General Analysis of Cube Satellite Technology: An Overview

International Journal of Aerospace Engineering, 2018

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.

medium platform, 2023

“Let us aspire to conduct more spectacular space missions in future years” Prepare to witness history in the making with the 75SSM program — a meticulously crafted initiative of Indian academia that will deploy an impressive fleet of 75 student-built satellites into low Earth orbit (LEO). This groundbreaking program pushes the boundaries of what’s possible in space exploration with cutting-edge technology and unprecedented student involvement. The 75SSM expedition is poised to be a remarkable achievement, ushering in a new era of space research and innovation.

In less than a decade, Cubesats have evolved from purely educational tools to a standard platform for technology demonstration and scientific instrumentation. The use of COTS (Commercial-Off-The-Shelf) components and the ongoing miniaturization of several technologies have already led to scattered instances of missions with promising scientific value. Furthermore, advantages in terms of development cost and development time with respect to larger satellites, as well as the possibility of launching several dozens of Cubesats with a single rocket launch, have brought forth the potential for radically new mission architectures consisting of very large constellations or clusters of Cubesats. These architectures promise to combine the temporal resolution of GEO missions with the spatial resolution of LEO missions, thus breaking a traditional tradeoff in Earth observation mission design. This paper assesses the current capabilities of Cubesats with respect to potential employment in Earth observation missions. A thorough review of Cubesat bus technology capabilities is performed, identifying potential limitations and their implications on 17 different Earth observation payload technologies. These results are matched to an exhaustive review of scientific requirements in the field of Earth observation, assessing the possibilities of Cubesats to cope with the requirements set for each one of 21 measurement categories. Based on this review, several Earth observation measurements are identified that can potentially be compatible with the current state-of-the-art of Cubesat technology although some of them have actually never been addressed by any Cubesat mission. Simultaneously, other measurements are identified which are unlikely to be performed by Cubesats in the next few years due to insuperable constraints. Ultimately, this paper is intended to supply a box of ideas for universities to design future Cubesat missions with high scientific payoff.

Nowadays, nanosatellites are widely used in space technology due to their small size, ease of deployment, and relatively short development period. CubeSat specifications have been suggested as an effort to standardize nanosatellite mission design. Standardization opens the door for inter-CubeSat communications that can be used to form a CubeSat Cloud and mimic regular large multifunctional satellites with wide range of features, measurements, and sensing capabilities. In this paper, we introduce a Comprehensive CubeSat (CoCube, Gurgaon, India) online database. CoCube database focuses mainly on the different subsystems used during the design and implementation stages of existing CubeSat missions. Based on the lessons learned by comparing various CubeSat design alternatives and components' structures and analyzing the best practices of CubeSat development, LibanSAT design is introduced. LibanSAT is a 1U CubeSat that serves two main objectives: (i) greenhouse gases observation and (ii) educational purposes. We benchmarked off-the-shelf subsystems from various suppliers and chose the most suitable for our target mission based on cost, size, weight, and power consumption. Finally, we introduce a new CubeSat security algorithm based on predefined anomaly detection baseline that serves as intrusion prevention system for the control channel.

Acta Astronautica, 2014

The paper deals with the mission analysis and conceptual design of an interplanetary 6U CubeSats system to be implemented in the L 1 Earth-Sun Lagrangian Point mission for solar observation and in-situ space weather measurements. Interplanetary CubeSats could be an interesting alternative to big missions, to fulfill both scientific and technological tasks in deep space, as proved by the growing interest in this kind of application in the scientific community and most of all at NASA. Such systems allow less costly missions, due to their reduced sizes and volumes, and consequently less demanding launches requirements. The CubeSats mission presented in this paper is aimed at supporting measurements of space weather. The mission envisages the deployment of a 6U CubeSats system in the L 1 Earth-Sun Lagrangian Point, where solar observations for in situ measurements of space weather to provide additional warning time to Earth can be carried out. The proposed mission is also intended as a technology validation mission, giving the chance to test advanced technologies, such as telecommunications and solar sails, envisaged as propulsion system. Furthermore, travelling outside the Van Allen belts, the 6U CubeSats system gives the opportunity to further investigate the space radiation environment: radiation dosimeters and advanced materials are envisaged to be implemented, in order to test their response to the harsh space environment, even in view of future implementation on other spacecrafts (e.g. manned spacecrafts). The main issue related to CubeSats is how to fit big science within a small package-namely power, mass, volume, and data limitations. One of the objectives of the work is therefore to identify and size the required subsystems and equipment, needed to accomplish specific mission objectives, and to investigate the most suitable configuration, in order to be compatible with the typical CubeSats (multi units) standards. The work has been developed as collaboration between Politecnico di Torino, Sapienza University of Rome, "Osservatorio Astrofisico di Torino-INAF" (Astrophysical Observatory of Torino) and DLR (Deutsches Zentrum für Luft-und Raumfahrt) in Bremen.

2014

This paper introduces 3 Cat-1, the first project of the Universitat Politècnica de Catalunya to build and launch a pico-satellite. Its main scope is to develop, construct, assembly, test and launch into a Low Earth Orbit a CubeSat with seven different payloads (mono-atomic oxygen detector, Graphene transistor, self-powered beacon, Geiger radiation counter, wireless power transfer, new topology solar cells and wireless power transfer experiment) are all fitted in a single unit CubeSat. On one hand, this is mainly an educational project in which the development of some of the subsystems is carried out by Master Thesis students. On the other hand, the satellite demonstrates its capabilities as optimum platform to perform small scientific experiments, and to demonstrate some of the new technologies that it incorporates. 3 Cat-1 launch is scheduled by summer 2014.

With the advent of the first satellite Sputnik, a new era for mankind has opened. With this new era, the concepts of satellites have become more important than ever for the amenities of the modern civilization that we enjoy today. However, there is still a great need for improvement in satellite technology and this can be best achieved by various Nanosatellite research and deployment programs. Due to its specific nature and its operational dynamics related to its vast application, a Nanosatellite programme can be very efficiently and effectively implemented under a University's R&D programme. Until today, many Nanosatellite have been successfully developed, launched and used by various Universities all across the world and many useful information and experience have come out of these activities. In this particular paper, a case study analysis of an ideal Nanosatellite research and deployment program for universities will be shown. This paper can serve as a fundamental case study of a Nanosatellite program and academic and research organizations can use this as a guideline for their programs. An optimal near polar, low earth orbit is calculated for this Nanosatellite along with its structural configurations. The orbit is calculated keeping in mind certain geographical constraints which defines the basic objectives of the mission. Moreover, different attitude adjustments systems are explored in order to create the most stable configuration in orbit. In addition, possible payload configurations for this particular case study will be analyzed and the corresponding launch systems along with its costs will be explored. The main focus will be on creating the most optimal configuration with the minimum of production and launching costs for the Nanosatellite. Thus, the payload capability as well as the launch configuration along with the orbit will be calculated accordingly. This paper hopes to demonstrate the technical aspects as well as the educational aspects of a University Cubesat project

Nowadays, with new technologies, smaller and cheaper satellites have been designed and launched. Such satellites fit as educational tools to future engineers. With few kilograms and reduced dimensions, they have simple operation, despite being complete systems capable to perform real missions. Having short life cycles, from design to disposal, they allow students to follow a complete project during academic lives. In this paper a generic platform for an 1U CubeSat is proposed, designed according to NASA and CubeSat Initiative standards. For so, typical loads during flight trajectory were considered. Cost, related to mass and benefits were contemplated for materials choice. Simulations on testing and launching conditions were performed in a systemic analysis. The structure was chosen using comparative method and possible arrangements of components were examined. The behavior of the structure both empty and with components was studied using FEM, with static load, natural frequencies, random and sinusoidal vibrations and impact analyses. The mass of the structure was reduced and the geometry adapted to allow better attachment of components. The final 1U structure is not heavier than commercial ones and allows mass reduction. It fulfills main structural requirements for 1U CubeSats imposed by CDS. This result is ready to be used by educational initiatives.

International Journal of Aerospace Engineering, 2019