CubeSat Platform Research Articles

Parabolic transformable reflector for CubeSat platform

CubeSat platform is used for creating small spacecrafts. Antennas for transmission of signals between the spacecraft and subscribers are inalienable parts of it. Different antenna configurations may be installed on a spacecraft depending on functions of their payload. Spacecrafts based on the CubeSat platform are equipped with transformable antennas with a drop-down reflector. There are several requirement to the construction of the reflector designed for operating via the CubSat platform: small volume in folded state; maximal aperture of a parabolic reflective surface in working position; ensuring the required accuracy characteristics of the reflective surface; simplicity of the opening mechanism and low weight. Usage of flexible swivel joints in the design of the antenna allows to create a simple and reliable opening mechanism and to provide the necessary rigidity of the structure and a small mass of the reflector. The paper proposes a new design of a transformable parabolic reflector for a spacecraft on the CubeSat platform. The main power element is a thin-walled torus shell with a reflector opening mechanism in the form of flexible hinges. A geometric analysis was carried out to determine the configuration of the reflector in the folded position. Modal analysis was completed to confirm that the required stiffness was achieved. Based on the analysis results, the design characteristics of the structure were selected that satisfy the condition of the minimum mass of the reflector. A technological process for manufacturing a reflector was developed, with the help of which the model of the structure was made. Reflector tests which were the transformation of the structure from the working position to the transport position and vice versa were carried out. The produced layout demonstrated the possibility of creating flight reflectors, the transform.

Kisműholdak fejlesztése a sokoldalúság és a könnyű reprodukálhatóság tükrében

A világűr mára már nem csak a gazdasági nagyhatalmak kiváltsága. A társuló technológia fejlődésének hatására bekövetkező költségcsökkenés eredményeképpen napjainkban akár egy kis cég, alacsony költségvetéssel is megmérettetheti magát a 21. század űrversenyében. Ehhez biztosítanak tökéletes platformot a nano- és mikroműholdak, amelyek alkalmazási lehetőségei folyamatosan bővülnek. Az egyre változatosabb hasznos terhek azonban értéktelenek a sokoldalú platformok és azok alapvető alrendszerei nélkül, mint például a fedélzeti számítógép, tápegység, kommunikációs egység vagy a műhold térbeli orientációjáért felelős alrendszer (Attitude Determination and Control System – ADCS). Így felmerül az igény egy olyan univerzális műholdplatform fejlesztésére, amelyben a létfontosságú alrendszerek biztosítva vannak különböző, harmadik fél által fejlesztett hasznos terhek, illetve tudományos kísérleti eszközök számára. Ezzel létrehozhatunk egy standardizált, költséghatékony és rugalmasan bővíthető, ezáltal még szélesebb körben elérhető kisműholdas platformot. A cikkben részletesen bemutatunk egy, a fentiekben leírt követelményeknek megfelelő univerzális CubeSatplatformot, kitérünk az egyedi mérnöki módszereket és megoldásokat igénylő fejlesztési folyamatokra, a nagy megbízhatóságú szoftvertechnológia előnyeire és a platform nyújtotta új lehetőségekre.

UVSQ-SAT, a Pathfinder CubeSat Mission for Observing Essential Climate Variables

The UltraViolet and infrared Sensors at high Quantum efficiency onboard a small SATellite (UVSQ-SAT) mission aims to demonstrate pioneering technologies for broadband measurement of the Earth’s radiation budget (ERB) and solar spectral irradiance (SSI) in the Herzberg continuum (200–242 nm) using high quantum efficiency ultraviolet and infrared sensors. This research and innovation mission has been initiated by the University of Versailles Saint-Quentin-en-Yvelines (UVSQ) with the support of the International Satellite Program in Research and Education (INSPIRE). The motivation of the UVSQ-SAT mission is to experiment miniaturized remote sensing sensors that could be used in the multi-point observation of Essential Climate Variables (ECV) by a small satellite constellation. UVSQ-SAT represents the first step in this ambitious satellite constellation project which is currently under development under the responsibility of the Laboratory Atmospheres, Environments, Space Observations (LATMOS), with the UVSQ-SAT CubeSat launch planned for 2020/2021. The UVSQ-SAT scientific payload consists of twelve miniaturized thermopile-based radiation sensors for monitoring incoming solar radiation and outgoing terrestrial radiation, four photodiodes that benefit from the intrinsic advantages of Ga 2 O 3 alloy-based sensors made by pulsed laser deposition for measuring solar UV spectral irradiance, and a new three-axis accelerometer/gyroscope/compass for satellite attitude estimation. We present here the scientific objectives of the UVSQ-SAT mission along the concepts and properties of the CubeSat platform and its payload. We also present the results of a numerical simulation study on the spatial reconstruction of the Earth’s radiation budget, on a geographical grid of 1 ° × 1 ° degree latitude-longitude, that could be achieved with UVSQ-SAT for different observation periods.

Multi-Needle Langmuir Probe System for Electron Density Measurements and Active Spacecraft Potential Control on CubeSats

In this paper, we present the CubeSat version of a scientific instrument called the multi-Needle Langmuir Probe (m-NLP). The m-NLP instrument measures the electron density in the ionosphere with kHz sampling rate, yielding meter scale resolution on low Earth orbit satellites. The sounding rocket version of m-NLP has flight heritage from nine sounding rockets. However, to get an in-orbit demonstration of the system a CubeSat implementation has been developed. The m-NLP measurement principle is based on several fixed bias probes, where each probe has to be biased above the spacecraft potential. To ensure that this requirement is fulfilled, the CubeSat version of the m-NLP will feature a new miniaturized thermionic electron emitter, which can actively control the potential of the satellite. The emitter is designed to accommodate the low size, weight, and power challenges of the CubeSat platform. Together with the in-flight determination of the spacecraft floating potential, it can autonomously control the potential of the spacecraft by emitting electrons. Preliminary, test results from the plasma chamber at the European Space and Technology Center in Holland are shown, verifying that a miniaturized electron emitter is able to actively control the floating potential of the spacecraft and, hence, improve the accuracy of the electron density measurements.

Validation of a Test Platform to Qualify Miniaturized Electric Propulsion Systems

Miniaturized electric propulsion systems are one of the main technologies that could increase interest in CubeSats for future space missions. However, the integration of miniaturized propulsion systems in modern CubeSat platforms presents some issues due to the mutual interactions in terms of power consumption, chemical contamination and generated thermal and electro-magnetic environments. The present paper deals with the validation of a flexible test platform to assess the interaction of propulsion systems with CubeSat-technologies from mechanical, electrical, magnetic, and chemical perspectives. The test platform is a 6U CubeSat hosting an electric propulsion system and able to manage a variety of electric propulsion systems. The platform can regulate and distribute electric power (up to 60 W), exchange data according to several protocols (e.g., CAN bus, UART, I2C, SPI), and provide different mechanical layouts in 4U box completely dedicated to the propulsion system. Moreover, the data gathered by the onboard sensors are combined with the data from external devices and tools providing unprecedented information about the mutual behavior of a CubeSat platform and an electric propulsion system.

Physically Controlled CubeSat Antennas With an Adaptive Frequency Operation

This letter advocates the use of mechanical actuation to alter the electrical length of components within antenna elements proposed for implementation onto a CubeSat platform. Such electrical length alteration reconfigures the antenna's frequency operation without affecting its polarization scheme. This concept is first demonstrated on a reconfigurable quadrifilar helix that reconfigures its frequency operation between 750 MHz and 1 GHz, while maintaining a circular polarization behavior. As a second demonstration, a Yagi–Uda antenna is reconfigured by changing the electrical length of its reflector, fed elements, and two directors. Such alteration results in a frequency reconfiguration between 1.2 and 1.5 GHz, while preserving the linear polarization behavior of the antenna array. For both antenna examples, the reconfiguration is implemented through the appropriate mechanical actuators that are integrated within the CubeSat's cavity. As a proof of concept, both structures are fabricated and integrated on the outside chassis of a 6U CubeSat $(\text{10}\times \text{20}\times \text{30}\,\text{cm}^{3})$ , where measured results greatly match the simulated data.

High-Resolution Image and Video CubeSat (HiREV): Development of Space Technology Test Platform Using a Low-Cost CubeSat Platform

In this paper, we present high-resolution image and video CubeSat (HiREV), the first constructed 6 U platform to reach the space technology test bed stage, developed by the Korea Aerospace Research Institute (KARI). The CubeSat system is a low-cost platform that has been widely applied to various space missions, from missions involving earth observation to deep space. Despite the emergence of the CubeSat technology worldwide, the CubeSat market in Korea is still in the beginning stages, and a standard testing platform is also in demand. For this reason, KARI is starting to develop a 6 U CubeSat platform, which includes a less than 3 U bus system and greater than 3 U payload space. HiREV has been developed with locally manufactured parts, creating a domestic commercial off-the-shelf infrastructure for CubeSat and 3 m resolution camera payload development. Core flight software has also been applied as an on-board flight software system. Presently, we have developed the main system, while HiREV is under space environmental testing.

Design and Implementation of 3U CubeSat Platform Architecture

This paper describes the main concept and development of a standard platform architecture of 3U Cube Satellite, whose design and performance were implemented and verified through the development of KAUSAT-5 3U CubeSat. The 3U standard platform is built in 1.5U size and developed as a modular concept to add and expand payloads and attitude control actuators to meet the user’s needs. In the case of the electrical power system, the solar panel, the battery, and the deployment mechanism are designed to be configured by the user. Mechanical system design maximizes the electrical capability to accommodate various payloads and to integrate and miniaturize EEE (Electrical, Electronic, and Electromechanical) parts and subsystem functions/performance into limited-size PCBs. The performance of KAUSAT-5 adopting standard platform was verified by mounting the VSCMG (Variable Speed Control Moment Gyro), which is one payload for technical demonstration, at the bottom of the platform and the infrared (IR) camera, which is the other payload for science mission, on the top. The 3U CubeSat equipped with the electronic optical camera is under development implementing the standard platform to reduce development cost and schedule by minimizing additional verification.

A high gain S-band slot antenna with MSS for CubeSat

Cube satellites, aka CubeSats, are a class of tiny satellites that have become popular for space programs. This is because they can be built relatively cheaply using commercial off-the-shelf components. Moreover, CubeSats can communicate with each other, and assemble into swarms to carry out different functions: e.g., wide area measurements and sensing. Swarms of CubeSats also have the effect of increasing the contact period with ground stations allowing for a longer communications window. These capabilities require CubeSats to be equipped with an efficient, high gain, small antenna to facilitate cross-link or inter-satellite communications. Henceforth, this paper presents a high gain coplanar waveguide (CPW)–fed slot antenna for CubeSats. A key feature is the use of a metasurface superstrate structure (MSS) to significantly improve gain and reduce back-lobe emissions. This also has the advantage of minimizing interference to components inside a CubeSat. We have comprehensively evaluated the antenna using the high-frequency simulator structure (HFSS) as well as a carrying out testing on a 3 U (10 × 10 × 30 cm3) CubeSat platform. We have studied the effect of MSS element sets and their position and the effect of a 3-U CubeSat body on the performance of the proposed antenna. The experimental results confirm that our antenna achieves a return loss of 21.5 dB and a fractional impedance bandwidth (BW) of 55.91% with S11 ≤ 10 dB and has a simulated and measured gains of 9.71 and 8.8 dBi respectively at the desired frequency of 2.45 GHz. In contrast, amongst all previous S-band planar antennas that are suitable for CubeSats, the best gain is only 5.96 dB at 2.45 GHz.

ПРИМЕНЕНИЕ СТАНДАРТА ШИРОКОПОЛОСНОГО ДОСТУПА IEEE 802.16 ДЛЯ ОПРЕДЕЛЕНИЯ ВЗАИМНОГО ПОЛОЖЕНИЯ КУБСАТОВ В СОСТАВЕ LEGA-SAT

It is considered the possibility of optimizing the use of the power capabilities of the cube-sat platform included in the "distributed satellite" to improve the performance of its payload. To optimize the use of energy capabilities, it was proposed to disconnect the onboard equipment of the command-and-telemetric radio link in the mode of regular operation of cube-sat in the "distributed satellite". To measure the current navigation parameters of cube-satellite in the conditions of group flight in the "distributed satellite" it is proposed to use the coordinates of the cube-satellite in the satellite coordinate system of the "distributed satellite" root satellite and the relative cube-relative velocity vector relative to the root satellite as the initial data. It is proposed to use a technique based on measurements of the distances between satellites in a "distributed satellite" and the projections of the vector of relative velocity for these distances to determine the coordinates of cube-sat in the satellite coordinate system. The features of the WiMAX broadband access protocol IEEE 802.16 protocols are examined to determine whether it is possible to perform mutual position measurements of satellites as part of a "distributed satellite" in one channel with information transmission. It pointed that the use of built-in means of measuring the range and access of mobile stations to the mobile WiMAX network makes it possible to perform measurements of the distance from the root satellite to the final satellite - cube-sat in the "distributed satellite". To perform the operations of measuring distances between the final satellites in the "distributed satellite", it is proposed to use the "competitive access zone" of the uplink sub-frame in the WiMAX network. A procedure for measuring the range between terminal satellites is proposed, based on measuring the propagation time of the distance measurement test signal between the assigned terminal satellites. It proposed a procedure for transmitting a test signal, taking into account the features of multiple access with orthogonal carrier separation (OFDMA). The proposed procedure can be implemented in a variant of the IEEE 802.16 standard network for application in a "distributed satellite"

Snow and Water Imaging Spectrometer: mission and instrument concepts for earth-orbiting CubeSats

The Snow and Water Imaging Spectrometer (SWIS) is a science-grade imaging spectrometer designed for CubeSat integration, spanning a 350- to 1700-nm spectral range with 5.7-nm sampling, a 10-degree field-of-view, and 0.3-mrad spatial resolution. The system operates at F / 1.8, providing the high throughput for low-reflectivity (<1 % ) water surfaces, while avoiding saturation over bright snow or clouds. The SWIS design utilizes heritage from previously demonstrated instruments on airborne platforms while advancing the state of the art in compact sensors of this kind in terms of size and spectral coverage. Compared with airborne campaigns, the CubeSat platform allows for more frequent and regular sampling, while maintaining intermediate to high resolution relative to heritage global sensors. Through frequent repeat observations from space at a moderate spatial resolution, SWIS can address key science questions concerning aquatic and terrestrial ecosystem changes, cryosphere warming and melt behavior, cloud and atmospheric science, and potential impacts of climate change and human activities on the environment.

Resolution limit of anisotropic magnetoresistance(AMR) based vector magnetometer

An AMR based vector magnetometer was developed for the Separated Payload program to explore the field-aligned currents in Earth polar region. It has the advantages of low volume and CubeSat platform compatible mass while still maintains adequate resolution. In order to determine the resolution limit of AMR based magnetometer, we measured the sensor’s intrinsic noise. This characteristic was in conflict with our prototype magnetoresistive magnetometer since phase sensitive detection(PSD) could only reject noise from interfacing circuit without affecting the signal to be measured. We believe that besides flipping the magnetization direction periodically, the set/reset technique also functions as a modulation to the magnetic field. The sensor operates at the modulation frequency and its noise level is much lower than that at low frequency. This technique is analyzed theoretically and a description from frequency perspective is given. By modulating the signal beyond corner frequency of the sensor and amplifier, both the sensor and interfacing circuit work in white noise region. Then we calculate the theoretical resolution limit of HMC1001 based magnetometer and the result shows that the noise floor is 24.9 pT/Hz0.5@1 Hz under 5 V bias with proper-matched amplifier.

Design, Analysis, Optimization, Manufacturing, and Testing of a 2U Cubesat

The design optimization, development, and verification by analysis and testing of the 1st Greek cubesat, developed by the University of Patras and Libre Space Foundation (UPSat (University of Patras Satellite)), is presented. The key innovative approach includes the replacement of the aluminum side faces with structural composite components, keeping the commonly used aluminum frame. A “hybrid” double-unit (2U) cubesat structure was optimized, built, and tested for all launch and thermal loads/specifications required for launch and mission operations as imposed from the EU-funded FP7-QB50 project. Results show that the new design of the structure using CFRP can offer similar levels of performance in terms of stiffness, while saving 30% of the mass, for the entire cubesat platform.

СОЗДАНИЕ АРХИТЕКТУРЫ «РАСПРЕДЕЛЕННОГО СПУТНИКА» ДЛЯ НИЗКООРБИТАЛЬНЫХ ИНФОРМАЦИОННО-ТЕЛЕКОММУНИКАЦИОННЫХ СИСТЕМ НА ОСНОВЕ ГРУППИРОВКИ МИКРО- И НАНОСПУТНИКОВ

Presented are the results of an analysis of the growing interest in the use of low Earth orbits (up to 1500 km high) for the introduction and development of the Internet of things (Internet of Things - IoT). Industrial Internet of things (Industrial Internet of Things-IIoT). Internet of things for remote areas (Remote Internet of Things - RioT, for the purposes of scientific research and economic use of natural resources, control of the development and operation of infrastructure projects, the operation of territorially distributed industrial production, transport infrastructure. Factors significantly limiting the further introduction of micro and nano satellites are given. The authors proposed to resolve this contradiction on the basis of the developed concept of creating the architecture of a "distributed satellite". As an example, the article considers possible applications of the distributed satellite architecture in two segments of the space information systems market: remote sensing of the Earth and telecommunication systems. The application of the "distributed satellite" in radar systems with synthesized aperture (SAR-system) was considered taking into account the requirements of the operators of satellite SAR-systems and consumers of their information. It is shown. that the use of the "distributed satellite" architecture in SAR-systems also makes it possible to realize the technology of multi-static radar with a "soft" interference base (from 200 m to 1 km). The scheme of organization and interaction of the "distributed satellite" in the satellite-transmitter on the platform of the micro satellite, which is the core of the satellite cluster, and several satellites-receivers on the cube-sat platform is presented. The functions performed by the satellite-transmitter, the inter-satellite radio link and the satellite-receiver are considered in detail. The work of the "distributed satellite" is illustrated by the presented structural diagram of the SAR-system for remote sensing of the Earth, a version of the architecture of the low-orbit satellite communication system and the scheme for constructing a satellite system for the provision of IoT services. In conclusion, it is noted that the architecture of the "distributed satellite" makes it possible to effectively use satellites of the class of micro/nano satellite (cube-sat) to create complex space-based information and telecommunication systems

Design of a CubeSat payload to test a magnetic measurement system for space-borne gravitational wave detectors

Space observatories for gravitational radiation such as LISA are equipped with dedicated on-board instrumentation capable of measuring magnetic fields with low-noise conditions at millihertz frequencies. The reason is that the core scientific payload can only operate successfully if the magnetic environment meets certain strict low-frequency requirements. With this purpose, a simplified version of the proposed magnetic measurement system for LISA has been developed for a six-unit CubeSat, which will make it possible to improve the technology readiness level (TRL) of the instrument. The special feature of the experiment is that the magnetic sensors integrated in the payload are magnetically shielded to low-frequency fluctuations by using a small cylindrical permalloy enclosure. This will allow the in-flight noise characterization of the system under the CubeSat orbit environment. Therefore, a CubeSat platform will offer the opportunity to measure the capability of the instrument and will guide the progress towards the improved magnetic measurement system for LISA. This article describes the principal characteristics and implementation of the CubeSat payload.

Highly miniaturized FEEP propulsion system (NanoFEEP) for attitude and orbit control of CubeSats

A highly miniaturized Field Emission Electric Propulsion (FEEP) system is currently under development at TU Dresden, called NanoFEEP [1]. The highly miniaturized thruster heads are very compact and have a volume of less than 3 cm3 and a weight of less than 6 g each. One thruster is able to generate continuous thrust of up to 8 μN with short term peaks of up to 22 μN. The very compact design and low power consumption (heating power demand between 50 and 150 mW) are achieved by using Gallium as metal propellant with its low melting point of approximately 30 °C. This makes it possible to implement an electric propulsion system consisting of four thruster heads, two neutralizers and the necessary electronics on a 1U CubeSat with its strong limitation in space, weight and available power. Even formation flying of 1U CubeSats using an electric propulsion system is possible with this system, which is shown by the example of a currently planned cooperation project between Wuerzburg University, Zentrum fuer Telematik and TU Dresden. It is planned to use the NanoFEEP electric propulsion system on the UWE (University Wuerzburg Experimental) 1U CubeSat platform [2] to demonstrate orbit and two axis attitude control with our electric propulsion system NanoFEEP. We present the latest performance characteristics of the NanoFEEP thrusters and the highly miniaturized electronics. Additionally, the concept and the current status of a novel cold neutralizer chip using Carbon Nano Tubes (CNTs) is presented.

³Cat-3/MOTS Nanosatellite Mission for Optical Multispectral and GNSS-R Earth Observation: Concept and Analysis.

The 3Cat-3/MOTS (3: Cube, Cat: Catalunya, 3: 3rd CubeSat mission/Missió Observació Terra Satèl·lit) mission is a joint initiative between the Institut Cartogràfic i Geològic de Catalunya (ICGC) and the Universitat Politècnica de Catalunya-BarcelonaTech (UPC) to foster innovative Earth Observation (EO) techniques based on data fusion of Global Navigation Satellite Systems Reflectometry (GNSS-R) and optical payloads. It is based on a 6U CubeSat platform, roughly a 10 cm × 20 cm × 30 cm parallelepiped. Since 2012, there has been a fast growing trend to use small satellites, especially nanosatellites, and in particular those following the CubeSat form factor. Small satellites possess intrinsic advantages over larger platforms in terms of cost, flexibility, and scalability, and may also enable constellations, trains, federations, or fractionated satellites or payloads based on a large number of individual satellites at an affordable cost. This work summarizes the mission analysis of 3Cat-3/MOTS, including its payload results, power budget (PB), thermal budget (TB), and data budget (DB). This mission analysis is addressed to transform EO data into territorial climate variables (soil moisture and land cover change) at the best possible achievable spatio-temporal resolution.

Universal CubeSat Platform Design Technique

This article summarizes cubesat technology, provides examples of their scientific impact, and describes the design and the manufacturing of a Cubesat platform. As for the design of the overall frame structure of the CubeSat, we have searched a lot of literature and consulted many predecessors' designs, and collected many satellite structure images. After analyzing the data, we aimed at all kinds of different structures’ advantages and disadvantages, finally we got a best design. It is a satellite of cubic shape (10 cm per side), weighing approximately 1kg, based on the creation of a central body made of different material using the 3D-Printing techniques. The 3D-Printing technique has several advantages including fast implementation, accuracy in manufacturing small parts and low cost. Moreover, concerning the construction of a small satellite, this technique is very useful thanks to the accuracy achievable in details, which are sometimes difficult and expensive to realize with the use of tools machine. The structure must be able to withstand the launch loads. For this reason, several simulations using an FEM simulation and an intensive vibration test campaign will be performed in the system development and test phase.

Preliminary orbital analysis for a CubeSat mission to the Didymos binary asteroid system

Nanosatellite missions represent a promising option for the exploration of the near-Earth asteroid population since they provide low-cost versatile platforms for scientific observations. This paper describes the preliminary orbital and navigation analyses for the DustCube mission, which was pre-selected to reach the binary asteroid system Didymos on-board ESA’s AIM spacecraft. Possible candidate orbits that exploit the binary nature of the system are identified and traded off to produce a preliminary concept of operations. The overall feasibility of the proposed scenario is then addressed by integrating the spacecraft trajectories in a realistic dynamical environment, evaluating their sensitivity to state errors, and estimating the accuracy of the orbit determination system.Preliminary results suggest that autonomous navigation of a Cubesat platform within a binary asteroid system is technically feasible. The proposed solution, which combines an initial parking orbit at the L4 equilibrium point with a Distant Retrograde Orbit for proximity operations, is shown to be consistent with the estimated orbit determination accuracy and allows to fulfil the mission requirements.

Feasibility of asteroid exploration using CubeSats—ASPECT case study

Operation of a small CubeSat in the deep-space microgravity environment brings additional challenging factors including the increased radiation environment, the significant contribution of non-gravitational forces to the satellite orbit, or the limited communication opportunities. These factors need to be taken into account in the form of modifications to the classic CubeSat architecture. Increased radiation resistance, the semi-autonomous satellite operation, navigation, and the active orbit correction are required. Such a modified CubeSat platform can potentially deliver a high performance to mass and cost ratios. The Asteroid Spectral Imaging Mission (ASPECT) is a three unit (3U) CubeSat mission built on these principles. It is part of the AIDA (Asteroid Impact & Deflection Assessment) project to the binary asteroid Didymos. ASPECT is equipped with a visible to near-infrared hyperspectral imager and will deliver both technological knowledge as well as scientific data about the origin and evolution of Solar System small bodies.