CubeSat Platform Research Articles

3Cat-8 Mission: A 6-Unit CubeSat for Ionospheric Multisensing and Technology Demonstration Test-Bed

This paper presents the mission analysis of 3Cat-8, a 6-Unit CubeSat mission being developed by the UPC NanoSat Lab for ionospheric research. The primary objective of the mission is to monitor the ionospheric scintillation of the aurora, and to perform several technological demonstrations. The satellite incorporates several novel systems, including a deployable Fresnel Zone Plate Antenna (FZPA), an integrated PocketQube deployer, a dual-receiver GNSS board for radio occultation and reflectometry experiments, and a polarimetric multi-spectral imager for auroral emission observations. The mission design, the suite of payloads, and the concept of operations are described in detail. This paper discusses the current development status of 3Cat-8, with several subsystems already developed and others in the final design phase. It is expected that the data gathered by 3Cat-8 will contribute to a better understanding of ionospheric effects on radio wave propagation and demonstrate the feasibility of compact remote sensors in a CubeSat platform.

Nanosatellite Design Considerations for a Mission to Explore the Propellant Sloshing Problem

Sloshing Platform for In-Orbit Controller Experimentation is an ambitious, student run mission to design and fly a cubesat to study fluid sloshing in spacecraft. The project will examine zero-g propellant sloshing from an experimental standpoint. Despite the small size and limited payload capacity, we intend to use the cubesat platform to mimic larger spacecraft and implement novel detection and computer vision methods in our analysis. Many modern spacecraft rely on propellant-filled tanks to perform attitude control and station-keeping maneuvers. When a large percentage of the spacecraft’s mass is comprised of liquid propellant, sloshing becomes a critical aspect of spacecraft attitude control and stability. The mission will study the tank/fluid dynamics using new methods to gain an enhanced understanding of low-gravity fluid disturbance effects and improve simulations using equivalent mechanical models (EMMs). Active control of the fluid leading to the reduction of propellant slosh settling times will improve the maneuverability and performance of spacecraft. This paper will focus on satellite payload research and design requirements used to inform other aspects of the SPICEsat design. In this paper, mission objectives will be discussed, numerical simulations for the proposed control algorithms are demonstrated, and a satellite experiment design is presented. Finally, we examine computational fluid dynamics models to validate the satellite design and propellant sensing components of the proposed spacecraft.

DivyaSat: Green Horizon Explorer

The "DivyaSat" project aims to tackle climate change and global warming by employing miniature, cost-effective instruments on a CubeSat platform. Inspired by the success of MeznSat, DivyaSat plans to utilize a shortwave infrared (SWIR) micro-spectrometer, called Argus 2000, to measure greenhouse gas concentrations in the atmosphere. Alongside the SWIR spectrometer, DivyaSat will incorporate a high-definition camera for accurate geolocation. This combination of instruments positions DivyaSat as a unique CubeSat mission capable of generating valuable data for atmospheric correction algorithms. This abstract provides an overview of DivyaSat's mission objectives, design, and potential contributions to understanding greenhouse gas concentrations in the atmosphere.

Laboratory investigations of sub-meter resolution telescope with segmented aperture dedicated to CubeSat platform

In current CubeSat observation satellites, the main design constraint is the available space. Standards dictating the unit dimensions of the payload severely restrict the maximum aperture and focal length of the optical instrument. In this paper, the authors present the results of work to produce a novel DeploScope optical system for a CubeSat-type observation satellite with a segmented aperture of the primary mirror deployed in space. The telescope is designed for Earth observation and is expected to find its application in the military, precision agriculture or environmental disaster prevention. The work includes a detailed analysis of the segment aperture effect on image repeatability for different numbers of main mirror segments. Based on it, the optimal configuration of the optical model of the telescope with an aperture of 188.5 mm and a focal length of 1100 mm was selected. Based on this analysis, a so-called laboratory version of the telescope was built, providing the possibility of free correction of each segment of the primary mirror while maintaining a solid stable base for other components of the module. Imaging tests were carried out on the laboratory version of the instrument and the system was optimized for a version suitable for implementation in the payload structure of the microsatellite.

Electric Sail Test Cube–Lunar Nanospacecraft, ESTCube-LuNa: Solar Wind Propulsion Demonstration Mission Concept

The electric solar wind sail, or E-sail, is a propellantless interplanetary propulsion system concept. By deflecting solar wind particles off their original course, it can generate a propulsive effect with nothing more than an electric charge. The high-voltage charge is applied to one or multiple centrifugally deployed hair-thin tethers, around which an electrostatic sheath is created. Electron emitters are required to compensate for the electron current gathered by the tether. The electric sail can also be utilised in low Earth orbit, or LEO, when passing through the ionosphere, where it serves as a plasma brake for deorbiting—several missions have been dedicated to LEO demonstration. In this article, we propose the ESTCube-LuNa mission concept and the preliminary cubesat design to be launched into the Moon’s orbit, where the solar wind is uninterrupted, except for the lunar wake and when the Moon is in the Earth’s magnetosphere. This article introduces E-sail demonstration experiments and the preliminary payload design, along with E-sail thrust validation and environment characterisation methods, a cis-lunar cubesat platform solution and an early concept of operations. The proposed lunar nanospacecraft concept is designed without a deep space network, typically used for lunar and deep space operations. Instead, radio telescopes are being repurposed for communications and radio frequency ranging, and celestial optical navigation is developed for on-board orbit determination.

Technology Demonstration of Space Situational Awareness (SSA) Mission on Stratospheric Balloon Platform

As the number of resident space objects (RSOs) orbiting Earth increases, the risk of collision increases, and mitigating this risk requires the detection, identification, characterization, and tracking of as many RSOs as possible in view at any given time, an area of research referred to as Space Situational Awareness (SSA). In order to develop algorithms for RSO detection and characterization, starfield images containing RSOs are needed. Such images can be obtained from star trackers, which have traditionally been used for attitude determination. Despite their low resolution, star tracker images have the potential to be useful for SSA. Using star trackers in this dual-purpose manner offers the benefit of leveraging existing star tracker technology already in orbit, eliminating the need for new and costly equipment to be launched into space. In August 2022, we launched a CubeSat-class payload, Resident Space Object Near-space Astrometric Research (RSONAR), on a stratospheric balloon. The primary objective of the payload was to demonstrate a dual-purpose star tracker for imaging and analyzing RSOs from a space-like environment, aiding in the field of SSA. Building on the experience and lessons learned from the 2022 campaign, we developed a next-generation dual-purpose camera in a 4U-inspired CubeSat platform, named RSONAR II. This payload was successfully launched in August 2023. With the RSONAR II payload, we developed a real-time, multi-purpose imaging system with two main cameras of varying cost that can adjust imaging parameters in real-time to evaluate the effectiveness of each configuration for RSO imaging. We also performed onboard RSO detection and attitude determination to verify the performance of our algorithms. Additionally, we implemented a downlink capability to verify payload performance during flight. To add a wider variety of images for testing our algorithms, we altered the resolution of one of the cameras throughout the mission. In this paper, we demonstrate a dual-purpose star tracker system for future SSA missions and compare two different sensor options for RSO imaging.

Design and Analysis of Cube Satellite Structure

Abstract: Currently, with new technologies, lower and cheaper satellites have been designed and launched. similar satellites fit as educational tools to unborn masterminds. With many kilograms and reduced confines, they've simple operation, despite being complete systems able to perform real operations. During CubeSat platform development, the conception of the design process is formulated and standard physical connections are proposed to find number of optimal design result in terms of introductory limitations and features comity. Specifically, new modular structure is proposed in order to allows flexible subsystems agreement. This paper checks and estimates the eventuality of one- unit CubeSat platform

Uvsq-Sat NG, a New CubeSat Pathfinder for Monitoring Earth Outgoing Energy and Greenhouse Gases

Climate change is undeniably one of the most pressing and critical challenges facing humanity in the 21st century. In this context, monitoring the Earth’s Energy Imbalance (EEI) is fundamental in conjunction with greenhouse gases (GHGs) in order to comprehensively understand and address climate change. The French Uvsq-Sat NG pathfinder mission addresses this issue through the implementation of a Six-Unit CubeSat, which has dimensions of 111.3 × 36.6 × 38.8 cm in its unstowed configuration. Uvsq-Sat NG is a satellite mission spearheaded by the Laboratoire Atmosphères, Observations Spatiales (LATMOS), and supported by the International Satellite Program in Research and Education (INSPIRE). The launch of this mission is planned for 2025. One of the Uvsq-Sat NG objectives is to ensure the smooth continuity of the Earth Radiation Budget (ERB) initiated via the Uvsq-Sat and Inspire-Sat satellites. Uvsq-Sat NG seeks to achieve broadband ERB measurements using state-of-the-art yet straightforward technologies. Another goal of the Uvsq-Sat NG mission is to conduct precise and comprehensive monitoring of atmospheric gas concentrations (CO2 and CH4) on a global scale and to investigate its correlation with Earth’s Outgoing Longwave Radiation (OLR). Uvsq-Sat NG carries several payloads, including Earth Radiative Sensors (ERSs) for monitoring incoming solar radiation and outgoing terrestrial radiation. A Near-Infrared (NIR) Spectrometer is onboard to assess GHGs’ atmospheric concentrations through observations in the wavelength range of 1200 to 2000 nm. Uvsq-Sat NG also includes a high-definition camera (NanoCam) designed to capture images of the Earth in the visible range. The NanoCam will facilitate data post-processing acquired via the spectrometer by ensuring accurate geolocation of the observed scenes. It will also offer the capability of observing the Earth’s limb, thus providing the opportunity to roughly estimate the vertical temperature profile of the atmosphere. We present here the scientific objectives of the Uvsq-Sat NG mission, along with a comprehensive overview of the CubeSat platform’s concepts and payload properties as well as the mission’s current status. Furthermore, we also describe a method for the retrieval of atmospheric gas columns (CO2, CH4, O2, H2O) from the Uvsq-Sat NG NIR Spectrometer data. The retrieval is based on spectra simulated for a range of environmental conditions (surface pressure, surface reflectance, vertical temperature profile, mixing ratios of primary gases, water vapor, other trace gases, cloud and aerosol optical depth distributions) as well as spectrometer characteristics (Signal-to-Noise Ratio (SNR) and spectral resolution from 1 to 6 nm).

Формирование концепции спутниковой группировки для раннего обнаружения лесных пожаров

The paper considers concept formation of a satellite constellation for early detection of fires in Siberia. Within the framework of the stated concept, an orbit was selected for deployment of a satellite constellation, and the flight path of satellites in a circular sun-synchronous orbit was constructed. The CubeSat platform is proposed as the basis for potentially applicable spacecraft for remote sensing of the Earth, the satellite expected appearance was created in the form of a 3D model, and the principle of satellites’ operation is described. It is assumed that the satellite would only take images and transmit them to the ground control station. To analyze images received from the satellites, the software is proposed that automatically detects fires and implements an algorithm using the OpenCV computer vision algorithm library. As a means of launching the satellite constellation, it is proposed to use the light-class Angara-1.2 launch vehicle.

USE OF OPEN-SOURCE COTS/MOTS HARDWARE AND SOFTWARE PLATFORMS FOR THE BUILD UP OF THE CUBESAT NANOSATELLITES

Abstract. CubeSats as a sub-class of nanosatellites have become a game-changer in the industry of scientific research and exploration of the new space technologies. Their cost effectiveness, relative ease of manufacturing, and the predicted lifecycle are the main factors of success. Having such popularity in mind – many vendors, student teams and enthusiast started to build their platforms to offer reuse and faster buildup of such satellites, introducing so-called COTS/MOTS approach of the satellite’s construction. However, looking into statistics – only 2.5% of the launched satellites were able to full perform their mission, and almost 25% just failed. Partially, the key problems are in the area of using non-radiation hardened electronics as the CubeSat idea is to use commercial (or at utmost automotive) components. Authors of the article provide a holistic view on the existing hardware and software platforms that are currently available as COTS/MOTS solutions, as well as their capabilities. Part of the research was done in the area of the available software frameworks, as the modern software has rather high cyclomatic complexity and often it is exactly software components that make CubeSat mission at risk. Software related frameworks are compared via the use of newly introduced by the authors multi-factor ranking model (FMCSA). At the same time the article raises the cross-country problem of the creation and use of the Ukrainian platform for the CubeSats. Authors propose a solution for the creation of the part of the CubeSat platform as the starting point and it is an On-Board Computer (OBC). The idea is to design an OBC that can solve the big portion of the known issues of the CubeSat hardware and software with the major stress on the hardware issues related to the Single-Event Upset (SEU) and Single-Event Latch Up (SEL), without moving to the radiation tolerant semiconductors. Proposed in the article solution combines the selection of the modern central processor, that is industry recognized, availability of the software solutions for it, as well as the power-domains control principle that allows to minimize the potential harm of the SEU and SEL radiation-driven events.

Software Integration of an IMU Sensor to a CubeSat Platform Based on CSP (CubeSat Space Protocol)

The development and use of nanosatellites have increased in recent years. Space programs were exclusive to governments with significant capital. Now, nanosatellites have changed the orbital ecosystem and have allowed new regions and a wide range of industries to position themselves in the so-called new space, a growing sector that democratizes the commercialization of space thanks to a smaller, more agile, and affordable technology. Nanosatellites have similar capabilities to their conventional counterparts but are commonly used for highly specific missions such as Earth observation, telecommunications, and meteorology. The complex development of a nanosatellite requires solving different engineering problems to assembly and integrate all hardware and software components into a small space. It requires the monitoring, control, and operation of the satellite’s features from the ground segment. One major challenge is the development of satellite mission control software for both space and ground segments in limited-time scheduled missions. This article describes the integration process of an EPSON M-G364PDCA Inertial Measurement Unit (IMU) to a CubeSat platform nanosatellite based on the Danish company GomSpace devices and a CSP protocol. The result is a hardware implementation and software development by the Colombian Air Force (FAC) team as part of the FACSAT-2 program. The integration of these components into the space and ground segment contributes to solve one challenge in the development of control software for space missions, as described above, and becomes the first approach for Colombian space nanosatellites software development. In addition, this research presents the Colombian Air Force configuration for space mission subsystems on the CSP network, the software development for the main on-board computer based on a NanoMind A3200 to setup the IMU —controlled and monitored from the ground segment through a CSP terminal on a Linux server—, and setup telemetry data from space to be sent periodically to the ground segment and stored locally in a MongoDB database for its subsequent visualization and analysis.

Experimental set-up of a thermal vacuum chamber for thermal model in-house correlation and characterization of the HYPSO hyperspectral imager

Space environment with changing temperatures and vacuum can affect the performance of optics instruments onboard satellites. Thermal models and tests are typically done to understand the optics performance within large space projects, but less often in nanosatellites projects. It is even more rarer for an optics payload inside a CubeSat platform, made by a third provider, to do functional tests on their optics during space environment test campaign. In this research, an in-house made vacuum chamber with the possibility to warm up (TVAC) the devices under tests, and wall-through transparency for optics experiments is set-up. In parallel, a thermal model of the HYPerspectral Small satellite for ocean Observation (HYPSO) Hyperspectral Imager (HSI) is developed. The HSI, which is a transmissive grating hyperspectral instrument ranged in the visible to near infrared wavelength, has been tested in TVAC. As thermal control is based on heating the device under test, a new method for fitting the thermal models inside vacuum chambers with only heating capability is proposed. Finally, the TVAC set-up and the thermal model fitting method have been demonstrated to be appropriate to validate the HSI thermal model, and to characterize the optics performance of HSI in vacuum and in the range of temperatures found inside the in-orbit HYPSO-1 CubeSat.

Feasibility of autonomous orbit keeping with optimal fuel consumption using drag-free CubeSat

In this paper, the composition of the drag-free CubeSat platform was introduced first. Then the control strategy of drag-free CubeSat orbit keeping was proposed. Finally, the simulation with the control scheme of the Homan transfer orbit was compared. By comparing and analyzing the fuel consumption of the drag-free track and Homan transfer track, it is demonstrated that the continuous drag compensation of the drag-free control scheme can significantly reduce the consumption of thruster mass, and the drag-free technology has good advantages in track stability.

A High Gain Deployable L/S Band Conical Helix Antenna Integrated With Optical System for Earth Observation CubeSats

In this study, a new spiral dual-band antenna integrated with an optical system for a small CubeSat spacecraft was proposed. It is challenging to design an antenna with a limited space on a CubeSat platform. To improve the space utilization, an antenna was designed based on the concept of not occupying the sides of the CubeSat. A feature of the proposed antenna system is its compactness, dual-band operation in the L- and S-bands, and possibility of integration with spacecraft cameras. As a result of the study, reflection coefficients of -18 dB and -23 dB and gain of 6.8 dBi and 7.4 dBi, respectively, were achieved at resonant frequencies of 1.7 GHz and 2.45 GHz. The conical shape of the spiral antenna allows the optical system to increase the coverage area, and a simple deployment system with feedback ensures the mission safety. These properties make the proposed antenna suitable for CubeSat systems.

Opportunities of Si-microstrip LGAD for next-generation space detectors

Low Gain Avalanche Diode (LGAD) is a consolidated technology developed for particle detectors at colliders which allows for simultaneous and accurate time (<100 ps) and position (tens of μm) resolutions. It is a candidate technology that could enable for the first time 5D tracking in space using LGAD Si-microstrip tracking systems. The intrinsic gain of LGAD sensors may also allow to decrease the sensor thickness while achieving signal yields similar to those of Si-microstrips currently operated in Space. In this document we discuss the possible applications and breakthrough opportunities in next generation large area cosmic ray detectors and sub-GeV gamma-ray detectors that could be enabled by LGAD Si-microstrip tracking detectors in Space. We propose the design of a cost-effective instrument demonstrator on a CubeSat platform to enable and qualify the operations of LGAD Si-microstrip detectors in space.

An Effort to Use a Solid Propellant Engine Arrangement in the Moon Soft Landing Problem

This paper presents a control design strategy for the soft-landing problem on the Moon using solid propellant engines (SPEs). While SPEs have controllability issues and issues relating to the fact that they cannot be restarted, they are characterized by their reliability, simplicity, and cost-effectiveness. Consequently, our main contribution is to tackle this disadvantage by formulating a 1-dimensional landing optimization problem using an array of SPEs in a CubeSat platform, which is analyzed for different numbers of engines in the array and for three types of propellant grain cross-section (PGCS). The engines and control parameters are optimized by a genetic algorithm (GA) due to the non-linearity of the problem and the uncertainties of the state variables. Two design approaches for control are analyzed, where the robust design based on the uncertainties of the variables shows the best performance. The results of Monte Carlo simulations were used to demonstrate the effectiveness of the robust design, which decreases the impact velocity as the number of SPEs increases. Using an arrangement of ten SPEs, the landing was at −2.97 m/s with a standard deviation of 0.99 m/s; using sixteen SPEs, the landing was at −2.04 m/s with a standard deviation of 0.48 m/s. Both have regressive PGCS.

NetSat—Challenges and lessons learned of a formation of 4 nano-satellites

The objective of the NetSat mission was to develop underlying technologies for small satellite formation flying and to demonstrate it at the level of four nano-satellites in three-dimensional configurations. Thus, base technologies, such as orbit determination, attitude determination and control, inter-satellite communication, and multi-satellite operations were studied and implemented on a 3U CubeSat platform. Technological challenges concerned in particular the precision 3-axis attitude control system in combination with an electric continuous low-thrust propulsion system. Different control approaches for efficient transitions between various formation topologies were analyzed, taking the limitations of the hardware platform (propellant mass, thrust level, power budget, attitude control capabilities) as well as external orbit perturbations into account and allowing for distributed control of multi-satellite formations. In a research program of over 15 years, the essential technologies for formations of small satellites were realized subsequently and then tested in orbit on multiple missions. On this basis, NetSat was launched on 28. September 2020 on a Soyuz rocket into a circular orbit of an altitude of 575km. During the operations phase several new operations concepts developed in the project, namely the Compass IoT network spanning all ground and satellite systems with more than 50 nodes, or a flexible operations frontend with auto-operations capabilities could be tested and allowed for operating such a multi-satellite network. Additionally, the implemented inter-satellite link among the satellites could be established and tested extensively, marking the first time that four 3U CubeSats were able to successfully demonstrate inter-satellite communication in orbit.

Development of Innovative CubeSat Platform for Mass Production

With the recent increase in CubeSats’ ability to undertake complex and advanced missions, they are being considered for missions such as constellations, which demand high development efficiency. From a satellite interface perspective, productivity can be maximized by implementing a flexible modular structural platform that promotes easy reconfigurability during the integration and testing phase. Thus, the structural design of a CubeSat plays a crucial role in facilitating the satellite integration process. In most cases, the mechanical interface implemented between the primary load-supporting structure and internal satellite subassemblies affects the speed and efficiency of satellite integration by adding or reducing complexity. Most CubeSat structural designs use stacking techniques to mount PCBs onto the primary structure using stacking rods/screws. As a result, the internal subsystems are interconnected. This conventional interface method is observed to increase the number of structural parts, while increasing complexity during integration. In this study, flexible 3U and 1U CubeSat platforms are developed, based on the slot concept. This innovative mounting design provides a simple method of mounting PCBs into the slots. The concept is evaluated and verified for its feasibility for mass production applications. Count and complexity analysis is carried to evaluate the proposed design against the conventional type of structural interface methods. The assessment reveals that this new concept demonstrates a significant improvement in the efficiency of the mass production process.

Scalable and Configurable Electrical Interface Board for Bus System Development of Different CubeSat Platforms

A flight-proven electrical bus system for the 1U CubeSat platform was designed in the BIRDS satellite program at the Kyushu Institute of Technology. The bus utilizes a backplane board as the mechanical and electrical interface between the subsystems and the payloads. The electrical routes on the backplane are configured by software using a complex programmable logic device (CPLD). It allows for reusability in multiple CubeSat projects while lowering costs and development time; as a result, resources can be directed toward developing the mission payloads. Lastly, it provides more time for integration and system-level verification, which are critical for a reliable and successful mission. The current trend of CubeSat launches is focused on 3U and 6U platforms due to their capability to accommodate multiple and complex payloads. Hence, a demonstration of the electrical bus system to adapt to larger platforms is necessary. This study demonstrates the configurable electrical interface board’s scalability in two cases: the capability to accommodate (1) multiple missions and (2) complex payload requirements. In the first case, a 3U-size configurable backplane prototype was designed to handle 13 mission payloads. Four CPLDs were used to manage the limited number of digital interfaces between the existing bus system and the mission payloads. The measured transmission delay was up to 20 ns, which is acceptable for simple serial communications such as UART and SPI. Furthermore, the measured energy consumption of the backplane per ISS orbit was only 28 mWh. Lastly, the designed backplane was proven to be highly reliable as no bit errors were detected throughout the functionality tests. In the second case, a configurable backplane was implemented in a 6U CubeSat with complex payload requirements compared to the 1U CubeSat platform. The CubeSat was deployed in ISS orbit, and the initial on-orbit results indicated that the designed backplane supported missions without issues.

Assessing the Capacity and Coverage of Satellite IoT for Developing Countries Using a CubeSat

Many regions in developing countries do not have any access to communication networks even though the number of devices connected through the Internet of Things (IoT) is increasing significantly. A small satellite platform could provide global network coverage in low Earth orbit to these remote locations at a low cost. This paper describes the overall mission architecture and the implementation of remote IoT using a 1U volume in 6U CubeSat platform named KITSUNE. In KITSUNE, one of the missions is to leverage IoT for building a network of remote ground sensor terminals (GST) in 11 mostly developing countries. This paper evaluates the capacity and coverage of a satellite-based IoT network for providing remote data-collection services to these countries. The amount of data that could be collected from the GSTs and forwarded accurately to the users determines the actual capacity of the Store and Forward (S&amp;F) mission. Therefore, there are several proposed parameters to estimate this capacity in this study. In addition, these parameters are retrieved from the simulations, ground test results, and on-orbit observations with the KITSUNE satellite. The proposed IoT system, which is composed of the GSTs and IoT subsystem onboard KITSUNE satellite, is determined to be capable of providing valuable information from remote locations. In addition, the collected data are achieved and analyzed to monitor sensory data specific to each country, and it could help to generate prediction profiles as well.