Digital Commons Network^™

Flight Envelope Assessment Of Smallsat Aerocapture Trajectories At Venus And Mars, Jack A. Joshi, Rohan G. Deskmukh, Soumyo Dutta, Angela Bowes

Small Satellite Conference

Aerocapture is an increasingly studied orbit insertion concept for small satellite (SmallSat) missions beyond low Earth orbit (LEO). Compared to fully propulsive methods, aerocapture reduces the orbit-insertion propellant mass by approaching on a hyperbolic path and using the planetary atmosphere to reduce the vehicle’s velocity such that the final target orbit is achieved. This allows for an increase in payload mass delivered to orbit and a reduction in launch-to -orbit time. To analyze the feasibility at Venus and Mars, aerocapture flight envelope analysis is conducted by assessing the guidable trajectory space during atmospheric flight given entry conditions, vehicle properties, target …

Mo Services And Cfdp In Action On Ops-Sat, Dominik Marszk, David Evans, Tom Mladenov, Georges Labrèche, Vladimir Zelenevskiy, Vasundhara Shiradhonkar

Small Satellite Conference

OPS-SAT is a 3U CubeSat launched by the European Space Agency (ESA) on December 18, 2019. It is the first nanosatellite to be directly owned and operated by ESA. The spacecraft is a flying platform that is easily accessible to European industry, institutions, and individuals enabling rapid prototyping, testing, and validation of their software and firmware experiments in space at no cost and no bureaucracy. Conceived to break the “has not flown, will not fly” cycle, OPS-SAT has spearheaded many firsts in both space and ground segments. For instance, its uplink rate is four times higher than any ESA spacecraft; …

Radio-Source Tracker: Autonomous Attitude, Knowledge, And Recovery On A Radio Interferometric Swam, Erwan Rouillé, Baptiste Cecconi, Boris Segret

Small Satellite Conference

The development of satellite swarm technology offers new possibilities for space studies and comes with new challenges. Among them is the need for knowledge on the swarm topology and attitude, especially in the context of space based radio interferometry. This paper presents an algorithm that recovers the absolute swarm attitude without the need for an external system such as GNSS (Global Navigation Satellite Systems). This algorithm uses the imaging capability of a low frequency radio interferometer in order to function like a star-tracker using the main radio sources in the sky. The recovery of the source directions for the Lost-In-Space …

Machine Learning Image Processing Algorithms Onboard Ops-Sat, Shreeyam Kacker, Alex Meredith, Kerri Cahoy, Georges Labrèche

Small Satellite Conference

We discuss the deployment of image processing algorithms developed for BeaverCube-2, a project under development between the MIT Space Telecommunications, Astronomy, Radiation (STAR) Lab and the Northrop Grumman Corporation. The algorithms were uploaded to and executed on OPS-SAT, a 3U CubeSat owned and operated by ESA with a processing payload that allows rapid prototyping, testing, and validation of software and firmware experiments in space at no cost to the experimenter. Testing these algorithms onboard OPS-SAT significantly reduces risk for future on-orbit image processing missions such as BeaverCube-2. We focus on four image processing algorithms used for cloud detection: a luminosity-thresholding …

High-Fidelity Spacecraft Thermal Modeling: Synthesis Of Stk, Spenvis, Matlab, Simulink, And Thermal Desktop Using Model-Based Systems Engineering, Michael Halvorson, Jackson Cho, Sean Farkas, Landon Boyd, Nolan Cartier, Kasey Cole, Nicholas Deangelo, Tristian Edwards, Tanner Middleton, Cole Moquin, Ben May, William Kilpatrick, Matt Taylor, Henry Tsai, Colin Cameron, Nicholas Tsolas

Small Satellite Conference

Verification and Validation (V&V) by analysis for required spacecraft Heater Wattage (HW) and Radiator Area (RA) is a rigorous, iterative procedure highly dependent on spacecraft areas, surface absorptivity, surface emissivity, orbital position, orbital attitude, and operational heat generation. The Alabama Burst Energetics eXplorer (ABEX) mission adopts a Model-Based Systems Engineering (MBSE) approach to analysis wherein model strengths and weaknesses are considered synergistically and integrated using SysML parametric and structural diagrams to create a System of Models (SoM). In this work, a procedure for comprehensive spacecraft thermal modeling is detailed using MBSE-centric Modeling and Simulation (M&S) practices. The SysML model is …

Small Satellite-Sized Hypersonic Inflatable Aerodynamic Decelerators For Interplanetary Science Missions, Shelly C. Mann, Angela Bowes, Rohan G. Deshmukh, Soumyo Dutta

Small Satellite Conference

To make the most of ridesharing opportunities, small satellite (SmallSat) mission designers endeavor to pack as much payload into a SmallSat-class form factor as possible. The mass and volume constraints of this smaller vehicle class present a challenge for interplanetary mission sets that require a means of achieving orbit insertion at their destination of interest. For a fully propulsive orbit insertion design, this may translate to the propellant mass being a significant fraction of the overall vehicle mass and prolonged insertion time. Aerocapture is a single quick maneuver that can significantly reduce the required propellant mass for orbit insertion. Because …

Windcube: A Cubesat Thermospheric Wind Instrument Utilizing Fabry-Pérot Interferometry, Scott Sewell, Qian Wu, Pat Zmarzly, Andrew Carlile, Alice Lecinski, Damon Burke, Mitch Jeffers, Michael Mcguirk, Caitlyn Quinn, Nir Patel, John Sobtzak, Ruth Lieberman, Karen Holland

Small Satellite Conference

WindCube is a 6U CubeSat mission selected for implementation through NASA’s HFORT program. Starting in 2022 and following ~36 months of development, integration and testing, the spacecraft will operate for ~12 months in low earth orbit to study the influence of thermospheric winds on the earth’s ionosphere. Its scientific payload is a limb viewing Fabry Pérot Interferometer (étalon) specially designed to fit into a 10cm x 10cm cross-sectional assembly. WindCube will make global maps of wind speed derived from the doppler shifted emission of the 630.0nm oxygen line (¹D > ³P), at altitudes near 250km. Projected performance includes …

The Nasa Cyclone Global Navigation Satellite System Smallsat Constellation, Christopher Ruf, Hugo Carreno Luengo, Clara Chew, Mahta Moghaddam, Derek Posselt, Juan Crespo, Zhaoxia Pu, April Warnock

Small Satellite Conference

The NASA Cyclone Global Navigation Satellite System (CYGNSS) mission consists of a constellation of eight microsatellites launched on 15 December 2016 into a common circular orbit at ~525 km altitude and 35 deg inclination. Each observatory carries a four channel bistatic radar receiver to measure GPS signals scattered by the Earth surface. Over ocean, near-surface wind speed, air-sea latent and sensible heat flux, and ocean microplastic concentration are derived from the measurements. Over land, near-surface soil moisture and inland water bodies extent are derived. The measurements penetrate through all levels of precipitation and most vegetation due to the 19 cm …

High-Energy Proton Testing Of Sensitive Electronics For Use On Modular Infrared Molecules And Ices Sensor (Mirmis) Instrument, S. Thirumangalath, E. Briede, A. Näsilä, V. Gupta, C. Boatella, H. Wojciech, V. Kletzl, R. Trops, N. E. Bowles

Small Satellite Conference

The Comet Interceptor (CI) mission is ESA's first "F" class mission, selected in June 2019. This mission consists of three spacecraft: Spacecraft A (main spacecraft), Spacecraft B1 (supplied by the Japanese space agency JAXA), and Spacecraft B2. In this paper, we highlight the Modular Infrared Molecular and Ices Sensor (MIRMIS) instrument, which is integrated into the CI Spacecraft A's scientific payload. In addition to hardware contributions from Finland (VTT Finland) and the UK (University of Oxford), the MIRMIS instrument team includes members from the University of Helsinki and NASA's Goddard Space Flight Centre. MIRMIS covers the spectral range of 0.9 …

A 1.5u Size 350-950nm Hyper-Spectral Camera Optical And Mechanical Design Without Mtf Degradation In The Temperature Range -100 To 300 ℃, Hanik Kim, Hyochoong Bang

Small Satellite Conference

1.5U sized hyper-spectral camera has been developed to be equipped in three-unit sized CubeSat. Even though this payload is developed for Cubesat, the optical and mechanical structure is designed for harsh environmental conditions to be equipped in the other satellite types. The optical performance of the payload is assessed using Modulation Transfer Function (MTF) in 350–950nm. The MTF is optimized with volume and MTF requirement constraints by CODE-V in the wavelength range. The constraints are 1.5U volume, the curvature ranges of fabricable aspheric design, fabrication errors, and the temperature variation in space. The 1.5U size constraint is defined to 100mm✕100mm✕145mm …

Design And Performance Of The Aero-Vista Magnetometer, Nicholas Belsten, Candence Payne, Rebecca Masterson, Kerri Cahoy, Mary Knapp, Tobias D. Gedenk, Frank D. Lind, Philip J. Erickson

Small Satellite Conference

We describe the design and performance of the magnetometer instrument for the CubeSat mission AERO-VISTA. AERO-VISTA requires in-situ vector magnetic measurements with magnetic precision and repeatability better than 100 nT at a minimum rate of 10 Hz. Our magnetometer system uses the three-axis Honeywell HMC1053 anisotropic magnetoresistive (AMR) sensor. As built, our instrument exhibits intrinsic magnetic noise better than 10 nTrms from 0.1 to 10 Hz, though self-interference effects degrade performance to about 50 nT to 200 nT uncertainty. The analog and mixed signal portion of each magnetometer occupies about 8 square centimeters of circuit board space and draws about …

Low Cost Sar Antenna With Wide Swath And High Ground Resolution, Hirobumi Saito, Kosei Ishimura, Takashi Tomura, Jiro Hirokawa

Small Satellite Conference

This paper describes our developments of SAR (Synthetic Aperture Radar) antennas for low-cost, wide swath and high ground resolution (0.5-0.25m). The antennas are 1D deployable, plane slot array antennas with a wide elevation beam pattern. RF is fed to each panel with a novel patented technology, non-contact waveguide system between panels. These types of SAR antennas make feasible a newly proposed DiskSat with SAR sensor system. The SAR antenna 600MHz bandwidth in X band for 0.5m SAR resolution is made from carbon fiber reinforced plastic (CFRP) for light weight and thermal stability. Furthermore, range resolution improves with wider frequency bandwidth. …

Binar Space Program: Binar-1 Results And Lessons Learned, Fergus Downey, Stuart Buchan, Benjamin Hartig, Daniel Busan, Jacob Cook, Robert Howie, Phil Bland, Jonathan Paxman

Small Satellite Conference

The Binar Space Program is a recently formed space research and education group part of the Space Science and Technology Center at Curtin University in Western Australia. Recently launching the first CubeSat from the state, Binar-1, the team is making steps towards creating a sustainable mission schedule for research and education. The Binar-1 mission primary objective was to demonstrate the custom designed systems made by PhD students and engineers at the university. The main technology being demonstrated was the integrated Binar CubeSat Core, which compacted the Electrical Power System, Attitude Determination and Control System, and flight computer system into 0.25U. …

Initial In-Orbit Operation Result Of Microsatellite Hibari: Attitude Control By Driving Solar Array Paddles, Kei Watanabe, Hiroyuki Kobayashi, Naoki Kawaguchi, Shogo Nerome, Yuki Amaki, Fumitaka Sagawa, Soichi Sato, Kenichiro Takahashi, Yuta Sasagawa, Kiyona Miyamoto, Yoichi Yatsu, Toshihiro Chujo, Saburo Matunaga

Small Satellite Conference

We have developed a 50kg class microsatellite "HIBARI". The mission of this satellite is to demonstrate a novel attitude control method for microsatellites which is called “Variable Shape Attitude Control (VSAC).” VSAC is a method using anti-torque by driving variable shape structures. HIBARI has four drivable solar array paddles, and will demonstrate VSAC.

The development of HIBARI began in 2019, and it was injected into orbit in November 2021 under the Innovative Satellite Technology Demonstration Program led by JAXA. Currently, HIBARI has completed its critical phase and paddle deployment phase, and is conducting paddle drive experiments in orbit. In paddle …

Tartan Artibeus: A Batteryless, Computational Satellite Research Platform, Brad Denby, Emily Ruppel, Vaibhav Singh, Shize Che, Chad Taylor, Fayyaz Zaidi, Swarun Kumar, Zac Manchester, Brandon Lucia

Small Satellite Conference

TTartan Artibeus (TA1) is the first batteryless, computational pocketqube satellite; its open-source hardware and software launched into low-Earth orbit (LEO) in January 2022. TA1 is a 1p (125 cm³) pocketqube built around the Tartan Artibeus Bus (TAB), which connects independently-designed modules into a batteryless, computational satellite. In TA1, TAB incorporates an electrical power supply (EPS) module that harvests solar energy into a supercapacitor, a fault-tolerant command and data handling (C&DH) module, a radio-communication module, and a configurable computational payload module.

The open-source hardware [17] and software [18] of TA1 supports independently designed modules oblivious to the batteryless nature …

Spectral Ocean Color (Spoc): Lessons Learned From The University Of Georgia Small Satellite Research Laboratory's First Satellite, Sydney Whilden, Deepak Mishra, David L. Cotten, Nicholas Neel

Small Satellite Conference

In October 2020, the University of Georgia Small Satellite Research Laboratory launched its first CubeSat, a 3U Earth-observation mission designed to collect multispectral data from Georgia’s coastal environments for UGA’s Center for Geospatial Research to make recommendations on environmental conservation, care, and use. SPOC successfully detumbled, but after approximately a month in orbit, a coronal mass ejection (we speculate) caused us to lose contact. Despite our disappointment at the loss of SPOC, we are leveraging the lessons learned for our upcoming missions. These lessons can be categorized in four principal areas: software (flight and payload), mission operations, testing, and educational …

The Colorado Ultraviolet Transit Experiment: The First Dedicated Ultraviolet Exoplanet Mission, Arika Egan, Kevin France, Nicholas Nell, Nicholas Decicco, Ambily Suresh, Rick Kohnert, Brian T. Fleming, Stefan Ulrich

Small Satellite Conference

The past few years of space mission development have seen an increase in the use of small satellites as platforms for dedicated astrophysical research; they offer unique capabilities for time-domain science and complementary advantages over large shared resource facilities like the Hubble Space Telescope, including: (1) low cost and relatively quick development timelines; (2) observing strategies dedicated to niche but important science questions; and (3) ample opportunity for students and early career scientists and engineers to be involved on the front lines of space mission development. The Colorado Ultraviolet Transit Experiment (CUTE) is a NASA-supported 6U CubeSat assembled …

Data Validation Of The Nasa Time-Resolved Observations Of Precipitation Structure And Storm Intensity With A Constellation Of Smallsats (Tropics) Pathfinder Microwave Radiometer, Amelia Gagnon, Samantha Hasler, Juliana Chew, William Blackwell, Vince Leslie, Kerri Cahoy

Small Satellite Conference

Launched in June 2021, the TROPICS Pathfinder CubeSat has a microwave radiometer payload sensitive to the frequencies for observing precipitation, humidity, temperature, and cloud ice. The observed brightness temperatures must be compared to a data set of ‘known’ quality to validate the measured data across all channels of the microwave radiometer. This research explores validating TROPICS Pathfinder data against reanalysis data to determine the quality of the provisional TROPICS Pathfinder data product, with an eye for the future of comparing against other microwave radiometer measurements. Validation involves comparing Pathfinder data to ERA5 reanalysis data by using the Community Radiative Transfer …

The Sum Of The Parts: Lessons Learnt From Designing And Building A 3.7 Metre S/X-Band Antenna, Kerry Clapham, Robin Mcneill, Chris Hann

Small Satellite Conference

A redundant 2.2m Cossor weather radar was made available to us. After some initial experimentation tracking NOAA weather satellites, we challenged ourselves to convert it into a reliable high performance S/X-Band Station suitable for supporting LEO missions. A new reflector, horn feed, RF chain, motors and gearing were specified, designed and installed during the upgrade. Modern control software was written to command the new antenna.

We found that designing and assembling such a system is educational at a both a systems and component level. In particular, at X-Band we found there is little margin for errors where many small details, …

Comparison Of The Low-Cost Sun Sensors Of The Source And Eive Cubesats, Nils Pentke, Joelle Schaefer, Timon Karl-Heinz Schwarz, Markus T. Koller, Steffen Gaisser, Sabine Klinkner

Small Satellite Conference

Sun sensors are commonly used attitude determination equipment which measure a spacecraft’s attitude relative to the sun. Multiple types of low-cost sun sensors were developed for the SOURCE and EIVE CubeSats. The SOURCE sun sensors consist of single photodiodes which are placed in a one-sensor-per-face as well as a pyramid arrangement. EIVE employs digital vector sun sensors based on quad-pin photodiodes. The SOURCE sun sensors in the one-sensor-per-face arrangement archive an accuracy of <10° while the pyramid arrangement accomplishes an accuracy of <7.5° without and <5° with calibration. EIVE’s vector sun sensors offer an raw accuracy of 3°±5°. Multiple calibration approaches are presented with the best results leading to an accuracy of 0.7±3°. A direct comparison between the SOURCE and EIVE sensor types and configurations can be drawn since the same test bench was used to measure all sensors. The objective of this paper is to present and compare the different sun sensor concepts and their results.

Design And Assembly Of An Inexpensive Cleanroom For Cubesat Teams, Alexander Leaf, Thomas Ganley, Priya Manavalan, Priya Grewal, Helena Ard, Aditya Shah, Carlos F. Lange

Small Satellite Conference

As space missions become more accessible to student teams through the spread of the CubeSat standard, there is an obvious desire for inexpensive clean spaces for satellite assembly. However, commercially available cleanrooms are costly and may not fit in limited spaces. We present our results and processes from the design, construction and testing of a low-cost cleanroom made of materials readily available at hardware stores.

Our cleanroom was designed to meet ISO 8 or better standards, based on results from previous work by other groups (Johnstone et al., 2007)¹ and requirements for our CubeSat missions. Overall, $2,733.51 CAD was …

Development Of A Simulation Framework For Cubesat Performance Modeling, Mark A. Kurtz, Andrew S. Keys, Kirk W. Johnson

Small Satellite Conference

Space systems are notoriously difficult to develop due to the nature of the environment in which they must operate. Designers have only a limited window to ensure systems will function as intended, placing a high importance on testing. This paper discussed the ongoing development of a simulation framework to support Hardware-in-the-Loop (HIL) testing of CubeSat subsystem hardware. This work is being conducted at the Air Force Institute of Technology (AFIT) in support of the institution’s CubeSat program. The simulation framework is organized into the classic spacecraft subsystems. Each of these subsystems will support a software model and interfaces for the …

Open-Source Software Suite For Small Satellites: C2a (Command Centric Architecture), S2e (Spacecraft Simulation Environment), And Wings (Web-Based Interface Ground-Station Software), Ryo Suzumoto, Satoshi Ikari, Kota Kakihara, Takayuki Hosonuma, Kanta Yanagida, Yuta Sakamoto, Masahiro Fujiwara, Hirotaka Kondo, Kentaro Enokida, Toshihiro Suzuki, Yoshinari Gyu, Hirotaka Sekine, Tomoki Mochizuki, Yutaro Ito, Ryu Funase, Shinichi Nakasuka

Small Satellite Conference

No abstract provided.

Simulation Of Single Gimbal Control Moment Gyroscopes (Sgcmg) Cluster For Microsatellite Maritime Surveillance Mission, Ki Hwan Keum, Regina Lee

Small Satellite Conference

The potential for agile missions for small satellites exists through development of single gimbal control moment gyroscopes (SGCMG). An SGCMG cluster comes with additional complexity and volume requirements, but efforts in their development have reduced their overall size while providing higher torque over similarly sized reaction wheels. In this paper, we present a feasibility study of a small satellite using a small volume pyramid SGCMG cluster for coastline monitoring through Simulink. Two realistic torque profiles for sweeping capture of complex coastlines within one minute were generated using STK, requiring maximum torques of 0.190 and 0.218 Nm and rapid slew rate. …

Development Of A Prelude Satellite Equipped With Electric Field And Plasma Measurement Sensors Based On Statistical Evaluation Of Seismic Precursors Using Artificial Vlf Radio Waves Obtained From In-Orbit Observations, Tomoyuki Iida, Masahiko Yamazaki, Masashi Kamogawa

Small Satellite Conference

In this paper, we focus on the artificial VLF radio wave and show the result of the evaluation of the signal intensity decrease by the effect of ionospheric fluctuation, which is regarded as a sign phenomenon of earthquake occurrence. This paper also describes the mission design of Prelude (Precursor electric field observation CubeSat demonstrator) which is aiming at elucidation of the precursory mechanism of earthquake, and the development situation of hybrid sensor (electric field and plasma measurement) which is a mission instrument.

We focused on the artificial VLF wave, in which the electromagnetic wave itself does not affect the ionosphere, …

A High Precision Accelerometer With An Optical Readout, Abdulrahman Alfauwaz, Sasha Buchman, John Lipa

Small Satellite Conference

Geodesic missions require precise accelerometers to improve the knowledge of the reference frame used for defining position coordinates, better calculating orbit parameters, and mapping the Earth’s gravitational field. Although space environment disturbances are typically relatively small, they generate large and significant accumulated drift errors over time. We describe a low noise accelerometer design that overcomes many of the limitations of existing designs and is capable of providing precision drag-free control in vehicles with thrusters. Furthermore, it can be used with some modifications, including active thermal control, to detect gravitational waves in an interferometer using drag-free satellites. Due to its flexible …

Spoac And Hinge Integrated Msac: Non-Holonomic Attitude Control Systems For Spacecraft, Abbas Bataleblu, Elena Fernández Bravo, Vedant, James T. Allison

Small Satellite Conference

Two novel spacecraft attitude control system technologies are introduced that both rely on the same nonholonomic control trajectory concept but that utilize distinct system implementations. The first of these two technologies is Hinge Integrated Multifunctional Structures for Attitude Control (MSAC), which is a new attitude control system that utilizes deployable panels to provide a spacecraft with both fine pointing and large angle slewing attitude control capabilities. Given its potential for high reliability and these control capabilities, Hinge Integrated MSAC is a viable alternative to conventional momentum exchange-based attitude control systems. This study details the Technology Readiness Level (TRL) advancement for …

Methods For Data-Centric Small Satellite Anomaly Detection And Fault Prediction, Joseph Melville, Joel B. Harley, Michael Lopez, Michael Crabtree, Seth Lacy

Small Satellite Conference

Autonomy can increase reaction speed, flexibility, and accuracy of satellite operations, especially in uncertain environments caused by delayed communication and/or adversarial conditions. An increased focus on small satellites makes the development of satellite autonomy even more salient, given fewer operators per satellite.

Anomaly detection automates satellite health monitoring, ensuring it functions as designed. This is typically achieved using various forms of recurrent neural networks (RNN). While many of these model-based works show promise, a majority use simulated data or assume lossless communication. In contrast, raw satellite telemetry often has dropped packets, sampling frequency mismatches, noise from electrical systems and radiation, …

Cubesat Single-Photon Detector Module For Performing In-Orbit Laser Annealing To Heal Radiation Damage, Nigar Sultana, Joanna Krynski, Jin Gyu Lim, Vadim Makarov, Thomas Jennewein, Logan M. Power, John Floyd, Michael Lembeck, Paul Kwiat

Small Satellite Conference

Silicon-based single-photon avalanche photodiodes (SPADs), widely considered for satellite-based quantum communications, suffer a constant increase of dark count rate (DCR) from radiation-induced proton displacement damage in their active areas. When this accumulated damage causes the DCR to exceed a certain threshold (for example, 10,000 counts per second), the SPADs become unreliable for quantum communications, limiting mission lifetime. Previous ground experiments showed that radiation-induced DCR of synthetically irradiated SPADs could be significantly improved by high-power laser annealing, a localized heating of SPADs’ active areas using a focused laser beam. The next step is therefore to demonstrate realtime laser annealing on constantly …

Fabrication Of Catalyst Infused Filament For 3-D Printing Of Hybrid Rocket Fuels, Kurt C. Olsen, Stephen A. Whitmore, Brayden Barton

Small Satellite Conference

Additive manufacturing changes the electrical breakdown properties of certain 3D-printed thermoplastics like Acrylonitrile Butadiene Styrene (ABS), and when printed materials are presented with a high-voltage electrical potential, electrical-arcing along the layered surface pyrolizes the material. This electrostatic property has been harnessed to develop a High-Performance Green Hybrid Propulsion (HPGHP) technology that has capability for reliable start, stop, and re-ignition. HPGHP operates reliably using gaseous oxygen (GOX) as the complementing oxidizer; but has experienced reliability and ignition latency issues when GOX is replaced by Nytrox, a higher-density blend of nitrous oxide and GOX. Ignition issues are overcome by infusing small amounts …