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Small satellites are efficient at performing Earth science from space due to their limited cost and size. Small satellites (cubesats) achieve much with limited power production/storage, heat dissipation, data storage, and ground contact points/bandwidth. As such it is beneficial to offload as much as possible to ground support systems. Consider the HyperAngular Rainbow Polarimeter (HARP) Cubesat. Its goals were to serve as a technical demonstration prior to the development of HARP2 aboard the NASA Plankton Aerosol Cloud and ocean Ecosystem (PACE) mission and to serve as an Earth viewing remote sensing platform which measured the characteristics of clouds and aerosols. HARP cubesat was limited to taking 5-minute capture sequences once every 24 h. It took approximately 10 such captures before it needed to perform data downlink and have its memory cleared for continued use. A ground station at NASA Wallops supported HARP with approximately three points of contact each day. To maximize the value of each capture, ground support software was developed leveraging public data to inform the schedule of each capture. In this paper, we review the algorithms and data sources that allowed us to: 1; predict the HARP orbital track a week in advance, 2; predict also the location of other remote sensing satellites and ground stations relative to HARP, 3; predict the ground view geometry of the instrument along its orbital track, 4; compare global climatological data products of clouds and aerosols along the predicted orbital tracks, and 5; identify and integrate important ground target locations based on remote sensing literature and ongoing natural phenomena. This HARP Orbital Prediction System (HOPS) made HARP into a successful technical demonstration which also offered significant science value. The HOPS system presents a valuable methodology for small satellites to operate efficiently despite their limited capabilities. HOPS is also a useful testbed for studying the sensitivity of scene geometry. Using HOPS, we show that for a wide field-of-view (FOV) instrument, like HARP, latitude/longitude geolocation varies by approximately 0.1+ at a height of 8-10 km. Scattering angles vary less than 0.01+ at similar heights, with the worst performance near direct backscatter (180+). [ABSTRACT FROM AUTHOR]

The EPFL Spacecraft Team (EST) is working on the Constellation of High-Performance Exospheric Science Satellites (CHESS) mission, which aims to launch a constellation of two CubeSats in 2027. These CubeSats will study the chemical composition of Earth's exosphere using time-of-flight mass spectrometry. To downlink the collected scientific data, the satellites will utilise a custom X-band transceiver, presented in this paper, operating in the amateur frequency range of 10.45 GHz to 10.50 GHz. The proposed transceiver architecture employs Software-Defined Radio (SDR) technology and can be easily adapted for different use cases. This modular approach has the potential to be suitable for future spacecraft missions, such as active debris removal or lifetime extension services, where flexible communication systems are required. • Hybrid SDR architectures enable versatile telecom systems for space missions. • IOD/IOV missions let students follow the entire life cycle of a space project. • Short development/prototyping cycles maximise the lessons learned in student teams. [ABSTRACT FROM AUTHOR]

The increasing space debris population in critical orbits due to spacecraft failure dictates the need for action. On-Orbit Servicing (OOS) has been proposed as a method for mitigating this trend by repairing existing space assets. The development of large servicing spacecraft has been given significant attention. In this paper, we are approaching the problem with a new paradigm for a servicing spacecraft by proposing a CubeSat class servicer equipped with a one-degree-of-freedom (DoF) robotic arm. Considering the OOS context, we choose the Orbital Replacement Unit (ORU) installation on a target spacecraft as a challenging benchmark task for the proposed servicer configuration. To carry out this task, we formulate and compare performance of four controllers to achieve coordinated control of both the CubeSat and the robotic arm for the installation task. We start with a basic PD controller and progress to the more advanced impedance controller, Model Predictive Control (MPC) and Model Predictive Impedance Control (MPIC) designs. The controllers are evaluated and compared across several relevant metrics for the ORU installation and their merits for practical implementation are discussed. • Comparative analysis of model-based controllers against traditional control methods. • Monte Carlo simulations used to test robustness of the controllers. • Novel, mechanically simple CubeSat servicer for simulated ORU installation. • MPC, PD controllers show similar success rates, MPC requires higher control efforts. [ABSTRACT FROM AUTHOR]

This study focuses on the autonomous detection of small (diameter < 50 m) faint (absolute magnitude > 20) Near-Earth Asteroids (NEAs) using commercial off-the-shelf (COTS) cameras during the approach phase of interplanetary CubeSat missions. To address the challenge of low signal-to-noise ratio (SNR) in COTS CubeSat sensors, a design tool was developed that incorporates camera parameters, asteroid parameters, approach phase geometry and an Earth-observation based SNR boosting technique, to ensure the autonomous detection of small NEAs during the approach phase. The tool generates a synthetic SNR that meets the target asteroid detection requirements (SNR ≥ 7) by stacking multiple frames of the target asteroid. The design tool defines requirements at the camera and trajectory design levels, exploring the problem design space of an asteroid rendezvous CubeSat mission. The validation of the tool was carried out using the NEA Scout asteroid and NEA Scout CubeSat mission requirements. The results demonstrate that the autonomous detection of small faint NEAs is achievable when the asteroid's positional uncertainty is within the CubeSat sensor's field of view. These findings have implications for current and future CubeSat missions to NEAs, offering insights into the feasibility of using off-the-shelf cameras for asteroid detection. • Commercial-off-the-shelf cameras can detect small, faint Near-Earth Asteroids. • CubeSat camera and trajectory parameter selection can guarantee asteroid detection. • Low CubeSat camera signal-to-noise ratios can be improved with image stacking. [ABSTRACT FROM AUTHOR]

This paper presents a mission concept designed for satellite-to-cell connectivity through a fractionated CubeSat approach, aiming to fulfill the objectives set by the BlueWalker-3 specifications. The envisioned system consists of 41 CubeSats, each adopting a 16U form factor, to provide dedicated coverage across specified sub-regions, as a reasonable solution. The pre-Phase-A design capitalizes on commercially available components with proven flight heritage, ensuring reliability and cost-efficiency. A genetic algorithm (GA)-based method has been introduced to tackle the complex challenge of designing a large antenna's folding pattern, with an analysis on how this design influences the overall system cost. The study conducts an in-depth analysis of system architecture and operational scenarios. Employing Monte-Carlo simulations, it assesses the Life Cycle Cost (LCC) and the system's resilience to failures, comparing it with similar configurations differing in CubeSat size and number. The results demonstrate that a fractionated approach significantly enhances the mission's scalability and robustness, providing substantial operational flexibility. The comparison highlights a cost-effective configuration within fractionated systems, emphasizing the proposed system's potential advantages. Furthermore, the paper addresses the environmental implications of deploying a fractionated spacecraft constellation, especially concerning astronomical studies. It underscores the CubeSats' minimized brightness and their reduced potential to interfere with telescopic observations, positioning the system as a more compatible option with nighttime sky studies. This consideration is particularly pertinent amidst increasing concerns over the impact of satellite constellations on astronomical research and night sky quality. • Introduction of a novel mission concept employing fractionated spacecraft for satellite-to-cell connectivity, showcasing an innovative design utilizing 41 CubeSats. • Comparative analysis demonstrating the proposed system's performance and cost advantages over the BlueWalker-3 mission, with findings supported by Monte-Carlo simulations. • Detailed discussion on the use of commercially available off-the-shelf components, highlighting the system's feasibility and reliability. • Exploration of the fractionated system's scalability and robustness, revealing potential for enhanced mission flexibility and economic efficiency. • Addressing the impact on astronomical observations, presenting a significant reduction in brightness and interference, enhancing compatibility with observational studies. [ABSTRACT FROM AUTHOR]

Space debris are a tangible risk for satellites in Earth orbits. Indeed, in the last decades fragmentation events have generated a large number of uncontrolled objects that have made the debris population grow. Modelling the space debris environment is becoming a fundamental task to evaluate the vulnerability of operational satellites, the probability of accidental collisions with uncontrolled objects, and the evolution of the debris population. With this aim, remote and in-situ measurements provide valuable data to tune the space debris population models and improve their reliability. While large satellites can be observed and tracked from ground, the sub-millimeter debris population requires in-situ measurements. In this context, in-orbit impact sensors are a key technology to obtain information about the sub-mm space debris environment. In this framework, a small-scale impact sensor sized to be integrated in a 2U CubeSat is being developed at the University of Padova. The sensor consists of a multitude of thin, conductive stripes arranged on a thin film of non-conductive material. When a debris hits the sensor, one or more stripes are severed, and the impact is detected. Moreover, the sensor design ensures low power consumption, making it feasible for CubeSat space missions. This work presents the latest outcomes obtained from the development of the sensor. Specifically, structural analyses are performed to assess that the sensor can withstand the launch loads, as well as thermal analyses to confirm its endurance capability with in-orbit temperatures. The number of expected impacts during the mission is predicted through orbital propagation, using state-of-the-art debris environment modelling tools. Finally, the paper presents a functional shooting test and vibration tests, executed onto a development model of the sensor, which verify its functionality and validate a Technology Readiness Level (TRL) of 4. • Space-borne sensor for in-situ monitoring of space debris. • Resistive impact sensor based on thin films and flexible PCB technology. • Thermal and structural analyses of CubeSat-sized impact sensor. • Vibrational test and functional test campaigns on a development model. [ABSTRACT FROM AUTHOR]

This study addresses the practical challenges associated with real-time kinematic relative navigation for cube satellites (CubeSats) performing rendezvous missions in a low Earth orbit (LEO). Considering the limitations of CubeSats, we propose a method to achieve precise centimeter-level relative navigation using single-frequency Global Positioning System (GPS) measurements. By using GPS visibility and minimizing errors in the LEO, our approach eliminates the need for additional sensors. We employed range-domain differential GPS with a Hatch filter to enhance the pseudorange accuracy. Double-difference integer ambiguities were resolved epoch-by-epoch using the least-squares ambiguity decorrelation adjustment (LAMBDA) technique without filters, to ensure efficiency. The algorithm was applied to CubeSat hardware, integrating cycle-slip detection and CubeSat-tailored ground plane designs. Simulations validated the algorithm's performance in LEO, and its real-world efficacy was evaluated through ground-based measurements in an open-sky environment. Considering hardware constraints, our method demonstrates the feasibility of achieving centimeter-level relative navigation for CubeSats, effectively and economically addressing a crucial need in autonomous space missions. [ABSTRACT FROM AUTHOR]

OMOTENASHI is a 6U CubeSat launched by the first NASA SLS rocket. Its mission was to demonstrate that a CubeSat can make a semi-hard landing on the Moon. Tight resource constraints make it difficult to mount a heater and a radiator in a CubeSat, so passive thermal control is a prominent design feature of OMOTENASHI that resolves the technical difficulty. In November 2019, a thermal vacuum test was conducted. This paper discusses the thermal design and the test results. OMOTENASHI was launched by SLS rocket on November 16, 2022. After the SLS rocket separation, OMOTENASHI's attitude control malfunctioned so it could not generate power from its solar cells. Eventually, communications were lost and have not been restored. Brief telemetry data confirmed that the temperature monitor functioned correctly for 30 min. This paper reports the flight results of the thermal status during the first ground station pass. Also, a comparison between the analysis model and telemetry data is shown. Finally, based on its estimated trajectory, the future thermal profile of the spacecraft and the result of the search operation are discussed. • OMOTENASHI was developed as the world's smallest moon lander that was launched by a NASA SLS rocket. • Passive thermal control design without a thermal controller is adopted by using a white paint and a graphite sheet. • Passive thermal control design can be utilized for future CubeSat missions under tight resource constraints. • This paper introduced the experiment and analysis method that achieves the thermal design for lunar missions by CubeSat. • The flight data after the launch of the SLS rocket showed the feasibility of this passive thermal control design. [ABSTRACT FROM AUTHOR]

This paper presents the development of a comprehensive Digital Engineering (DE) testing framework for CubeSat applications, demonstrated through the SleeperSat-1 (SPST-1) modular small satellite project at the University of Texas at El Paso Aerospace Center. The study emphasizes the integration of Digital Engineering tools, particularly Digital Twins (DT), to enhance the testing and validation processes of CubeSat under diverse environmental conditions. The research outlines the creation and implementation of a high-fidelity Digital Twin model for the SPST-1, incorporating Computer-Aided Design (CAD), Finite Element Method (FEM), and simulation models to ensure accurate representations of the satellite’s physical counterparts. Specifically, this research creates a high-fidelity Digital Twin model of the SleeperSat-1 CubeSat chassis and validates the solution against actual environmental testing, to find discrepancies and optimize the design for enhanced reliability and efficiency. This approach facilitates efficient early-stage testing, reducing the need for extensive physical prototyping and thereby minimizing time and costs. The SPST-1 project showcases the potential of Digital Engineering to improve reliability, scalability, and adaptability in CubeSat development. The findings highlight the transformative impact of Digital Twins in satellite design, offering promising advancements in design, testing, and operational workflows. [ABSTRACT FROM AUTHOR]

Most communication systems developed for the space industry are employing two passive antennas: one being dedicated to the uplink channel and the other to the downlink channel. Our challenge in this paper is to develop a dual-band antenna operating for both channels. This work presents the dual-band antenna design process and describes its simulated performances measurements and results using CST MWS. The antenna consists of a square patch with four slots around edge, two layers of substrate separated by a ground plane, and a suitable feed network located at the bottom. The design shown has a small footprint of 70 × 70 × 7.012 m m suitable for CubeSat communication system. The designed antenna achieves the following main characteristics: in uplink a bandwidth of 141.6MHz (from 1.9533 to 2.0949GHz), a gain of 7.13dB with a return loss of - 23.62 d B , and an axial ratio of 1.254dB for the 2.034GHz frequency. In the downlink, a bandwidth of 153.3MHz (from 3.1519 to 3.3052GHz), a gain of 7.3dB with a return loss of - 19.18 d B , and an axial ratio 2.649dB for the 3.252GHz frequency. [ABSTRACT FROM AUTHOR]

Wireless energy transfer (WET) devices using arrays of hybrid photo-thermoelectric plasmonic (HPTP) generators are under investigation to be a potential power source choice for CubeSats. This power generation system is based on the conversion of photon energy into electric energy via thermal gradients employing a large-range pulsed laser as source. During the study of the devices' integration on board a 3U CubeSat, the thermal subsystem was identified as the most critical, and thus its study has a major relevance for the demonstration of the technology herein proposed. The methodology employed to characterize the HPTP generators within the CubeSat thermal model is shown in this paper. From here, we cover the influence of the most significant model parameters under a given operational case, as well as a comparison on the performance of different thermoelectric devices configurations. Overall, the results show a maximization of the power obtained with the circular cells configuration and a very small variation in the temperature field with changes in the most significant parameters in the ranges dictated by the European Cooperation for Space Standardization (ECSS) that enables high reliability on the results that could be obtained from the model, despite the uncertainty inherent in a sensitivity study at the early stages of the project development. [ABSTRACT FROM AUTHOR]

This paper presents the first in-orbit results of the modular two-unit (2U) nanosatellite SOMP2b, focusing on the satellite bus itself and its scientific payloads. Launched in January 2021, SOMP2b comprises an innovative highly integrated satellite design with a high payload capacity. It contains the in-situ measurement of atomic oxygen in the thermosphere (FIPEXnano), a thermoelectric generator to investigate waste heat recovery in satellites (TEGonSOMP) and a material experiment to study the behaviour of carbon nanotubes in a space environment (CiREX2). The commissioning of the satellite bus was, in most respects, successful. Despite manageable limitations in communication and attitude functions, the payloads TEGonSOMP and FIPEXnano were successfully commissioned. Regarding the failure of CiREX2, countermeasures in fthe orm of in-orbit software updates are being investigated at the time of this publication. [ABSTRACT FROM AUTHOR]

Market trends in the space sector suggest a notable increase in satellite operations and market value for the coming decade. In parallel, there has been a shift in the industrial and academic sectors from traditional Document-Based System Engineering to Model-based systems engineering (MBSE) combined with Concurrent engineering (CE) practices. Due to growing demands, the drivers behind this change have been the need for quicker and more cost-effective design processes. A key challenge in this transition remains to determine how to effectively formalize and exchange data during all design stages and across all discipline-specific tools; as representing systems through models can be a complex endeavor. For instance, during the Preliminary design (PD) phase, the integration of system models with external mathematical models for simulations, analyses, and system budgeting is crucial. The introduction of CubeSats and their standard has partly addressed the question of standardization and has aided in reducing overall development time and costs in the space sector. Nevertheless, questions about how to successfully exchange data endure. This paper focuses on formalizing a CubeSat model for use across various stages of the PD phase. The entire process is conducted with the exclusive use of open-source tools, to facilitate the transparency of data integration across the PD phases, and the overall life cycle of a CubeSat. The paper has two primary outcomes: (i) developing a generic CubeSat model using Systems modeling language (SysML) that includes data storage and visualization through the application of Unified modeling language (UML) stereotypes, streamlining in parallel information exchange for integration with various simulation and analysis tools; (ii) creating an end-to-end use case scenario within the Nanostar software suite (NSS), an open-source framework designed to streamline data exchange across different software during CE sessions. A case study from a theoretical academic space mission concept is presented as the illustration of how to utilize the proposed formalization, and it serves as well as a preliminary validation of the proposed formalization. The proposed formalization positions the CubeSat SysML model as the central data source throughout the design process. It also supports automated trade-off analyses by combining the benefits of SysML with effective data instantiating across all PD study phases. [ABSTRACT FROM AUTHOR]

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Nano-satellites, which are following the CubeSat standard have established for demanding industrial and scientific applications with critical requirements on reliability and radiation tolerance. The employment of commercial off-the-shelf components enables a state-of-the-art performance but requires extensive testing to avoid and mitigate malefunctions due to the space environment. The CubeSat mission CLIMB is representative for future missions with a complex payload, a high power budget and a harsh radiation exposure. For this reason, a comprehensive irradiation study of its on-board-computer was done. The total ionizing dose damage of 50 krad was evaluated at a 60 Co source. As a consequence of this test, specific components were exchanged before performing single event effect studies at the synchrotron accelerator MedAustron. A board-level test revealed that the majority of effects concern the central micro controller wherefore was followed by a component-level test. Those irradiation tests make use of a pencil beam to map the device under test, which provides additional information to localize effects - by the timestamp - at the expense of an increased irradiation time compared to a homogeneous exposure. In this paper, we summarize the major findings of the test campaign and mitigation means and present a procedure for single event effect studies at medical accelerators. [ABSTRACT FROM AUTHOR]

This paper presents the design of a digital twin for a 6U CubeSat electrical power system, including the solar arrays, solar array regulators, battery, power distribution unit, and load subsystems. The digital twin is validated by comparing its real-time outputs with those of the physical system. Experimental tests confirm its feasibility, showing that the digital twin's real-time outputs closely match those of the physical system. Additionally, the digital twin can be used for control-hardware-in-the-loop and power-hardware-in-the-loop tests, allowing the real-time integration of simulated subsystems with hardware. This capability facilitates testing of new subsystems and optimization during the project's development phases. Additionally, to demonstrate the advanced capabilities of this model, the digital twin is used to simulate the CubeSat electrical power system behavior in real time throughout a complete orbital cycle in low Earth orbit conditions. This simulation provides valuable insights into the CubeSat operation by capturing the transient and steady-state responses of the EPS components under real orbital conditions. The results obtained indicate that the digital twin significantly enhances the testing and optimization process of new subsystems during the development phases of the project. Moreover, the capabilities of the digital twin can be further augmented by incorporating real-time telemetry data from the CubeSat, resulting in a highly accurate replication of the satellite's in-orbit behavior. This approach is crucial for identifying and diagnosing failures or malfunctions in the electrical power system, ensuring the robust and reliable operation of the CubeSat. [ABSTRACT FROM AUTHOR]

The objective of this research is to investigate the computational efficiency of various system architectures of onboard software for the onboard computers of CubeSat nanosatellites. The subject of this study is the computing overhead associated with using the containerization method in the construction of the onboard software for CubeSat nanosatellites. Purpose: To experimentally investigate the possibility and feasibility of using the containerization method in the onboard software of CubeSat nanosatellites. Objectives: to define the need to find new architectural solutions in the onboard software of the CubeSat nanosatellite; to perform a comparative analysis of the advantages and disadvantages of using monolithic (classical) and microservice architecture in the onboard software of the CubeSat nanosatellite; to justify the choice of the system software environment for executing containers; to determine the typical structure of CubeSat software and the strategy for adapting the WASM3 container environment to the FreeRTOS operating system; to develop a plan; and to conduct an expert evaluation based on the results of the evaluation to formulate conclusions about the possibility and feasibility of using container architecture in the onboard software of the CubeSat nanosatellite. Conclusions. This study demonstrates the relevance of developing software for satellites based on microservices and containers. The experimental results allow us to compare the performance of the onboard computer when executing various algorithms implemented using the C programming language (“Bare-Metal” approach) and the architecture based on the microservices approach, branched between containers of the WASM3 environment running under the FreeRTOS, and developed in C and C++ programming languages. The main conclusion of this work is the potential of using the Falco SBC/CDHM hardware platform as an affordable and powerful computing platform for CubeSat nanosatellites.

From a technical and economic point of view, cold gas propulsion for nanosatellites is one of the more rational systems. There is a problem, however: the optimal spherical shape for a high-pressure vessel only takes up half the cubic volume of the CubeSat unit. To increase the volume, it is proposed to switch to a cubic-shaped tank. The aim of this work is to synthesize the more rational structural design of a pressurant tank that fits within a cubic constraint, which provides the perfect balance between the mass of the structure and the delta-V budget available for the propulsion system. The proposed variants are as follows: a set of four cylinders with spherical bottoms; 14 equal spheres arranged in a face-centered cubic packing; a thin-walled cube supported by ribs, the location and parameters of which provide the smallest mass of the structure; a cube, the reinforcement scheme of which is calculated using topology optimization method; an original polyspheric and bypass design schemes where the filling of the volume of the cube is created by a set of spherical and cylindrical shells of different radii. All the considered vessel variants can be obtained using additive technologies, such as selective laser sintering. For each variant, the internal volume and mass of the vessels were obtained, as well as the delta-V budget, taking into account the mass of the tank and the mass of the stored gas. The analysis of the results reveals that there are two structures that are more rational. The new bypass scheme provides the largest delta-V budget, but it has a 1.6 times larger mass than the initial spherical vessel design. It should be noted that the difference in vessel mass is not crucial for CubeSat form factor satellites. Choosing a rational design may require a larger delta-V budget. The possibility of increasing the reserve delta-V of the CubeSat cold gas propulsion system by 25–35 % due to the transition from a spherical to a cube-shaped tank has been demonstrated. At the same time, the mass of the tank structure increases by 1.6–6.3 times, which can be considered an acceptable price for increasing the efficiency of the propulsion system. The new bypass scheme offers the optimal balance of mass and delta-V reserve. • Increasing the delta-V budget of the CubeSat cold gas propulsion system by 25–35 %. • Transition from a spherical pressure vessel to a conformable pressure vessel. • The new vessel design scheme gives the largest delta-V budget, is proposed. • Considered variant of vessel can be obtained using additive technologies. [ABSTRACT FROM AUTHOR]

Nanosatellites, as a standardized Space research project with fast and cost-effective development possibilities, have enabled universities in a growing number of emerging countries to develop a wide range of space missions in Low Earth Orbit (LEO). This paper aims to contribute to research efforts to improve the success of university nanosatellite missions using Model-Based Systems Engineering (MBSE) to facilitate the initial project management and design phases. The proposed model-based approach is the result of experience gained from the MASAT1 project, a Moroccan university nanosatellite, and it is based on an architectural framework that allows the system to be described via a set of views. The management and design process is based on a reference framework based on existing standards such as ESA's European Cooperation for Spatial Standardization (ECSS). The choice fell on the Systems Modeling Language (SysML) for the MBSE implementation with the future goal of developing executable SysML Modeling approaches. [ABSTRACT FROM AUTHOR]

Con la creación del CubeSat se marcó el inicio de un creciente interés en la exploración de tecnologías espaciales. El CubeSat es una estandarización que tiene el propósito de reducir costos y tiempos de producción de satélites, permitiendo el acceso al espacio a universidades o grupos de investigación que cuentan con recursos científicos para experimentar nuevas tecnologías y facilitar la investigación aeroespacial. A lo largo de los años, se han mejorado aspectos clave, como la miniaturización de componentes, sistemas de propulsión, eficiencia energética y comunicación. Sin embargo, persisten desafíos en la robustez espacial, costos y longevidad operativa, por lo que la selección adecuada de materiales es esencial porque deben soportar las condiciones extremas del espacio. La impresión 3D ha ganado protagonismo en la industria espacial, aunque, se ha explorado su potencial en aplicaciones aeroespaciales, su adopción en CubeSats todavía enfrenta desafíos. Mediante una revisión sistemática de literatura se buscó comprender el impacto de la impresión 3D en las estructuras de CubeSats frente a materiales convencionales, comparando sus propiedades clave frente a las condiciones del espacio. Los resultados destacaron la flexibilidad y personalización que ofrece la fabricación tridimensional, pero también señalaron las ventajas de los materiales convencionales en resistencia mecánica. La fabricación aditiva está transformando la industria espacial, la elección entre la impresión 3D y materiales clásicos dependerá de las necesidades de la misión espacial.

The object of this study was to study the energy consumption of the on-board computer of the CubeSat nanosatellite. The subject of this study is the on-board computer energy consumption model and its energy efficiency optimization method. The purpose of this work was to develop a model of an on-board computer’s energy consumption and a method of optimizing its energy efficiency, followed by an experimental verification of the effectiveness of this method. Task: justify the feasibility of finding new methods for optimizing the energy efficiency of the on-board computer of the CubeSat nanosatellite; prepare for the experiment, namely, develop a model of the on-board computer's energy consumption and a method of optimizing its energy efficiency, develop an experiment plan, and conduct measurement methodology; conduct experimental research and present the main results of the experiment; provide a meaningful interpretation of the obtained experimental results; generalize the conclusions, formulate the advantages and disadvantages of this work, and propose directions for further research. Conclusions. The power consumption of the on-board computers of nanosatellites must be reduced by hardware and software means. This study examines the effectiveness of known energy-saving methods for the authors' "Falco SBC 1.0" computing platform. These methods include dynamic frequency scaling (DFS), the race-to-dark (RTD) algorithm, and the combined algorithm, which proved to be the most effective. The results were idealized because they did not consider OS overhead. The proposed methodology can be used to evaluate other platforms. The following studies will consider the following areas: energy consumption in various processor energy-saving modes, overhead costs of multi-threaded real-time operating systems, and power management of non-processor components. Solving these problems remains an important area of scientific research.

The technology of building CubeSat-class nanosatellites has created a breakthrough in exploring near space for research and education. The availability of commercial solutions for the rapid integration of hardware and software of a CubeSat under development and the launch of such a nano-satellite into Earth orbit as a parasitic payload has made this technology accessible and attractive to universities worldwide. Despite this popularity, the statistics of nanosatellite failures after launch require a systematic approach to their design and construction and the selection of off-the-shelf (COTS) components. The object of the study is to determine the overall efficiency of standardized network interfaces when used in the onboard network of CubeSat nanosatellites. The subject of the article is a method for comprehensively evaluating the effectiveness of standardized network interfaces for data exchange in the onboard network of CubeSat nanosatellites, taking into account typical scenarios for data and command exchange. The aim of the study was to substantiate the method of expert evaluation of the technical efficiency of standardized network interfaces for data exchange in the onboard network of CubeSat nanosatellites, taking into account the following factors: energy efficiency, multi-mastering capability, resistance to electromagnetic interference, redundancy, coverage following the OSI network model, data transmission speed, and complexity of network technology implementation by software. Objectives: To analyze modern methods of organizing onboard avionics networks of nanosatellites of the CubeSat class, formulate an expert comparison model, and compare the selected information onboard networks following the model and the list of selected networks and their protocols. Results: an expert model consisting of a 7-factor comparison was created, modern and most widely used in the industry onboard networks were selected, and each network was compared according to the proposed model. Conclusions: The two most common and efficient models, I2C and CAN, were selected as recommended for use in the avionics of the KhAI1Sat nanosatellite and the “Boryviter”/”Falco” onboard computer being developed by the authors. Although the difference in power consumption between these two types of networks is significant, each has certain advantages in terms of noise immunity, multicasting, and application.

Access to space for small private companies requires to improve the ability to bring low-cost satellites into orbit. CubeSats offer a unique opportunity to meet these needs thanks to their reduced production times, the low manufacturing costs and ease of use. In order to be able to communicate with each other, exchange information and interact, it is necessary to place CubeSats in formation: in this context, miniature propulsion technologies, including chemical and electric propulsion, play a critical role in achieving mission requirements and maintaining satellites position. In this article, the feasibility of solid propellant micro rockets, fully integrated in an opposing array of printed thrust chambers is examined: each rocket can be fired together with the others or separately to modulate thrust. Theoretical and experimental results show that the microthruster, made of nylon and carbon fiber, have good mechanical and thermal resistance and simultaneously good performance is achieved. In particular, a microthruster with a diameter of 4 mm and a length of 6 mm, with 55 g of black powder propellant, achieves a thrust of about 3.5 N for about 7 ms.

Quantum key distribution is costly and, at the moment, offers low performance in space applications. Other more recent protocols could offer a potential practical solution to this problem. In this work, a preliminary optical payload design using commercial off-the-shelf elements for a quantum communication downlink in a 3U CubeSat is proposed. It is shown that this quantum state emitter allows the establishment of two types of quantum communication between the satellite and the ground station: quantum key distribution and quantum keyless private communication. Numerical simulations are provided that show the feasibility of the scheme for both protocols as well as their performance. For the simplified BB84, a maximum secret key rate of about 80 kHz and minimum QBER of slightly more than 0.07% is found, at the zenith, while for quantum private keyless communication, a 700 MHz private rate is achieved. This design serves as a platform for the implementation of novel quantum communication protocols that can improve the performance of quantum communications in space. [ABSTRACT FROM AUTHOR]

This study introduces a robust model-based framework designed for the verification and validation (V&V) of Attitude Determination and Control Systems (ADCSs) in nanosatellites, focusing on magnetic actuation while still being applicable to larger spacecraft platforms. By employing Model-in-the-Loop (MIL), Software-in-the-Loop (SIL), Processor-in-the-Loop (PIL), and Hardware-in-the-Loop (HIL) methodologies, this framework enables a thorough and systematic approach to testing and validation. The framework facilitates the assessment of long-term maneuvers, addressing challenges such as initial small-attitude errors and restricted 3D movements. Two specific maneuvers are evaluated: detumbling and nadir pointing, utilizing quaternions and a comprehensive suite of sensors, including six sun sensors, a three-axis magnetometer, a three-axis gyroscope, GPS, and three magnetorquers. The methodologies—MIL, SIL, PIL, and HIL—integrate the behaviors of digital sensors, analog signals, and astrodynamic perturbations. Based on an optimized SIL environment, Monte Carlo simulations were performed to optimize control gains for nadir pointing, achieving a mean pointing accuracy of 11.69° (MIL) and 18.22° (PIL), and an angular velocity norm of 0.0022 rad/s for detumbling. The HIL environment demonstrated a mean pointing accuracy of 9.96° and an angular velocity norm of 0.0024 rad/s. This comprehensive framework significantly advances the design and verification processes for nanosatellite ADCSs, enhancing the reliability and performance of nanosatellite missions. [ABSTRACT FROM AUTHOR]

The space community is moving forward with the development of in-orbit servicing and removal technologies to enable the circular economy in space and improve future space missions' scientific and commercial return and space environment exploitation. The application of nanosatellites to carry out proximity operations presents an additional opportunity to support various novel and cost-effective distributed mission architectures. The SpEye CubeSat mission, funded by the Agenzia Spaziale Italiana in the framework of the Alcor Program, aims at demonstrating inspection and rendezvous guidance navigation and control capabilities of a nanosatellite in close-proximity of the satellite carrier in a low Earth orbit environment. This paper focuses on the design of the SpEye mission and on the guidance and control strategies to enable its technological demonstrations. Particular attention is placed on the safety aspects of trajectory design, considered of paramount importance for the robust autonomous operations of a low-cost CubeSat in proximity to another satellite. • CubeSat mission for proximity operations demonstration. • In-orbit experiments applicable to the In-Orbit Servicing (IOS) and Active Debris Removal (ADR) domains. • Mission design and ConOps of a nanosatellite mission released by a carrier for proximity operations purposes. • Safe inspection design considering the optimisation of information cost metric. • Close range rendezvous solved with sequential convex programming and with enhanced safety applied. [ABSTRACT FROM AUTHOR]

As CubeSats are increasingly used for commercial purposes such as Earth observation, communication, and scientific research, it is essential to improve their reliability. Recent studies show that primarily insufficient functional testing on system level led to low success rates in former missions. Additionally, high-precision attitude control becomes more important for small satellites, especially in formation missions with multiple cooperating satellites. This paper introduces a unique test facility that allows for automated calibration and verification of the attitude determination and control system of fully integrated CubeSats with high accuracy. Calibration and functional testing at the system level are crucial for ensuring accurate in-orbit performance and detecting failures that may be caused by interfaces or interference with other subsystems. Testing fully integrated satellites prevents mission loss and significantly increases reliability. The automation of calibration and testing procedures improves the overall system quality, while simultaneously reducing the required verification effort, to meet the demands of the growing number of CubeSat missions. This paper presents the results of successfully performed automated system-level tests and provides a comprehensive outlook on verifying cooperative attitude control in multi-satellite formations. This contribution is significant for universities, companies, and agencies by providing an example concept and implementation of automated attitude control testing on system level with extension toward testing cooperating satellites. [ABSTRACT FROM AUTHOR]

DOCKS is a smart docking system developed within the framework of the Space Rider Observer Cube mission (SROC) but suitable for use in more general scenarios. This paper presents the mechanical design of the system and the kinematic tests performed on it. The system merges a classical probe drogue configuration with a gripper-like design, to manage the connection between the parts, and it is equipped with a suite of sensors to estimate the relative pose of the target. The system is also equipped with a dedicated computer, making it a smart standalone system. A series of kinematic tests have been conducted to validate the capability of the system to passively manage misalignment during the docking manoeuvre. The final tests are presented to assess the maximum load that the system could handle, even when inactive. [ABSTRACT FROM AUTHOR]

This research aims to address the need for monitoring the behavior of organic and inorganic materials in hypergravity conditions. To fulfill this objective, a container with specific features was designed. The container has a box with a lid, measuring 10×10×10 cm, conforming to the 1U volume of the CubeSat standard. It includes four cylindrical spaces to accommodate the sample wells. The container was 3D printed using polylactic acid (PLA) wire. For the electronic components, four ESP32-CAM modules were utilized, with two programmed to capture and upload photos to the cloud, and the other two programmed to capture and store photos on a micro SD memory card. Additionally, four light emitting diodes (LEDs) were incorporated to illuminate the well spaces. The total weight of the container is 450 grams, and it has a maximum wireless upload distance of 10 meters to the cloud. The storage capacity of the SD memory card determines the number of images that can be saved. [ABSTRACT FROM AUTHOR]

Gamma-ray bursts (GRBs) are intense and short-lived cosmic explosions. Miniaturised CubeSat-compatible instruments for the study of GRBs are being developed to help bridge the gap in large missions and assist in achieving full sky coverage. CubeSats are small, compact satellites conforming to a design standard and have transformed the space industry. They are relatively low-cost and are developed on fast timescales, which has provided unparalleled access to space. This paper focuses on GMOD, the gamma-ray module, onboard the 2U CubeSat EIRSAT-1, launched on December 1st 2023. GMOD is a scintillation-based instrument with a cerium bromide crystal coupled to an array of sixteen silicon photomultipliers, designed for the detection of GRBs. The characterisation of GMOD in the spacecraft, along with the validation of an updated spacecraft MEGAlib model is presented and this approach can be followed by other CubeSats with similar science goals. The energy resolution of the flight model is 7.07% at 662 keV and the effective area peaks in the tens to hundreds of keV, making it a suitable instrument for the detection of GRBs. An investigation into the instrument's angular response is also detailed. The results from this characterisation campaign are a benchmark for the instrument's performance pre-launch and will be used to compare with the detector's performance in orbit. [ABSTRACT FROM AUTHOR]

This paper explores the wide-ranging topography of micro-propulsion systems that have been flown in different small satellite missions. CubeSats, known for their compact size and affordability, have gained popularity in the realm of space exploration. However, their limited propulsion capabilities have often been a constraint in achieving certain mission objectives. In response to this challenge, space propulsion experts have developed a wide spectrum of miniaturized propulsion systems tailored to CubeSats, each offering distinct advantages. This literature review provides a comprehensive analysis of these micro-propulsion systems, categorizing them into distinct families based on their primary energy sources. The review provides informative graphs illustrating propulsion performance metrics, serving as beneficial resources for mission planners and satellite designers when selecting the most suitable propulsion system for a particular mission requirement. [ABSTRACT FROM AUTHOR]

Thanks to advancements in silicon photomultiplier sensors (SiPMs) and system-on-chip (SoC) technology, our INFN Roma1 group developed ArduSiPM in 2012, the first all-in-one scintillator particle detector in the literature. It used a custom Arduino Due shield to process fast signals, utilizing the Microchip Sam3X8E SoC's internal peripherals to control and acquire SiPM signals. The availability of radiation-tolerant SoCs, combined with the goal of reducing system space and weight, led to the development of an innovative second-generation board, a better-performing device called Cosmo ArduSiPM, suitable for space missions. The architecture of the new detector is based on the Microchip SAMV71 300 MHz, 32-bit ARM® Cortex®-M7 (Microchip Technology Inc., Chandler, AZ, USA). While the analog front-end is essentially identical to the ArduSiPM, it utilizes components with the smallest possible package. The board fits in a CubeSat module. Thanks to the compact design, the board has two independent channels, with a total weight of only 40 grams within a CubeSat form factor. The ArduSiPM architecture is based on a single microcontroller and fast discrete analog electronics. It benefits from the continued development of SoCs related to the IoT (Internet of Things) market. Compared with a system with a custom ASIC, this architecture based on software and SoC capabilities offers considerable advantages in terms of cost and development time. The ability to incorporate new commercial SoCs, continuously emerging from advancements in the aerospace and automotive industries, provides the system with a robust foundation for sustained growth over the years. A detailed characterization of the hardware and the system's response to different photon fluxes is presented in this article. Additionally, coupling the device with a scintillator was tested at the end of this article as a preliminary trial for future measurements, showing potential for further enhancement of the detector's capabilities. [ABSTRACT FROM AUTHOR]

Space exploration presents vast prospects for scientific, industrial, and economic progress. This paper introduces the MeSat mission as a pioneering approach to Mars exploration. The MeSat aims to deepen our understanding of Martian conditions and resources by employing an optimized Earth-to-Mars trajectory, enabling a comprehensive study of the Martian atmosphere and surface. The mission comprises a cargo microsatellite hosting three 6U CubeSats and two 3U CubeSats, deployed into four separate Mars orbits to form a constellation. Each CubeSat carries distinct payloads: a THz radiometer for Martian water vapor atmospheric observation, a high-resolution surface camera, a high-tech spectrometer, and a Fourier transform spectrometer (FTS) for wind speed readings. This paper includes the majority of the key parameters; however, we focus our discussion more on two aspects of this pioneering mission: the first aspect contains the proposal of four distinct payloads for the study of Mars' atmosphere and the second aspect proposes an optimal mission design algorithm that analyzes a fuel-efficient low-thrust trajectory from Earth to Mars. Regarding the payloads, the THz radiometer requires a specific design; hence, we explain this payload in more depth; the rest of the payloads, we suggest utilizing commercially available elements for the cost-effective manufacture of a whole system. For mission trajectory optimization, the study employs a dual-step hybrid optimization algorithm (PSO-homotopy) to analyze fuel-efficient low-thrust trajectories from Earth to Mars, incorporating the ephemeris dynamics model to account for gravitational perturbations in the entire Solar System. In practical mission design, crucial factors like hyperbolic excess velocity, diverse opportunities for Earth launch and Mars rendezvous, varied propulsion systems, and time of flight (TOF) play vital roles in trajectory optimization. In summary, for the MeSat mission, we propose a comprehensive Mars environmental mission design. We consider all aspects of the mission from trajectory design to engineering detail design, since we would like to inspire future Mars missions with a complete report. [ABSTRACT FROM AUTHOR]

In recent years, there has been a notable push for cost reduction in space applications, aligning with the growing interest in CubeSats. To unlock their full capabilities, propulsion is essential for executing complex missions. However, many propulsion technologies struggle to combine a low power-to-thrust ratio (PTTR), delivering sufficient total impulse, and providing high thrust, all within the limited space of a CubeSat. In this context, the Advanced Cusp Field Thruster (ACFT) emerges as a novel candidate, encapsulating all these crucial characteristics. To validate its performance of the thruster without the integration of a dedicated feeding system and a Power Processing Unit (PPU), a miniaturized development model of an ACFT underwent a 1650-hour endurance test, followed by a subsequent end-of-test characterization. This led to the achievement of a total impulse of 4400 Ns and a maximum thrust of 1522 ± 41 μ N at a specific impulse of 1035 ± 41.4 s, a PTTR of 29.5 ± 0.8 W/mN (without neutralizer), and an overall efficiency of 17.2 ± 1.1% using krypton. • Overview of current CubeSat propulsion technologies. • Introducing ACFT as a novel CubeSat propulsion option. • 1650-hour endurance test of ACFT shows 4400 Ns total impulse. • Miniaturized ACFT: 1522 μ N thrust, 1035 s impulse, 29.5 W/mN PTTR with Kr. • Self-cleaning suspected to reduce backsputtering effects. [ABSTRACT FROM AUTHOR]

We present the operation of the CubeSat De-orbiting All-Printed Propulsion System (Cube-de-ALPS), a thin-film Vacuum Arc Thruster being developed at the University of Southampton in collaboration with the European Space Agency to provide robust de-orbiting capability to sub-3U CubeSats. It comprises a flexible substrate on which coplanar arrays of vacuum arc micro-thrusters (micro-VAT) are printed alongside small supporting electronic subsystems. In particular, we focus on the application of a Cube-de-ALPS End-Of-Life disposal to an under-actuated 1U CubeSat with uncontrolled spin. In this scenario, a Faraday cup will provide coarse angle-of-attack estimates and trigger a single micro-VAT to ignite every time it points towards the forward velocity vector. Orbital lifetime estimates for different fuel materials, configurations, and operational modes are estimated using simplified dynamics and analytical thrust averaging. These results are compared to high-fidelity numerical simulations including full six degrees of freedom coupled attitude and orbital dynamics to confirm the viability of the concept and confirm that Cube-de-ALPS can de-orbit CubeSats from 1400 km. • A novel printed Vacuum Arc Thruster system with a Faraday cup to de-orbit small CubeSats. • A practical control law compatible with approximate on-board angle-of-attack readings on under-actuated CubeSats. • Semi-analytical simulations of system performance for preliminary system sizing. • High-fidelity numerical simulations of a 1U CubeSat confirm it can de-orbit from 1400 km. [ABSTRACT FROM AUTHOR]

Magnetometers are essential instruments in space physics, but their measurements are often contaminated by various external interference sources. In this work, we present a comprehensive review of existing magnetometer interference removal methods and introduce MAGPRIME (MAGnetic signal PRocessing, Interference Mitigation, and Enhancement), an open‐source Python library featuring a collection of state‐of‐the‐art interference removal algorithms. MAGPRIME streamlines the process of interference removal in magnetic field data by providing researchers with an integrated, easy‐to‐use platform. We detail the design, structure, and functionality of the library, as well as its potential to facilitate future research by enabling rapid testing and customization of interference removal methods. Using the MAGPRIME Library, we present two Monte Carlo benchmark results to compare the efficacy of interference removal algorithms in different magnetometer configurations. In Benchmark A, the Underdetermined Blind Source Separation (UBSS) and traditional gradiometry algorithms surpass the uncleaned boom‐mounted magnetometers, achieving improved correlation and reducing median error in each simulation. Benchmark B tests the efficacy of the suite of MAGPRIME algorithms in a boomless magnetometer configuration. In this configuration, the UBSS algorithm proves to significantly reduce median error, along with improvements in median correlation and signal to noise ratio. This study highlights MAGPRIME's potential in enhancing magnetic field measurement accuracy in various spacecraft designs, from traditional gradiometry setups to compact, cost‐effective alternatives like bus‐mounted CubeSat magnetometers, thus establishing it as a valuable tool for researchers and engineers in space exploration and magnetism studies. Plain Language Summary: Magnetometers, tools used to measure magnetic fields, are crucial for space exploration but often face interference from a spacecraft's own systems. This can distort measurements, making it hard to get accurate data. In order to address this, we introduce MAGPRIME, an open‐source software that helps clean up these magnetic field measurements. It is user‐friendly and integrates various techniques to reduce interference in the data. We tested MAGPRIME in two scenarios: one with magnetometers on a long mechanical arm or boom, and another without the boom. The results from these cases show that the use of MAGPRIME can make it easier and cheaper to get reliable magnetic field data, especially for smaller satellites like CubeSats. Key Points: MAGPRIME is an open‐source Python library with advanced interference removal algorithms for magnetic field measurements in space missionsThe MAGPRIME library is designed to be a community‐driven platform for magnetometer signal processing algorithmsMonte Carlo simulation results show UBSS achieves significant interference reduction in both boom and bus‐mounted magnetometer setups [ABSTRACT FROM AUTHOR]

Beyond-5G (B5G) technology plays a pivotal role in the next generation of communication infrastructure to support the future Society 5.0, a concept introduced in the 5th Basic Plan for Science and Technology by the Japanese Cabinet to define the long-term growth strategy for reconciling economic development with the resolution of social issues through the promotion of science and technologies. Free-space laser communication is a key element in boosting the data transmission capabilities required for B5G applications. The NICT will complete in 2024 the first fully functional prototypes of a series of miniaturized laser-communication terminals for multiple platforms. These terminals are designed to adapt to a wide range of requirements to address scenarios where laser communications can offer a competitive, enhanced solution compared to existing technologies. This paper provides an overview of these terminals' capabilities and the plans for their functional validation, as well as preliminary data from the first full-system tests. A number of innovations integrated into the terminals are introduced, such as the manufacture of the smallest miniaturized EDFA with integrated HPA and LNA and full space qualification to date, the first-ever integration of a beam-divergence control system in a practical communication terminal, the development of the most compact Tbit/s-class modem prototype documented in the literature, and the smallest gimbal design integrated in a lasercom terminal. Furthermore, this paper outlines the mid-term plans for demonstration in the most significant realistic scenarios, emphasizing the use of High-Altitude Platform Stations (HAPSs) and ultra-small satellites. [ABSTRACT FROM AUTHOR]

Despite a growing interest in developing and launching CubeSats, areas related to their testing and simulation still need to improve systematization, especially within universities. Regarding the temperature of CubeSats, the battery is one of the most critical components, which is why it is common to use active control techniques, such as heaters, based on the Joule effect, which impacts the satellite’s task scheduling. Despite previous works in the literature, no study simultaneously contemplates the scheduling of tasks and the thermal control of the battery, under varying energy, with the rigor and advantages of exact optimization algorithms. This letter proposes to address these two combined features: 1) the analysis and modeling of the nanosatellite scheduling problem to optimize the use of energy resources and 2) the maximize the mission value extraction while considering the battery temperature. In order to include the battery temperature control in the modeling, a proxy model will be used considering a finite volume method based on the heat transfer equations that govern the thermal models of a battery. Thus, a mathematical model of task scheduling capable of considering the thermal control of the battery will be introduced. [ABSTRACT FROM AUTHOR]

Nanosatellites are proliferating as low-cost, dedicated remote sensing opportunities for small nations. However, nanosatellites' performance as remote sensing platforms is impaired by low downlink speeds, which typically range from 1200 to 9600 bps. Additionally, an estimated 67% of downloaded data are unusable for further applications due to excess cloud cover. To alleviate this issue, we propose an image segmentation and prioritization algorithm to classify and segment the contents of captured images onboard the nanosatellite. This algorithm prioritizes images with clear captures of water bodies and vegetated areas with high downlink priority. This in-orbit organization of images will aid ground station operators with downlinking images suitable for further ground-based remote sensing analysis. The proposed algorithm uses Convolutional Neural Network (CNN) models to classify and segment captured image data. In this study, we compare various model architectures and backbone designs for segmentation and assess their performance. The models are trained on a dataset that simulates captured data from nanosatellites and transferred to the satellite hardware to conduct inferences. Ground testing for the satellite has achieved a peak Mean IoU of 75% and an F1 Score of 0.85 for multi-class segmentation. The proposed algorithm is expected to improve data budget downlink efficiency by up to 42% based on validation testing. [ABSTRACT FROM AUTHOR]

In this work a broadband Magnetoelectric (ME) dipole antenna for the Global Navigation Satellite System (GNSS) applied to nanosatellites is proposed. The antenna consists of a reflective cavity with open walls containing four gaps to enhance the axial ratio (AR) bandwidth. Additionally, it includes two ME dipoles formed by two pairs of vertical and horizontal copper plates, one of which is trapezoidal and a T-Γ-shaped cross-feeding structure. A prototype was designed and subsequently manufactured and measured. The experimentally obtained results exhibit consistent agreement with simulated outcomes, demonstrating that the antenna has a wide impedance bandwidth of 111.36% from 1.13 GHz to 1.62 GHz for the Voltage Standing Wave Ratio (VSWR) ≤ 2 and a 3 dB AR bandwidth of 120.45% from 1.10 GHz to 1.63 GHz. Within this range, high gain (≥8.5 dBi) and high radiation efficiency (90%) can be achieved. Furthermore, the antenna exhibits right-hand circular polarization (RHCP) and possesses good unidirectional radiation characteristics with a high front-to-back ratio (≥ 20 dB). [ABSTRACT FROM AUTHOR]

CubeSats are a type of spacecraft which have become popular since the early 2000. They are known for their quick development time and low cost, when comparing them to larger satellites. However, there is a significant drawback which has been recorded during these years of operations, namely an high failure rate which turns almost half of them into space debris. The reasons behind these malfunctions are often attributed to flawed spacecraft design choices or failures of commercial off-the-shelf (COTS) products. To improve the design of CubeSats, several software tools for performing the conceptual design have been proposed. These tools are often limited in their capabilities and are not suitable for all types of CubeSat missions. To address this issue, the University of Applied Sciences Wiener Neustadt (FHWN) in cooperation with Technische Universität Dresden is developing a software tool called GREATCUBE+. Its goal is to increase the success rate of CubeSats by providing a satellite model which is composed of commercial-off-the-shelf (COTS) products backed up by empirical heritage, analytical proof, and numerical analysis. One of the main features of this tool is the ability of dealing with different typologies of payloads. GREATCUBE+ has been validated with various successful CubeSat missions and it provides design solutions with an accuracy of above 90% when it comes to CubeSat weights and volumes. Using this software, CubeSat design teams can proceed from the conceptual development to the testing and assembly phases quicker, hoping to result in higher quality CubeSats and fewer failures. [ABSTRACT FROM AUTHOR]

CubeSats are designed to optimize applications within the strict constraints of space and power. This paper presents an On-Board Image Enhancement technique for remote sensing payloads, focusing on achieving Auto White Balance (AWB) with limited resources and enhancing the capabilities of small/microsatellites. The study introduces hardware-based techniques, including histogram adjustment, De-Bayer processing, and AWB, all tailored to minimize hardware resource consumption on CubeSats. The integrated 1U CubeSat system comprises a sensor board, an Image Data Processor (IDP) unit, and onboard computing, with a total power consumption estimated at 2.2 W. This system facilitates image capture at a resolution of 1920 × 1200 and utilizes the proposed algorithm for image enhancement on remote sensing payloads to improve the quality of images captured in low-light environments, thereby demonstrating significant advancements in satellite image processing and object-detection capabilities. [ABSTRACT FROM AUTHOR]

Precision beam pointing plays a critical role in free-space optical communications terminals in uplink, downlink and inter-satellite link scenarios. Among the various methods of beam steering, the use of fast steering mirrors (FSM) is widely adopted, with many commercial solutions employing diverse technologies, particularly focusing on small, high-bandwidth mirrors. This paper introduces a method using lightweight, commercial off-the-shelf components to construct a custom closed-loop steering mirror platform, suitable for mirror apertures exceeding 100 mm. The approach involves integrating optical encoders into two off-the-shelf open-loop actuators. These encoders read the signal reflected on purposefully diamond-machined knurled screw knobs, providing maximum contrast between light and dark lines. The resulting steering mirror has the potential to complement or replace FSM in applications requiring a larger stroke, at the expense of motion speed. In the presented setup, the mirror tilt resolution achieved based on the encoder closed-loop signal feedback is 45 μ rad, with a mean slew rate of 1.5 mrad/s. Importantly, the steering assembly is self-locking, requiring no power to maintain a steady pointing angle. Using the mirror to actively correct for a constantly moving incoming beam, a 5-fold increase in concentration of the beam spot on the center of the detector was obtained compared to a fixed position mirror, demonstrating the mirrors ability to correct for satellite platform jitter and drift. [ABSTRACT FROM AUTHOR]

Small satellites are efficient at performing Earth science from space due to their limited cost and size. Small satellites (cubesats) achieve much with limited power production/storage, heat dissipation, data storage, and ground contact points/bandwidth. As such it is beneficial to offload as much as possible to ground support systems. Consider the HyperAngular Rainbow Polarimeter (HARP) Cubesat. Its goals were to serve as a technical demonstration prior to the development of HARP2 aboard the NASA Plankton Aerosol Cloud and ocean Ecosystem (PACE) mission and to serve as an Earth viewing remote sensing platform which measured the characteristics of clouds and aerosols. HARP cubesat was limited to taking 5-minute capture sequences once every 24 h. It took approximately 10 such captures before it needed to perform data downlink and have its memory cleared for continued use. A ground station at NASA Wallops supported HARP with approximately three points of contact each day. To maximize the value of each capture, ground support software was developed leveraging public data to inform the schedule of each capture. In this paper, we review the algorithms and data sources that allowed us to: 1; predict the HARP orbital track a week in advance, 2; predict also the location of other remote sensing satellites and ground stations relative to HARP, 3; predict the ground view geometry of the instrument along its orbital track, 4; compare global climatological data products of clouds and aerosols along the predicted orbital tracks, and 5; identify and integrate important ground target locations based on remote sensing literature and ongoing natural phenomena. This HARP Orbital Prediction System (HOPS) made HARP into a successful technical demonstration which also offered significant science value. The HOPS system presents a valuable methodology for small satellites to operate efficiently despite their limited capabilities. HOPS is also a useful testbed for studying the sensitivity of scene geometry. Using HOPS, we show that for a wide field-of-view (FOV) instrument, like HARP, latitude/longitude geolocation varies by approximately 0.1∘ at a height of 8–10 km. Scattering angles vary less than 0.01∘ at similar heights, with the worst performance near direct backscatter 180∘.

Space research relies heavily on satellites, and technological developments are critical to the success of these missions. In order to estimate satellite pose, a simulation of an IMU sensor using Matplotlib is presented in this study. A roll, pitch, and yaw value analysis is performed on data obtained from the BNO-055 IMU sensor. A prototype ground station's helical antenna is used to investigate these parameters. For effective communication between the satellite body and ground station setup, a low-cost transceiver module RF-433Mhz module is connected to the ground station. IMUsensors are essential for inertial measurements in spacecraft, which support ground station monitoring. This study makes use of a four-turn helical antenna that is built for deployment and designed using the 4nec2 simulation program for RF-based satellite-ground station communication. The antenna's VSWR is 1.432, and its directivity is 18.581. Matplotlib is utilized to model variations in roll, pitch, and yaw values. Roll, pitch, and yaw ranges that are observed are −0.375 to 0.25, −0.375 to 0.5625, and −0.3125 to 0.1875, in that order. These ranges are useful in effectively visualizing the body pose of the CubeSat when connecting via PySerial to a Matplotlib-developed program.

The power limitations of nanosatellites, particularly during peak demand periods such as data transmission and maneuvering, hinder their operational capabilities. Traditional Electrical Power Subsystems relying solely on batteries face challenges in delivering the necessary power density and maintaining battery life, especially during eclipses. This study proposes an innovative Hybrid Energy Storage System for a 3U nanosatellite, integrating high-energy-density batteries with high-power-density supercapacitors, using an active parallel hybrid topology with two bidirectional converters and an optimal power management strategy. Using MATLAB and Simulink models, the study optimizes the Hybrid Energy Storage System by focusing on minimizing the capacity rate and depth of discharge to extend battery life. Simulation results show a 53.42% reduction in depth of discharge compared to a battery-only system, indicating a significant extension of battery life. Additionally, the proposed system allows for a minimal 2.08% increase in overall mass while maintaining enhanced performance. This research fills a critical gap in the literature by exploring active Hybrid Energy Storage System topologies for spacecraft applications, beyond the traditional passive and semi-active configurations. The innovative power management strategy ensures efficient energy utilization, significantly enhancing the reliability and efficiency of nanosatellite missions. The findings offer a practical solution to improve mission performance and extend the operational lifespan of nanosatellites, paving the way for more robust and capable small satellite deployments.