Smallsat antennas, enabling new telecommunication and science achievements.
Cwik, Tom↗
Cubesat Deployment from a Near Rectilinear Halo Orbit
Satellites deployed from the Gateway in a Near Rectilinear Halo Orbit (NRHO) must be safely delivered their desired destinations in cislunar space and beyond. The presence of simultaneously significant gravitational forces from the Moon, the Earth, and the Sun, along with the absence of atmospheric drag, complicates the mission design problem for cubesats deployed from the Gateway. The current investigation defines candidate green zones for safe satellite deployment, allowing a passive departing spacecraft to avoid recontact with the Gateway as it departs the NRHO vicinity.
NRHO↗
PetitSat - a 6U CubeSat to Examine Plasma Density Enhancements in the Ionosphere
PetitSat is a CubeSat mission designed to examine the link between Medium-Scale Traveling Ionospheric Disturbances (MSTIDs) in the upper atmosphere and plasma density enhancements. The mission will provide in situ measurements of the plasma density, 3D ion drift, as well as ion and neutral composition. The instrument suite includes a combined retarding potential analyzer and cross-track drift meter and an ion-neutral mass spectrometer. This instrument suite will provide comprehensive information about the fluctuations in plasma, as well as changes in the neutral profile. petitSat will launch into a 51 deg inclination orbit at 400 km (consistent with an International Space Station deployment), allowing for numerous conjunctions with the Boston University All-Sky Imager network and GPS receivers from the International Global Navigation Satellite Systems (GNSS) Service (IGS) network over the mission lifetime.
Jeffrey Hamilton Klenzing↗
Pointing, Acquisition, and Tracking for the TBIRD Cubesat Mission: System Design and Pre-Flight Results
The Terabyte InfraRed Delivery (TBIRD) program will establish a communication link from a nanosatellite in low-Earth orbit to a ground station at burst rates up to 200 Gbps. The TBIRD payload is currently in the process of integrating with the 6-U CubeSat host bus and pre-flight testing has been completed. An overview of the pointing, acquisition, and tracking system for TBIRD is provided as well as a summary of results from pre-flight testing. TBIRD relies on the spacecraft bus to implement fine pointing corrections supplied by its quad sensor at a rate of 10 Hz. The measured accuracy of pointing feedback is about 10μrad RMS per axis. A custom optical assembly was designed for transmitter/receiver alignment stability which was measured to be within 25μrad two-axis through environmental testing. With TBIRD feedback in the loop, single axis pointing accuracy of the downlink is predicted to be about 30μrad RMS.
space communications↗
Satellite-To-Satellite Imaging in Support of LEO Optical Navigation, Using the ASTERIA Cubesat
The Arcsecond Space Telescope Enabling Research in Astrophysics (ASTERIA) was a 6-unit CubeSat technology demonstration mission that was built at NASA’s Jet Propulsion Laboratory (JPL) and deployed from the International Space Station (ISS) on November 20th, 2017. After successfully completing its 90-day primary mission that demonstrated arcsecond-level line-of-sight pointing and focal plane thermal stability for exoplanet detection, it entered an extended mission performing onboard software demonstrations alongside science until end of mission in December 2019. At the end of its lifetime it was being used as a demonstration platform for several experiments, including low earth orbit (LEO) optical navigation operations. With its visible light astrometric camera and stable attitude control system, the ASTERIA spacecraft showed itself to be a capable platform for the imaging of geosynchronous satellites from LEO. This paper will describe the imagery attained in flight and also the image processing algorithms that were developed to render that imagery into navigation quality data. These algorithms dealt with hot pixel filtering, noise modeling, attitude registration, star signal rejection and satellite signal identification. Brightness prediction algorithms used for target selection will also be discussed.
Fesq, Lorraine↗
Results from the ASTERIA CubeSat Extended Mission Experiments
Over the past two years, JPL has used the ASTERIA (Arcsecond Space Telescope Enabling Research In Astrophysics) CubeSat as an in-flight test platform during extended missions. ASTERIA successfully completed its prime mission in early 2018, and continued to operate in low Earth orbit (LEO) for an additional twenty months. This paper describes demonstrations that were performed on the spacecraft and on the ground-based testbed during the extended mission. These demonstrations fall into three categories: Autonomy technology maturation, hardware characterization, and science discovery. Autonomy technology maturation supported three development efforts. The first shifted the spacecraft commanding paradigm from time-based sequences to Task Networks (tasknets), which allow simpler commanding and more robust onboard execution. The second demonstrated onboard orbit determination in Low Earth Orbit (LEO) without GPS. This activity used a fully-independent means of spacecraft orbit determination for Earth orbiters using only passive imaging. The third technology provided in situ hardware health state estimation using a model-based reasoning technique. These three technologies were demonstrated either in flight or on the testbed individually, and then were combined to demonstrate the capability to perform autonomous navigation on board without ground intervention, even in the presence of anomalies. Hardware characterization involved both onboard and ground-based activities. On board, nonstandard attitude control modes were commanded to characterize the spacecraft pointing jitter as a function of target brightness, reaction wheel speed, controller gain, and the number of guide stars. The results provide insights into the contribution of jitter to the ASTERIA photometry and inform the feasibility of future astrophysics small satellite missions for which jitter control is an enabling technology. On the ground, the ASTERIA Operations Team coordinated with Amazon Web Services (AWS) to configure their new ground stations to communicate with ASTERIA to prove out their viability. ASTERIA used AWS ground stations for nominal operations for the last four months of the mission. Finally, ASTERIA continued to perform exoplanet science as the spacecraft was well-suited to execute long-term monitoring of stars such as alpha Centauri to search for small transiting planets. The science team also imaged a number of interesting objects including a comet, an asteroid, cities at night, and the moon, and coordinated with other projects on Targets of Opportunity for follow-up confirmations and co-observations. Throughout the prime and the extended missions, the ASTERIA spacecraft proved to be a mighty platform that “will go into history as an innovative milestone.”[1 - Zurbuchen]
Doran, Patrick↗
Development of a COTS-Based Propulsion System Controller for NASA's Lunar Flashlight CubeSat Mission
The Lunar Flashlight mission is designed to send a 6U CubeSat into Lunar orbit with the aim of finding water-ice deposits on the Lunar south pole. Georgia Tech’s Space Systems Design Laboratory (SSDL) is developing a low-cost propulsion system controller for this satellite using commercial-o↵-the-shelf (COTS) parts, with an emphasis on overcoming the harsh environment of Lunar orbit through careful architecture and testing. This paper provides in-depth coverage of the LFPS controller development and testing processes, showing how an embedded system based on COTS parts can be designed for the intense environment of space. From the high-level requirements architecture to the selection of specific hardware components and software design choices, followed by rigorous environmental testing of the design, radiation and other environmental hardening can be achieved with high confidence.
Cavender, Daniel↗
The PolCube CubeSat Polarimeter for Earth Science
PolCube is a 12U CubeSat + polarimeter instrument designed by NASA Langley and the Korea Astronomy and Space Science Institute (KASI) for Earth Science. PolCube is based on the PolCam polarimeter onboard the Korean Pathfinder Lunar Observatory (KPLO) that launched in August 2022. The objective of the PolCube instrument is to retrieve detailed fine-mode (pollution and smoke) and coarse-mode (sea-salt and dust) aerosol properties over the ocean for a range of light to heavy aerosol loadings using its polarimetric-imaging capability at multiple angles and wavelengths from 410 − 865 nm. An additional objective is to discriminate aerosols from thin clouds. We quantify the performance of aerosol and ocean remote sensing products from the PolCube polarimeter instrument using the Microphysical Aerosol Properties from Polarimetry (MAPP) remote sensing retrieval algorithm. PolCube’s accurate and high-resolution aerosol-retrieval products will provide unique spatial and temporal coverage of the Earth that can be used synergistically with other instruments, such as the PACE (Plankton, Aerosols, Clouds and Ecosystems) and GEMS (Geostationary Environmental Monitoring Spectrometer) mission to improve air-quality forecasting. We present the PolCube-MAPP retrieval algorithm, which used optimal estimation and artificial intelligence, as well as multiple powerful inherent optical property look-up-tables for the Earth’s aerosol, cloud, and hydrosol particles. We estimate that PolCube can retrieve total aerosol optical depth at 555 nm (AOD555) within ±0.068, fine-mode AOD555 within ±0.078, and fine-mode single-scattering albedo within ±0.036, where all uncertainties are expressed as one standard deviation (1σ).
Snorre Stamnes↗
On-Orbit Results of Pointing, Acquisition, and Tracking for the TBIRD Cubesat Mission
Since launch in May 2022, the TeraByte Infrared Delivery (TBIRD) payload on a 6U CubeSat has successfully demonstrated 100/200 Gbps laser communications and has transferred >1 TB in a pass from low Earth orbit to ground. To support the narrow downlink beam needed for high rate communications, the payload provides pointing feedback to the host spacecraft to precisely track the ground station throughout the 5-minute pass. This paper presents the on-orbit results of the pointing and tracking system for TBIRD, including initial acquisition and closed-loop tracking performance of 20–35 µrad RMS per axis. Results from on-orbit characterization of the transmit beam are also presented. Measurements of Tx/Rx alignment show stability within 20 µrad, ensuring that tracking on the uplink accurately points the downlink.
TBIRD↗
On-Orbit Demonstration of 200-Gbps Laser Communication Downlink from the Tbird Cubesat
Since launch in May 2022, NASA’s TeraByte Infrared Delivery (TBIRD) program has successfully demonstrated 100-Gbps and 200-Gbps laser communication downlinks from a 6U CubeSat in low-Earth orbit to a ground station. The TBIRD system operates during 5-minute passes over the ground station and has demonstrated an error-free downlink transfer of > 1 Terabyte (TB) in a single pass. This paper presents an overview of the architecture, link operations, and system performance results to date.
laser communications↗