Flexible On-Board avionics for new Space

• Matthias Pichler

FOTEC’s Activities on Testing Space Hardware Against Atomic Oxygen

• Siegfried Zoehrer (FOTEC)

Radiation, thermal extremes, low pressure, and Atomic Oxygen (ATOX) are inevitable factors limiting lifetime and functionality of spacecraft in Earth orbits. Particularly ATOX is considered as one of the most serious hazards to spacecraft materials at altitudes of 200 to 700 km. Due to its reactivity and relative orbital speed of about 8 km/s, it leads to spacecraft material erosion, degradation, performance issues, and potential system failure. Ground testing is crucial for qualifying space hardware to reduce operational risks. ATOX test facilities are becoming more important due to increased popularity of Very Low Earth Orbits (VLEO), especially for defense payloads. These facilities try to mimic projected atmospheric conditions like particle flux, velocity distribution, elemental composition, ion fraction, and ambient pressure. However, it’s experimentally challenging and complex to measure such parameters reliably. Most facilities only report very limited data, if at all. At FOTEC, we developed a test facility prototype where also larger samples and (sub)systems, potentially up to live thrusters and smaller satellites, could be tested. This facility is based on an oxygen ion beam source with controllable ion velocity distribution and flux. The beam is then neutralized by an electron source creating the (V)LEO ATOX environment in the vacuum chamber. This ion source is already functional. It can be mounted in any of our large vacuum chambers (up to 3 m length and 2.5 m diameter). Our current work focuses on characterizing and improving our physical under-standing of the device. By applying diagnostics in form of a Retarding Potential Analyzer, a high precision digital Faraday cup, an internal plasma electrode, a residual gas analyzer, and Kapton witness samples, we compare test conditions with the targeted atmospheric conditions. Once requirements are reached, a coupling test with our FEEP thruster will be performed. Afterwards, our goal is to provide the new facility for environmental testing of space hardware for internal use and as a service for third parties within our “One Stop Shop for Space Testing”strategy.

Simplified Functional Testing of Cubesats in Thermal Vacuum

• Volker Liedtke (Aerospace & Advanced Composites GmbH)

Keywords: Thermal Vacuum Testing, Cubesat Reference: [1] Method for CubeSat Thermal-Vacuum Cycling Test Specification, Roy Stevenson Soler Chisabas, Geilson Loureiro, Carlos de Oliveira Lino, Daniel Fernando Cantor, 47th International Conference on Environmental Systems ICES-2017-102, 16-20 July 2017, Charleston, South Carolina Cubesats are cost-efficient, small satellites, often made with off-the-shelf components that are not explicitly developed for space environment. A full characterisation under space environment –from launch to mission –is a complex and costly task. However, a minimum of preflight testing should be performed, to verify the functionality of the satellite’s key components under vacuum and expected temperatures of operation [1]. Potential tests may address the functionality of electric and electronic components under thermal vacuum, the operation of moving parts (antennas, solar cells, sensors), and the verification of the thermal management of the item under test. A common test sequence consists of pre-tests at room temperature in ambient atmosphere, followed by testing under vacuum at RT, and the verification of the functionality at operational temperatures. Multiple thermal cycles may be performed. Additionally, a thermal vacuum bakeout for reducing the amount of molecular organic contamination from off-the-shelf components is considered beneficial. At AAC, the focus is on fast and cost-efficient testing, based on customer provided GSE and standard interfaces. Depending on the respective cubesat, the test programme can be adopted and optimised for the specific mission needs with limited additional effort. Though requiring additional time and budget, the testing of a cubesat’s key components under simplified LEO conditions is substantially increasing the chances for the success of the mission.

Single Event Effect Testing with the Variable-Depth Bragg-Peak Method and Light Ions

• Wolfgang Treberspurg
• Martin Eizinger (FOTEC Forschungs- und Technologietransfer GmbH)

Abstract: The probability of a radiation-induced bit-error in static random-access memory (SRAM), expressed as the single-event-effect cross-section, has a strong dependence on linear energy transfer (LET). This dependence is usually modelled using a cumulative Weibull distribution function, where higher LET predicts a higher upset probability. A common approach for determining the parameters of the Weibull distribution is by obtaining experimental values of the cross-section for specific values of LET.The Variable-Depth Bragg-Peak (VDBP) method achieves this mainly by introducing different thicknesses of degrader material into the pristine beam [1]. The controlled variable in this approach is not LET but energy, and due to the stochastic nature of energy loss, the degraders do not reduce the energy of all particles equally, which introduces dispersion. This effect is particularly strong at low energies, which is where the VDBP method largely operates to achieve as high LETs as possible for the given particle species. An energy spread translates into an LET spread, which for light ions (e.g. carbon) can be over half of the achievable LET range. We present an approach where the spread in LET is taken into account systematically instead of appearing as an uncertainty. Instead of computing the LET for each thickness and fitting the Weibull distribution to the resulting points directly, this approach computes a pre-dicted cross-section for each degrader thick-ness using an assumed Weibull distribution and compares it to the experimental value at that thickness. This enables the use of light ions for single-event-effect testing. The potency of the method is shown by determining the Weibull parameters for experimental data of an SRAM sample. The shape of the experimental cross-section over degrader thickness is sufficiently unique, compared to the degrees of freedom of the Weibull distribution, to suggest that our indirect method yields unambiguous Weibull parameters. References: [1] S. Buchner et al., “Variable Depth Bragg Peak Method for Single Event Effects Testing,” in IEEE Transactions on Nuclear Science, vol. 58, no. 6, pp. 2976-2982, Dec. 2011

Environmental Testing of Satellite Sub Assemblies: UMBRAGROUP-SERMS’s Experience on TVAC, Pyroshock, and Vibration Qualification for an In – Orbit Servicing Brake Mechanism

• Serena Borsini (Umbragroup S.p.A.)
• Alessia Ricci

The increasing reliability demands of New Space missions require rigorous environmental qualification of satellite subsystems. In this context, UMBRAGROUP S.p.A., in collaboration with SERMS Test Center (Terni, Italy), performed a complete environmental and structural test campaign on the Joint Brake mechanism of an IOS (In Orbit Servicing) platform. The qualification activities addressed three critical areas—thermal vacuum, vibration, and pyroshock—using ECSS compliant high performance facilities. This work presents the tailored test setups, mission driven qualification levels, and high fidelity monitoring combined with systematic post test functional assessment. Thermal vacuum testing was performed in the SERMS TVAC chamber (pressure <10⁻⁴ Pa) across −60℃ to +100℃. The key challenge was the tribological behavior of the friction material in vacuum, where outgassing, adhesion changes, and modified wear mechanisms can affect torque stability. Vibration qualification reached 35 Grms using electrodynamic shakers and dedicated fixtures, with focus on structural stiffness and modal stability above the required 200 Hz resonance threshold. Pyroshock testing achieved 2000 g, verifying mechanical robustness along all axes. Particular attention is given to the challenges associated with testing actuated mechanical subassemblies: to meet the stringent time and cost constraints of the New Space Economy, the brake was actuated directly inside the thermal vacuum chamber using a characterized rotary feedthrough. This approach eliminated the need for a large chamber—reducing energy consumption—and allowed the performance test bench to remain outside the vacuum environment. As a result, the bench did not require vacuum compatible components (e.g., motors, lubrication systems, dedicated cabling), enabling significant savings in both complexity and cost. This contribution illustrates a robust, ECSS compliant approach to qualifying mechanical subsystems for New Space missions through the combined use of UMBRAGROUP’s test benches and SERMS’s environmental facilities. The lessons learned contribute to the broader SmallSat community through practical insights on subsystem qualification, support ongoing optimization of test tailoring for low mass actuated components and highlight the joint capabilities as strategic assets for Small-Sats.

Practical Best Practices in Total Ionizing Dose Testing for Space Applications

• Christoph Tscherne

Total Ionizing Dose (TID) effects pose critical challenges to the performance and longevity of electronic components in space environments. In this presentation, Christoph Tscherne, head of business unit Aerospace Radiation Competence Center from Seibersdorf Laboratories, will provide an overview of Total Ionizing Dose testing, covering the underlying physical mechanisms, practical implementation of TID test campaigns, and key considerations for effective evaluation. Drawing on real-world examples and best practices from environmental testing laboratories, the talk will highlight common pitfalls, strategies for reliable measurements, and insights to improve test planning and interpretation. The talk aims to equip engineers and researchers working in small satellite development with actionable guidance to enhance radiation tolerance assessments in their projects.

Leveraging Small-Satellites for Defence Missions: Mission-Level Drivers for Environmental Qualification in the MoD's Emerging Space Program

• Wilmar ENDER (MoD AUSTRIA)

The rapid proliferation of SmallSats enables governmental and defence-related actors to establish national space capabilities at comparatively low cost and development time. However, building such capabilities goes beyond individual missions and requires a coherent mission-level understanding of how mission objectives, operational needs and concepts, and architectural choices impact environmental qualification strategies. This contribution presents an unclassified perspective from a governmental end-user currently establishing a national SmallSat capability with a strong reliance on CubeSat platforms. Rather than focusing on specific environmental test methods, the presentation addresses how high-level mission drivers –such as resilience, availability, responsiveness, and constellation-based architectures –translate into environmental qualification needs. Particular attention is given to the use of commercial off-the-shelf (COTS) components and the resulting trade-offs between component-level qualification, system-level mitigation measures, and mission-level risk acceptance. Furthermore, lessons learned at the interface between mission design, industrial participation, and national test infrastructures will be discussed. It highlights how public end-users can enable “SME-friendly”qualification strategies through clear requirement philosophies, incremental mission development, and early alignment between mission concepts and environmental testing assumptions. By linking national capability building with system-level implications such as environmental qualification, this contribution aims to foster a shared understanding among industry, academia, and test facilities, to support best-practice approaches for future SmallSat missions in both civil and security-related contexts.

Sustainable wood-based materials for future satellite concepts

• Christian Hansmann (Wood K plus - Competence Center for Wood Composites & Wood Chemistry, Linz, Austria; BOKU University, Institute of Wood Technology and Renewable Materials, Department of Natural Sciences and Sustainable Resources, Vienna, Austria)
• Johanna Fries (FOTEC Forschungs- und Technologietransfer GmbH)

Future small satellite missions are increasingly constrained by mass, cost, and environmental considerations, while simultaneously demanding higher performance and extended operational lifetimes. High-aspect-ratio (HAR) satellite represent a novel and innovative design and offer significant potential for mass savings with enhanced performance. Due to the larger surface area, the versatility and performance can be enhanced, and the efficiency regarding satellite stackability can increase the launch vehicle use [1]. They impose new structural, thermal, and material challenges that must be addressed early in the design phase. This contribution presents HAR satellite design benefits for future missions and a sustainability-driven approach to material selection. In our current research activities, FOTEC and Wood K plus address environmental challenges following the rapidly growing satellite industry. The GLOW project focuses on Green Low-Earth Orbit Woodcraft for small satellites, e.g. HAR satellites. State-of-the-art satellites release considerable amounts of aluminum oxide particles into the stratosphere during reentry and may impact atmospheric chemistry. In addition, in the upcoming years thousands of satellites will add up the traffic in space. With the aim of reducing re-entry emissions, the consortium investigates on sustainable, advanced and robust material solutions. The engineered wood-based structures promise a lower environmental footprint and a nearly complete burning during reentry leaving minimal residues. They are selected via material and mission requirements such as mechanical properties, outgassing behavior and compatibility with space environmental conditions, especially during re-entry of a satellite. Sustainability aspects are assessed across the material life cycle, covering raw material sourcing, manufacturing processes and performing multiple tests with different wood samples. As wood experts, the team from Wood K plus is selecting the most promising wood materials based on the requirements given by the aerospace team from FOTEC. Within a trade-off the most suitable wood material types are selected and afterwards characterized. Within this contribution, HAR satellites will be introduced as an innovative concept, first test results with wood-based materials will be shown as well as potential materials for structural satellite manufacturing.

FEEP as Enabling Technology for Commercial Smallsat Missions and Constellations

• David Krejci (ENPULSION)

Since the first flight of a Field Emission Electric Propulsion (FEEP) thruster in 2018 in a joint IOD by ENPULSION and FOTEC, more than 300 ENPULSION FEEP systems have been launched, including over 200 heritage NANO systems, as well as an increasingly large number of successor products. These include the higher power MICRO systems and the updated NANO R3 and NANO AR3 systems. All these FEEP propulsion systems are based on passively-fed, Indium-based liquid metal FEEP technology, based on liquid metal ion source heritage developed at FOTEC. The passive propellant feed system in combination with a propellant that is in solid state during integration and launch make FEEP systems especially attractive for small satellite missions and missions that focus on simple, fast and cost-efficient integration and launch campaigns. In these FEEP systems, thrust is generated through electrostatic acceleration of ions extracted from a liquid propellant by suspending the liquified metal propellant in porous, sharp emitter features. This emitter including propellant is then biased to high voltage with respect to a counter electrode called extractor to induce a Taylor cone, leading to ion emission at the apex of the Taylor cone. To increase thrust, 28 emission sites are arranged in a characteristic crown shaped emitter geometry for the NANO thrusters, achieving thrust levels in the order of 350 µN. To increase thrust levels, 4 of these emitter crowns are operated in parallel in the MICRO thruster, allowing thrust levels at nominal 1 mN. Depending on emitter and extractor voltage settings, propulsion systems can be operated in a specific impulse range from approx. 1000 to beyond 4000 s. The NANO AR3 system is an evolution of the 0.35 mN NANO R3 propulsion unit that adds beam steering capability without moving parts by differential throttling of regions of the ion emitter, utilizing three independently controllable extractor segments. This work provides a statistical overview of previous missions employing FEEP propulsion systems, and discusses selected missions and applications enabled previously by this technology

Preparation of a dual-frequency commercial off-the-shelf GNSS receiver for space

• Gregor Möller (TU Wien)
• Hoor Bano (TU Wien)

The increasing number of nano- and small-satellite missions has created a growing demand for affordable, low-power navigation solutions suitable for space applications. According to the GSA GNSS Market Report 2024, approximately 5,000 GNSS devices are currently deployed on satellite missions, primarily addressing the high-performance domain with average device revenues of about €200k. While these systems enable centimeter-level orbit determination and environmental monitoring, their cost and complexity limit their applicability for larger satellite constellations. The key challenge is therefore to assess whether commercial off-the-shelf (COTS) GNSS receivers can meet the technical and environmental requirements of space missions. To address this need, the nanoGNSS project was initiated at ETH Zurich in 2019 and joined by TU Wien in 2023. The objective is to evaluate and qualify a highly efficient, small, low-cost, and low-power COTS GNSS receiver for onboard CubeSat applications, enabling decimeter- to centimeter-level orbit determination. The baseline hardware is the u-blox ZED-F9P dual-frequency GNSS receiver, capable of tracking all four GNSS constellations at up to 20 Hz and computing real-time onboard solutions based on code and carrier-phase measurements. The technical approach combines performance assessment under simulated orbital conditions with environmental qualification testing. The receiver was subjected to thermal vacuum testing at RUAG Space and proton irradiation campaigns at the Paul Scherrer Institute. Dedicated test procedures were developed to evaluate signal tracking performance, clock stability, positioning algorithms, Single Event Effects, and long-term radiation susceptibility. The results demonstrate that the receiver maintains robust dual-frequency tracking and precise orbit determination capabilities under simulated orbital conditions. However, temperature gradients significantly affect internal clock stability and, consequently, the signal tracking loop performance. Radiation testing quantified the occurrence of Single Event Effects under varying solar activity conditions, providing clear requirements for shielding. In addition, we briefly investigated possible measures to protect the antennas against atomic oxygen. These findings indicate that selected COTS GNSS hardware can achieve decimeter-level orbit accuracy in space when appropriate mitigation measures are implemented. The presented development therefore represents a key step toward enabling scalable, cost-efficient GNSS-based navigation solutions for nano- and small-satellite missions.

Space Radiation Intelligence

• Peter Beck (Seibersdorf Laboratories GmbH)