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A Modular Command And Data Handling System Concept For Small Satellites, Abdullah Alsalmani, Mohammed Almehrezi, Abdul-Halim Jallad

Small Satellite Conference

The increasing demand for high-performance computer systems on board space missions applications, such as artificial intelligence and machine learning, are drivers of the need for higher on-board command and data handling specifications. Consequently, a modular Command and Data Handling Subsystem (CDHS) is required in order to manage the complexity of future CDHS hardware. Some systems have applied a similar approach; however, they either focus on large scale satellites or have a certain level of complexity that limits their usage by learners. This paper proposes a modular Command and Data Handling System that includes several layers providing more flexibility in design …

Derivation Of Transfer Function Of A Two-Degree-Of-Freedom Damped System With Base Excitation, Marco Villa, Hilaryl Au, Amir Damansouz, Min Kee Goh

Small Satellite Conference

The derivation of a closed-form expression for the acceleration transfer function of a two-degree-of-freedom (2DOF) spring-damper system with a base excitation vibration input is presented in this paper. An analytical example was solved with a finite element model to verify the closed-form expression. In the current small satellite industry, dynamic coupling between the launch vehicle and the deployer/satellite assembly is that of interest. This coupling can amplify the launch loads into the deployer/satellite assembly. In this paper, analytical method is used to derive the two-degree-of-freedom system response of a mass, spring, and damper system to a base excitation. After achieving …

Lessons Learned From The Application Of Risk Management Process To Sport Cubesat Project, Pedro Cabral, Linelcio Paula, Lidia Shibuya Sato, Willer Gomes Dos Santos, Loures Da Costa

Small Satellite Conference

The project implementation of a CubeSat System may have many risks which negatively impact aspects such as technical performance, system safety, cost, and schedule. To increase mission success, we may apply a risk management process. The Scintillation Prediction Observation Research Task (SPORT) CubeSat Project is a scientific mission to address the space weather problem of understanding the preconditions leading to equatorial plasma bubbles. SPORT is an international partnership between institutions from the United States of America and Brazil. The present research focuses on risk management activities from the point of view of the ITA Space Center in Brazil. There is …

S-Band Qpsk Transmitter For Picosatellites, Jay Deorukhkar, Peter W. Pachowicz

Small Satellite Conference

The small satellite field has become popular amongst academia, amateur satellite (AMSAT) community, and commercial businesses due to the miniaturization of components and smaller form factors. Specifically, the picosatellite structure has gained attraction for its size and affordability of launch fees. However, the size constraint makes it difficult to generate power and limits the transmit power for downlink. Therefore, efficient data modulation is key to providing high data downlink rates. Also, the typical VHF and UHF frequency spectrum used for satellites is getting congested. Hence, the higher frequency bands such as S-band and X-band are gaining attraction and offer higher …

Gosa – An European Offshore Spaceport For Microlaunchers & Small Satellites, Andreas Stamminger, Dieter Birreck, Christian Boehmer, Oliver Spalthoff, Heiko Felderhoff, Arne Gausepohl, Andreas Nil, Heiko Rinderle, Sabine Von Der Recke

Small Satellite Conference

Europe profits from the boom of the New Space industry, a growing number of startups and small and medium-sized companies offering space infrastructure and space-based services. With HyImpulse, ISAR Aerospace, Orbex, PLD, Rocket Factory Augsburg and Skyrora, several promising microlauncher companies are located in Europe. An offshore spaceport with a well-connected on-shore site in Northern Germany enabling launch of small satellites to Polar or Sun Synchronous Low Earth Orbits provides the opportunity for this growing New Space region to develop a cluster in a future market and thereby create an economic eco system, which spans everything from the satellite manufacturer …

Solar Polar Explorer Enabling Launch Technology, Warren Frick, Don Hassler, John Andrews

Small Satellite Conference

To unlock mysteries of our sun, Southwest Research Institute (SwRI) and its propulsion system partner Northrop Grumman confronted the challenge of getting sensors to the sun for detailed observation on a limited budget. SwRI’s proposed Solaris mission paired a solar observatory with the Orion 38 and Orion 50 XLT Solid Rocket Motor (SRM)-based stages for a gravity-assisted slingshot maneuver around Jupiter.

The NASA Heliophysics Medium Explorer (MIDEX) program selected Solaris in 2020 for a concept study that ran through 2022. Solaris aimed to conduct high-latitude observations of the Sun’s south and north regions to resolve our understanding of how their …

Advancements In The Epsilon Launch Vehicle's Rideshare Capability And Future Missions, Shin Yamada, Makoto Horikawa, Hitomi Izumi, Kazuhiro Yagi, Takayuki Imoto

Small Satellite Conference

Fifth Epsilon launch vehicle (Epsilon-5) with Innovative Satellite Technology Demonstration-2 was successfully launched from JAXA Uchinoura Space Center in Kagoshima, Japan on November 9, 2021. Successful injection of nine satellites with high accuracy demonstrated the capability of Epsilon launch vehicle for rideshare missions of various satellite sizes. The new Epsilon Satellite Mount Structure-II (ESMS-II) and an adapter was developed to launch more satellites.

In the paper, we first introduce Epsilon launch vehicle and its multi-launch capability. Then, we describe the mission design of Epsilon-5 and rideshare specific configuration. Finally, we mention the rideshare opportunity provided by Epsilon launch vehicle in …

Path To The First Flight Of The Sl-Omv, Christopher Loghry, John Howat, James Leak

Small Satellite Conference

The growing number of Small Launch Vehicles (SLV) will lower the cost of space access in the coming years, but many challenges remain for CubeSats. CubeSats still have the concerns and obstacles as a secondary payload on a larger rocket as they do on a small rocket such as desired orbital location and constellation phasing without using on-board propulsion or time-consuming differential drag.

Many of these challenges can be met using the Small Launch Orbital Maneuvering Vehicle (SL-OMV). The SL-OMV is a propulsive adapter that can be used to distribute CubeSat payloads with different orbital parameters than the primary payload …

18 Sds Small Satellite Support, Cynthia Wilson, Diana Mckissock

Small Satellite Conference

In addition to its primary mission, the U.S. Space Force’s 18th Space Defense Squadron (18 SDS) provides orbital data and services at no cost to satellite owners and operators worldwide in the interests of spaceflight safety. We track all artificial objects in Earth orbit, generate orbital elements and forecast reentries, and publish the data on the website, www.space-track.org. In concert with our sister squadron, the 19th Space Defense Squadron (19 SDS), the data produced by the 18 SDS is used to predict close approaches to support collision avoidance by satellite operators including small satellite owners. Of note, however, neither the …

Multiconfiguration Loads Analysis For Missions With An Uncertain Rideshare Manifest, Erik C. Mellquist, Barbara Braun, Derek Ring, Tom Hiel, David Stephens

Small Satellite Conference

Rideshare or “multi-manifest” missions – where several smaller “rideshare” spacecraft are launched together, usually with a larger “forward” spacecraft – are becoming increasingly common. In many cases, the properties or configuration of the rideshare spacecraft are not well-defined during initial launch manifesting and may not be finalized until a few months before launch. In this paper, a multiconfiguration loads analysis (MLA) process is presented that can enable flexibility in the mission manifesting process by allowing for uncertainty in the final rideshare configuration, including late manifest changes or swaps, without requiring additional loads analyses to those specified in the Load Cycle …

A Small Launch Per Month? - 2022 Edition Of The Annual Industry Survey, Carlos Niederstrasser

Small Satellite Conference

While many, including this author, have publicly stated that the number of small launch vehicles under development is not sustainable, investor money continues to flow into this market segment. New announcements of multimillion funding rounds are occurring several times a year. Even the challenges posed by the worldwide COVID pandemic, have not slowed down this trend. In 2015 we first presented this survey at the AIAA/USU Conference on Small Satellites1, and we identified twenty small launch vehicles under development. By mid-2022 eleven vehicles in this class were operational, 47 were identified under development, and another 47 more were potential new …

Positionality: The Interplay Of Space, Context And Identity, Rebecca Y. Bayeck

Instructional Technology and Learning Sciences Faculty Publications

This article considers the way in which positionality shifts and is formed during a cross-cultural study to reveal the complexity of the insider-outsider status. As a researcher in a male-dominated game setting, I reflect on the research process and my interactions with participants to show the interplay of space, context, and identity in shaping a researcher’s status. I discuss the process of gaining access to the research site and participants, and data collection in relation to space, context, and identity. The interaction of my identities with space, and context informed my status at various moments. This interplay constructs a complex …

Development Of Ascent Propellant Thrusters And Propulsion Systems, Mackenzie Kilcoin, Daniel Cavender, Tomas Hasanof, Michael Zaluki, Tim Mckechnie, Corinne Sedano, Hunter Williams

Small Satellite Conference

Since the 1960s, hydrazine technology has dominated the market of propulsion technology by providing reliable performance on a wide variety of spacecraft. Efforts to replace hydrazine with a higher-performance and safer alternative have engaged numerous emerging technologies in the industry to mature. ASCENT propellant, also known as AF-M315E, is an example of one such green propellant. Initially developed to provide a safer handling environment than hydrazine, ASCENT offers higher overall performance than a hydrazine equivalent by creating more heat during ignition. The next generation of propulsion technology, based on ASCENT propellant, produces a higher impulse and energy density, expanding the …

Pre-Flight Testing Results Of Multiple Water Propulsion Systems - Resistojet And Ion Thruster For Smallsats, Jun Asakawa, Hiroyuki Koizumi, Kazuya Yaginuma, Yuichi Nakagawa

Small Satellite Conference

This paper described re-flight flight testing results of the miniature water propulsion system combined an ion thruster and resistojet thrusters which is to be demonstrated on-orbit by JAXA’s program named Innovative Satellite Technology Demonstration-3. The unified propulsion system has a huge potential to expand micro/nano-spacecraft utilization and decrease the risk of debris.

Design And Testing Of A 100-Mn Class Water Micropropulsion System Using Wire-Fed Magnesium Combustion, Mariko Akiyama, Rucheng Zhang, Hiroyuki Koizumi, Kimiya Komurasaki

Small Satellite Conference

In this study, the brand-new micropropulsion system is introduced to cover the thrust performances shorthanded by the exiting systems. It uses water as an oxidizer and a magnesium wire as a fuel. We constructed the lab-scale model of this micropropulsion system, and conducted several experiments to obtain the reaction rate of magnesium wire in water-vapor flow. Reaction rate showed almost proportional dependence on water-vapor mass flow rate. We constructed the revised version of lab-scale model, and will continue experiments for detailed analysis of combustion.

Twin Ion Engine Demonstration For Small Spacecraft Applications, Michael Tsay, Riley Terhaar, Kyle Emmi, Carl Barcroft

Small Satellite Conference

Two iodine-fueled, second-generation (Gen-2) “BIT-3” gridded RF ion propulsion systems were successfully demonstrated in proximity. The test units feature a host of upgrades from the flight models delivered to Lunar IceCube and LunaH-Map 6U Cube missions onboard NASA’s SLS Artemis 1. Each Gen-2 BIT-3 system is capable of 1.1 mN thrust, 2,150 sec specific impulse and 31.7 kN-sec total impulse, at 75W maximum power input. The twin engines, separated by a mere 6.5 cm, successfully performed simultaneous startup, sequential startup, and throttling, all without noticeable plasma interference. Onboard telemetry confirms that both thruster and cathode pairs operated nominally, and both …

Additively Manufactured Rcs For Small Satellites And Landers, James F. Horton, Joseph A. Helali, Mela H. Fung, Bryan M. Webb, Stephen A. Yows, William S. Brown, Shawn D. Buckley, William F. Sack

Small Satellite Conference

After a fifty year absence, NASA’s return to the lunar surface under the Artemis Program – for long term human exploration and utilization – is driving commercial and academic opportunities for small satellite and small lander platforms (e.g., Commercial Lunar Payload Services program – CLPS). Bipropellant thrusters are a reliable, low risk, and flight proven method for the propulsion and attitude control that is required for complex maneuvers such entry, descent, and landing (EDL) or in-space proximity operations. However, due to the increasingly competitive commercial spaceflight market in the last decade, satellite subsystems must also be affordable to buy their …

A Miniaturized Hydrogen Peroxide/Abs Based Hybrid Propulsion Systems For Cubesats, Tyson K. Smith, Zachary Lewis, Kurt Olsen, Ryan Thibaudeau, Stephen A. Whitmore

Small Satellite Conference

The Space Dynamics Lab is developing a prototype "green" hybrid prototype propulsion system for SmallSats. The system is based on Utah State's patented High Performance Green Hybrid Propulsion (HPGHP) technology. HPGHP leverages unique dielectric breakdown properties of 3D-printed acrylonitrile butadiene styrene (ABS), allowing re-start, stop, and re-ignition. HPGHP works most reliably using gaseous oxygen (GOX) as the oxidizer, but has experienced ignition reliability and latency issues when replaced by high test hydrogen peroxide (HTP). This deficiency results from HTP's high decomposition energy barrier. Tests show that noble metal catalysts like platinum on alumina are effective at decomposing 90% HTP in …

Propellant Management Of Water-Based Microthruster For Suborbital 0g Testing, Katherine Fowee Gasaway, Steven Pugia, Alina Alexeenko, Anthony Cofer

Small Satellite Conference

Size and power are primary limitations on nanosat missions, especially for propulsion, attitude control, or formation flight. New micropropulsion systems that are smaller, lighter, and less power expensive are required for versatile nanosats for cislunar and interplanetary missions. The Film-Evaporation MEMS Tunable Array (FEMTA) is water-based microthruster for CubeSat attitude adjustment that has been developed at Purdue University. FEMTA will provide an attitude control system for microsatellites that uses < 1 W of power in < 0.5 U of volume. The nozzles on FEMTA use heaters at the base of micro-capillary channels to induce film-evaporation, creating a highly controllable, low-power thrust. The novel capillary action thruster also requires a novel liquid 0G propellant management system. The FEMTA 0G propellant management system is a vapor pressure driven pump. It is self-regulating, does not rely on gravity, and does not require complex pressurization systems, making it suitable for microsatellite applications. The system uses a low vapor pressure fluid pressurant to apply a passive, constant deforming pressure upon a diaphragm that separates the pressurant from the propellant. The ratio of specific volume between the pressurant and the propellant is high enough that, as propellant is expended, the diaphragm compresses as the pressurant expands to fill the volume of the spent propellant. As part of the NASA Space Technology Research, Development, Demonstration, and Insertion (REDDI) program, the FEMTA 0G propellant management system is set to be tested during a suborbital Blue Origin New Shepard flight. In preparation for a 2023 launch, an experiment to test the propellant management system has been designed and built and engineering tests have been performed.

Design And Optimization Of An Autonomous Constellation Of Small-Satellites For Leo And Beyond, Mohammed Irfan Rashed, Hyochoong Bang

Small Satellite Conference

The speedy data reception with useful applications such as disaster management remains to be need of the hour. This paper addresses the major concerns relating to deployment and control of the larger small satellite (mainly cubesats) constellations in LEO by determining their relative position and velocity errors under certain acceptable limits with collision avoidance techniques. The article will also discuss the importance of Inter-satellite link to significantly to strengthen the satellite tracking and their data sharing speeds. The issue of optimal dispatch of the satellites by optimizing the constellation size is detailed though observing and controlling the orbits using a …

Thermal Modeling Of Femta Micropropulsion System For Cubesat Attitude Control, Florian Alexander Hoeft, Steven Pugia, Alina Alexeenko

Small Satellite Conference

Nano and pico-class satellite platforms such as 1U CubeSats, PocketQubes, and ThinSats introduce unique power and volume constraints on propulsion systems. The Film-Evaporation MEMS Tunable Array(FEMTA) microthruster is one compact, low-power technology that is well suited for these applications. FEMTA thrusters are microfabricated on 1 cm x 1 cm x 1 mm silicon and glass chips. Each chip contains an array of micrometer-scale capillaries which are electrically heated to vaporize the liquid propellant and generate controlled thrust. Sixth generation FEMTA devices have been demonstrated to produce greater than 300 microNewton of thrust per 1 Watt of electrical power at 90 …

Test And Evaluation Of Grissom-1 Cubesat Communication Subsystem, Michael J. Bittle, Andrew S. Keys

Small Satellite Conference

The Grissom-1 mission (GM1), slated to launch in September 2022, is the first in a series of 6-Unit CubeSat satellites built and operated by the Air Force Institute of Technology’s (AFIT’s) Center for Space Research and Assurance (CSRA). Mission success for GM1 depends on a comprehensive campaign of testing and assessment to confirm the components, design, and assembly of all systems and subsystems within the satellite. This paper specifically focuses on the testing and analysis of all communication links between the spacecraft, the ground system, and the Satellite Operations Center (SOC) being hosted at the Air Force Instituteof Technology at …

Design Proposal And Realization Of An Academic-Nanosat "Pedago-Sat" Platform For Aerospace Training, Boutte Aissa, Belaidi El Yazid

Small Satellite Conference

Through this project, we try to promote the local aerospace knowledge by proposing a new kind of cooperation between the algerian universities and the ALgerian Space Agency (ASAL). The adopted method consists in developing an engineering training platform of a Nano-satellite (Open-source) and preparing functional and practical test courses to allow to the students and trainees the access to various knowledge related to the development and integration of satellites. The development plan granted to this platform (PEDAGO-SAT) is 36 months. At first milestone, a preliminary design realization of prototype are done, covering the certain equipment and sub-systems. The mechanical structure …

Development Of A Modular Propulsion System For Use In A Deep Space Hybrid Architecture, Stephen Mauthe, Bradley Hoover, James Brent, Noah Szczepanik

Small Satellite Conference

With recent and upcoming initiatives to revisit the moon and to begin planning for sending humans to Mars, the role of small spacecraft to facilitate and compliment these types of missions continues to grow. However, unlike low-Earth orbit (LEO), where small satellites have historically found their highest utilization, venturing further away from Earth and the more benign space environment it provides can prove to be a challenge for spacecraft designers. Factors can become difficult to design for, such as expected temperature ranges, power generation and radiation effects. At the same time, the objectives that small spacecraft are attempting to accomplish …

Development Of University-Friendly Cubesat Bus And Ground Station Architecture Using Software-Defined Radios, Jin S. Kang

Small Satellite Conference

The goal of the research and development presented in this paper is to introduce a CubeSat bus and ground station architecture that is made to be much more approachable to schools and universities. The three main pillars of the effort are low-cost, maintaining flexibility, and lowering the bar of entry. The presented CubeSat bus includes PyCubed board which houses most of the core satellite bus components on a single board. The board can handle main processing, data storage, UHF radio communication, telemetry sensors, and power management. This UHF radio is paired with a software-defined radio (SDR) that serves as the …

Flight And Direct To Earth/Space Relay Communication System Architecture For Gsfc Cubesat Missions, Ethan Abele, Serhat Altunc, Obadiah Kegege, Kaitlyn Ryder, Behnam Azimi, Michael Campola, Kevin Lynaugh, Gianfranco Barnaba, Sabit Ekin, John O'Hara

Small Satellite Conference

The CubeSat platform is finding increasing use in space science applications due to its low cost and comparative ease of launch. It is becoming a key scientific discovery tool in low Earth orbit (LEO) and beyond, including geosynchronous equatorial orbit (GEO), the Lagrange Points, Lunar missions, and more. The increasing complexity of these missions and their scientific goals must be supported by equal advancements in communications technology. Higher data rates and greater reliability are required every year. However, the reduced Size, Weight, and Power (SWaP) constraints of CubeSat platforms introduce unique challenges in the area of satellite communications. There is …

Real-Time Relay Of Small Satellite Remote Sensing Data To Tactical Military Operators, Robert Zitz, James Schwenke, Rob Singh

Small Satellite Conference

A Medium Earth Orbit (MEO) constellation of high bandwidth optical and RF relay satellites is urgently needed to provide real-time continuous tasking uplink and data downlink from the growing constellations of commercial remote sensing satellites. Tactical military operators have a need to establish communications links to these commercial assets, from commercial CONUS ground stations or directly to deployed ground terminals, when and where they need it. This level of access adds significant risk mitigation against adversary threats to foreign ground stations and data processing nodes in combat and can make the concept of a hybrid architecture combining government satellites and …

System Architecture For A Cubesat Dte Laser Communication System, Pj Du Plooy, Gilles Ackaert, G. Witvoet, W. Crowcombe

Small Satellite Conference

Small satellites and CubeSats are playing an increasingly larger role in technology demonstrations, research, and obtaining data for commercial use from space. As these use cases and applications for CubeSats increase and expand the need to get fast, secure and reliable access to the data gathered by the payloads on these spacecraft also increases. To support these developments AAC Hyperion together with TNO has developed a down-to-earth laser communication module for small satellites and CubeSats with a downlink capability of 1 Gbit/s, namely CubeCAT.

One of the challenges that needed to be solved to ensure success was how to deal …

Angels: Opening The Door Of The French Newspace, Laurène Gillot, Dominique Delacroix, Romain Mathieu, Christian Rossiquet, Thibéry Cussac, Dries Caluwaerts, Corinne Fournigault

Small Satellite Conference

In December 2019, ANGELS, the first nanosatellite designed and developed by French industry, supported by the French Space Agency, CNES, was launched from Kourou. Development and qualification of the satellite were achieved in two and a half years: quite a challenge!

The ANGELS demonstration mission was set up as a co-funded partnership between CNES and Hemeria in order both to validate new technologies and to promote the “new space” approach. Thales Alenia Space & Syrlinks led the team in charge of the Argos Néo instrument payload. The data collected for two years now show that the chosen compromise was the …

Ops-Sat Leop And Commissioning: Running A Nanosatellite Project In A Space Agency Context, David Evans, Georges Labrèche, Tom Mladenov, Dominik Marszk, 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. The spacecraft is equipped with a full set of sensors and actuators including a camera, GNSS, star tracker, reaction wheels, high speed X band and S band communication, laser receiver, software defined radio receiver, and …