CubeSat Nanosatellites Research Articles

Observations of solar cosmic rays using cubesat nanosatellites

We discussed the possibilities of using cubesat nanosatellites for studying solar cosmic rays. SCR electron fluxes in the polar caps at an altitude of ~550 km were detected. The measurements were carried out with DeCoR scintillation detectors operated at several cubesats of Moscow State University during the solar cosmic ray event on September 6–21, 2022.

Inertial microfluidic mixer for biological CubeSat missions

Nanosatellites of CubeSat type due to, i.a., minimized costs of space missions, as well as the potential large application area, have become a significant part of the space economy sector recently. The opportunity to apply miniaturized microsystem (MEMS) tools in satellite space missions further accelerates both the space and the MEMS markets, which in the coming years are considered to become inseparable. As a response to the aforementioned perspectives, this paper presents a microfluidic mixer system for biological research to be conducted onboard CubeSat nanosatellites. As a high complexity of the space systems is not desired due to the need for failure-free and remotely controlled operation, the principal concept of the work was to design an entirely passive micromixer, based on lab-on-chip technologies. For the first time, the microfluidic mixer that uses inertial force generated by rocket engines during launch to the orbit is proposed to provide an appropriate mixing of liquid samples. Such a solution not only saves the space occupied by standard pumping systems, but also reduces the energy requirements, ultimately minimizing the number of battery modules and the whole CubeSat size. The structures of the microfluidic mixers were fabricated entirely out of biocompatible resins using MultiJet 3D printing technology. To verify the functionality of the passive mixing system, optical detection consisting of the array of blue LEDs and phototransistors was applied successfully. The performance of the device was tested utilizing an experimental rocket, as a part of the Spaceport America Cup 2023 competition.Graphical abstract

Analysis of the thermal control system for the 3U CubeSat nanosatellite – “IXAYA”

Abstract In recent years, space exploration has become increasingly accessible to a diverse array of countries, facilitated in part by CubeSat nanosatellites. These versatile nanosatellites find applications in a wide spectrum of fields, from forest fire detection and meteorological observation to communication systems, particle analysis, and hot spot identification. This article delves into the outcomes of a comprehensive thermal analysis conducted on the IXAYA nanosatellite. The primary mission of this nanosatellite is to identify hot spots in the vicinity of Mexico City. The thermal analysis process entails a meticulous review of each subsystem along with the associated boundary conditions. This study commences with the definition of an optical payload and a thorough assessment of subsystem requirements. Subsequently, we calculate both external and internal thermal loads. With these foundational data points, we progress to ascertain the temperature distribution across the entirety of the satellite, ensuring that all constituent elements remain within their designated operational temperature ranges. In the closing section, we present our findings and conclusions.

Багатокритеріальне оцінювання стандартизованих інтерфейсів бортових мереж наносупутників CubeSat

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.

Hyperspectral camera as a compact payload architecture for remote sensing applications.

Monitoring and observation over the surface of the Earth have been a matter of global interest. In this path, recent efforts aim to develop a spatial mission to perform remote sensing applications. Mainly, CubeSat nanosatellites have emerged as a standard for developing low-weight and small-sized instruments. In terms of payloads, state-of-the-art optical systems for CubeSats are expensive and designed to work in general use cases. To overcome these limitations, this paper presents a 1.4 U compact optical system to acquire spectral images from a CubeSat standard satellite at the height of 550 km. To validate the proposed architecture, optical simulations using ray tracing simulation software are presented. Because the performance of computer vision tasks is highly related to data quality, we compared the optical system in terms of the classification performance on a real remote sensing application. The performances of the optical characterization and land cover classification show that the proposed optical system achieves a compact instrument, operating at a spectral range from 450 nm to 900 nm discretized on 35 spectral bands. The optical system has an overall f-number of 3.41 with a ground sampling distance of 52.8 m and a swath of 40 km. Additionally, the design parameters for each optical element are publicly available for validation, repeatability, and reproducibility of the results.

Simplified Fe modeling of the PyCubed PCB complete with components for CubeSat missions

CubeSat nano-satellites are, to date, the cheapest independent mean of bringing a payload into orbit. The most frequent cause of failure for this kind of launches is the mechanical failure of electronic boards or soldered electronic elements due to vibrations or shocks. For this reason, the numerical finite element design and experimental verification phases of printed circuit boards (PCBs) with soldered components are extremely delicate and critical in the assessment of the integrity of the boards during launch. In simulating the mechanical behaviour of PCBs it is important to consider the material properties, the geometry, and the type of components mounted on them. Possibly the most widely used open-source CubeSat PCBs are the PyCubed. While these avionics platforms, programmable entirely in Python, are radiation-tested and integrate many control features into a single low-cost PCB, they lack of a proper mechanical characterization. Indeed, we believe that the knowledge of the dynamic behaviour of this PCB is crucial to achieve high-reliability CubeSats and to improve the mission success rates. For this reason, this paper will not only provide a mechanical and physical characterization of the PyCuded open-source printed circuits; but above all, it will generate an innovative simplified and reliable numerical model of the PCB that reflects the dynamic behaviour of the complete motherboard of components during the launch. To support and to complete the analysis, numerical/experimental modal comparisons will be used to validate the proposed models. In this way, all designers of PyCubed PCBs will be able to simulate, as realistically as possible, the complete mechanical behaviour of the printed circuit in the presence of components, reducing time, costs, and design risks. The approach the authors proposed, could also be used to model other generic types of printed circuits boards.

A novel design of CubeSat deployment system for transformable structures

One of the challenges of nanosatellites use is the limited payload volume. In this regard, transformable structures are frequently used in the development of nanosatellites. Most modern deployment mechanisms are based on thread burning. However, they have a significant disadvantage, which consists in a difficult procedure of thread replacement. The paper presents the novel design of a deployment system for CubeSat nanosatellites, which is based on Rose's alloy. In the “cold” state, the Rose's alloy holds the deployable structure in a closed position, and when temperature reaches 92–98° Celsius, the alloy melts and a structure deploys. On the basis of the experiments, the required heating power for deployment was determined. The heating time and kinematic characteristics of the system were also estimated experimentally. Our paper presents electronic circuitry and the deployment algorithm of the proposed system. We also consider abnormal operation of the deployment system. In addition, a set of environmental tests was carried out: thermal tests, vacuum tests, vibration and shock tests. The proposed system has successfully passed all the experiments and will be launched to space in 2022.

Development and application of an embedded computer system for CubeSats exemplified by the OPS-SAT space mission

The space industry is one of today’s major growth markets and a very interesting business sector for innovation, science, and technology. In the last century, the space industry has dramatically changed and undergone strong commercialization referred to as “New Space”. In addition to the commercialization, the concept of CubeSats has become well established in the market during the last decade. The European Space Agency (ESA) has acknowledged this trend and uses CubeSat nanosatellites for projects like the OPS-SAT mission. OPS-SAT uses state-of-the-art embedded systems for various tasks. These embedded systems are the key for the great mission success of OPS-SAT and provide outstanding computational power for various experiments conducted with the OPS-SAT flying laboratory. This paper describes the fundamental design of these embedded systems and discusses some of the related achievements during the OPS-SAT mission.

Technics for experimental determination of CubeSat mass-centering and inertial characteristics

Due to inability to set a high accuracy of initial data in theoretical calculations of mass-centering and inertial characteristics of nanosatellites, a problem arises concerning the experimental determination of their actual values. For a number of reasons, the devices designed for large spacecraft are not appropriate for small ones. This paper describes a device for measuring the center of mass coordinates and moments of inertia developed at Samara University specifically for CubeSat nanosatellites, as well as a technology for experimental determination of the design parameters of nanoclass spacecraft. The accuracy of determining the design parameters using the proposed device is confirmed by a series of experiments with standards. Key words: nanosatellite, center of mass coordinates, moment of inertia, inertia tensor, measuring platform.

W46. CRISPR/CAS9-MEDIATED CREATION OF A CELLULAR MODEL TO INVESTIGATE THE FUNCTION OF EGR1 TRANSCRIPTION FACTOR ASSOCIATED WITH SCHIZOPHRENIA

In complex software, such as various intelligent monitoring and control systems, the requirements for its reliability and safety increase. However, traditional reliability models cannot longer describe its reliability behavior with sufficient accuracy. This paper presents an approach to software reliability assessment using high-order Markov chains on an example of CubeSat nanosatellites flight software. The method uses the developed algorithm of high-order Markov process representation through an equivalent first-order process. The simulation results show that high-order Markov chains can increase the accuracy of the failure rate assessment up to 50%. Hence, the usage of the high-order reliability models is obvious for accurate and reliable evaluation of software reliability and safety.

S- И X-ДИАПАЗОННАЯ ПАТЧ-АНТЕННА ДЛЯ НАНОСПУТНИКОВ CUBESAT

The CubeSat concept has become very popular with both university groups and researchers, space agencies, governments and companies. CubeSat offers a fast and affordable way for a wide range of stakeholders to be active in space. Due to the high degree of modularity and widespread use of off­the­shelf commercial subsystems, CubeSat projects can be prepared for flight much faster than using traditional satellite schedules usually within one to two years. In this paper, we have considered a model of an S and X band patch antenna for CubeSat nanosatellites in the field of Earth remote sensing (ERS). The antenna dimensions were determined and designed according to the dimensions of the small spacecraft. The shape of the emitting part was formed using a geometric fractal with an anisotropic structure. Using the CST Microwave Studio software package, the electro­dynamic, frequency characteristics and directional properties of the antenna were determined. The results of computer simulations demonstrate that the developed antenna concept has a multi­band property and meets all the parameters that are necessary for receiving and transmitting data in the S and X bands. It was also found that the anisotropic fractal structure allows the antenna to have several operating frequencies.

Novel Omnimagnet actuation method for a Cubesat nano-satellite

In this work, an Omnimagnet is proposed to replace the commercially available three orthogonal Magnetorquers actuator commonly used in CubeSat nano-satellites. The Omnimagnet geometrical parameters were optimized to reduce weight and power consumption and maximize the magnetic dipole moment. Finite element analysis was carried out on the proposed magnetic actuator to calculate its output torque. The Omnimagnet proved its superior performance with respect to the three orthogonal Magnetorquers in providing the same torque with less weight and power consumption.

Предотвращение возможности возникновения резонансных режимов движения для низковысотных спутников класса CUBESAT

Resonant modes of motion, manifested as a significant increase in the oscillation amplitude of the spatial angle of attack, can result in the failure of the CubeSat mission. This paper is concerned with the study of the resonant motion modes of aerodynamically stabilized CubeSat nanosatellites in low circular orbits with small inertia and mass asymmetry. In contrast to axisymmetric bodies of rotation, resonances in CubeSat nanosatellites can be caused not only by small asymmetry, but they also arise due to the form factor of the rectangular parallelepiped. Formulas have been obtained to determine the critical values of the nanosatellite longitudinal angular velocity at which the conditions for the emergence of resonant motion modes are fulfilled. An approach is proposed to prevent possible resonances for CubeSat nanosatellites.

Reliability assessment of CubeSat nanosatellites flight software by high-order Markov chains

In complex software, such as various intelligent monitoring and control systems, the requirements for its reliability and safety increase. However, traditional reliability models cannot longer describe its reliability behavior with sufficient accuracy. This paper presents an approach to software reliability assessment using high-order Markov chains on an example of CubeSat nanosatellites flight software. The method uses the developed algorithm of high-order Markov process representation through an equivalent first-order process. The simulation results show that high-order Markov chains can increase the accuracy of the failure rate assessment up to 50%. Hence, the usage of the high-order reliability models is obvious for accurate and reliable evaluation of software reliability and safety.

Prototype of a Computer Vision-Based CubeSat Detection System for Laser Communications

Up to now, CubeSat nano-satellites have strong limitations in communication data rates ( $$\sim \hbox {100}$$ kbps) and bandwidth due to the strictness of CubeSat standard. However, if they could be endowed with optical communications (data rates up to 1 Gbps in optimal state), CubeSat applications would exponentially increase. Nonetheless, laser communications face some important drawbacks as the development of a very strict and accurate tracking mechanism. This work proposes an on-board fine pointing system to locate an optical ground station beacon using an embedded system complying with the restrictive CubeSat standard. Such on-board fine pointing system works based on computer vision. The experimental prototype is implemented in Matlab/Simulink, within a Raspberry Pi 3B. The main outcome is the usage of off-the-shelf components (COTS), obtaining an efficient tracking with low power consumption in very noisy and reflective environments. The developed system proves to be fast, stable and strong. It also satisfies the strict size and power consumption restrictions of CubeSat standard.

Procedure of experimental evaluation of nanoclass spacecraft design parameters using the ground test equipment

As it is impossible to set high accuracy of the initial data for theoretical calculations of the design parameters, such as the mass-centering and inertial characteristics of nanosatellites, the problem of experimental determination of their actual values arises. For a number of reasons, the devices designed for large spacecraft are not appropriate for the small ones. This paper describes a device developed at Samara University for measuring the center of mass coordinates and moments of inertia specifically for CubeSat nanosatellites, as well as a technology for experimental evaluation of the design parameters of nanoclass spacecraft. The accuracy of determining the design parameters using the proposed device is confirmed by a series of experiments with standards.

Анализ конструкции устройства аэродинамического торможения спутников CubeSat для увода с низких околоземных орбит

Clogging near-Earth outer space by spacecrafts that have failed is a threat of collision with functioning objects in space. To solve the problem of man-made debris, which may affect the development of cosmonautics in the future, a lot of collision avoidance maneuvers are proposed. The most feasible method is to use spherical braking devices providing a predictable descent of the satellite from the orbit, regardless of the orientation of its body, and the shortest time of departure from low earth orbits. Based on the results of the system analysis, the rational composition and configuration design of the device using spherical brake shells for deorbiting CubeSat nanosatellites from low Earth orbits were determined, taking into account the mass and size limitations of the standard 1U CubeSat module.

Design Parameters Selection for CubeSat Nanosatellite with a Passive Stabilization System

Probabilistic study of angular motion dynamics has been performed for CubeSat nanosatellites with passive stabilization systems, including aerodynamic, aerodynamic-gravitational, gravitational, and gravitational-aerodynamic ones. Analytical functions of the maximum angle values distribution have been obtained for a nanosatellite axes deviation from required directions (orbital velocity vector or a local vertical) for uniform distribution and Rayleigh distribution of component values of the initial angular velocity vector. Formulas have been derived and nomograms have been plotted for selecting the design parameters (geometrical dimensions, static stability margin, moments of inertia) which ensure the required attitude with the specified probability in circular orbits.

On the way to the optimal design of an inflatable aerodynamic decelerator of space debris removal system for CubeSat nanosatellites

In order to avoid pollution of the near-Earth space out-of-service small spacecrafts could be transferred to the disposal orbits in dense atmosphere with the help of inflatable decelerator. The issues of aerodynamics and heat transfer are of key importance for such systems design. The movement conditions in a low Earth orbit of a spherical inflatable aerodynamic decelerator designed for small spacecrafts removal are considered. The preliminary results of thermal analysis of the decelerator made of polymer film with the surface metallization are presented.

The heat transfer features of the thin-walled shell of an inflatable aerodynamic decelerator for CubeSat nanosatellites

Small spacecraft, first of all, nanosatellites of a CubeSat standard have a relatively small operational life. After their operational lives have expired, they turn into space debris. Disabled spacecraft can be transferred to the disposal orbit in the dense atmosphere using inflatable decelerators in order to avoid pollution of the near-Earth space. Decelerator’s temperature state is formed under the action of thermal radiation from the Sun and the Earth and kinetic heating caused by movement in a free-molecular medium. The specific features of heat transfer of inflatable decelerator’s thin-walled spherical shell are considered. The inflatable decelerator is designed for spacecraft removal during moving in the low-earth orbit.