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Attitude Stabilization For Cubesat
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Book Synopsis Attitude Stabilization for CubeSat by : Mohammed Chessab Mahdi
Download or read book Attitude Stabilization for CubeSat written by Mohammed Chessab Mahdi and published by Cambridge Scholars Publishing. This book was released on 2018-11-14 with total page 190 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book explores CubeSat technology, and develops a nonlinear mathematical model of a spacecraft with the assumption that the satellite is a rigid body. It places emphasis on the CubeSat subsystem, orbit dynamics and perturbations, the satellite attitude dynamic and modeling, and components of attitude determination and the control subsystem. The book focuses on the attitude stabilization methods of spacecraft, and presents gravity gradient stabilization, aerodynamic stabilization, and permanent magnets stabilization as passive stabilization methods, and spin stabilization and three axis stabilization as active stabilization methods. It also discusses the need to develop a control system design, and describes the design of three controller configurations, namely the Proportional–Integral–Derivative Controller (PID), the Linear Quadratic Regulator (LQR), and the Fuzzy Logic Controller (FLC) and how they can be used to design the attitude control of CubeSat three-axis stabilization. Furthermore, it presents the design of a suitable attitude stabilization system by combining gravity gradient stabilization with magnetic torquing, and the design of magnetic coils which can be added in order to improve the accuracy of attitude stabilization. The book then investigates, simulates, and compares possible controller configurations that can be used to control the currents of magnetic coils when magnetic coils behave as the actuator of the system.
Book Synopsis Optimal Attitude Control Management for a Cubesat by : Michael James Develle (II.)
Download or read book Optimal Attitude Control Management for a Cubesat written by Michael James Develle (II.) and published by . This book was released on 2011 with total page 49 pages. Available in PDF, EPUB and Kindle. Book excerpt: CubeSats have become popular among universities, research organizations, and government agencies due to their low cost, small size, and light weight. Their standardized configurations further reduce the development time and ensure more frequent launch opportunities. Early cubesat missions focused on hardware validation and simple communication missions, with little requirement for pointing accuracy. Most of these used magnetic torque rods or coils for attitude stabilization. However, the intrinsic problems associated with magnetic torque systems, such as the lack of three-axis control and low pointing accuracy, make them unsuitable for more advanced missions such as detailed imaging and on-orbit inspection. Three-axis control in a cubesat can be achieved by combining magnetic torque coils with other devices such as thrusters, but the lifetime is limited by the fuel source onboard. To maximize the mission lifetime, a fast attitude control management algorithm that could optimally manage the usage of the magnetic and thruster torques is desirable. Therefore, a recently developed method, the B-Spline-augmented virtual motion camouflage, is presented in this defense to solve the problem. This approach provides results which are very close to those obtained through other popular nonlinear constrained optimal control methods with a significantly reduced computational time. Simulation results are presented to validate the capabilities of the method in this application.
Book Synopsis Spacecraft Attitude Determination and Control by : J.R. Wertz
Download or read book Spacecraft Attitude Determination and Control written by J.R. Wertz and published by Springer Science & Business Media. This book was released on 2012-12-06 with total page 877 pages. Available in PDF, EPUB and Kindle. Book excerpt: Roger D. Werking Head, Attitude Determination and Control Section National Aeronautics and Space Administration/ Goddard Space Flight Center Extensiye work has been done for many years in the areas of attitude determination, attitude prediction, and attitude control. During this time, it has been difficult to obtain reference material that provided a comprehensive overview of attitude support activities. This lack of reference material has made it difficult for those not intimately involved in attitude functions to become acquainted with the ideas and activities which are essential to understanding the various aspects of spacecraft attitude support. As a result, I felt the need for a document which could be used by a variety of persons to obtain an understanding of the work which has been done in support of spacecraft attitude objectives. It is believed that this book, prepared by the Computer Sciences Corporation under the able direction of Dr. James Wertz, provides this type of reference. This book can serve as a reference for individuals involved in mission planning, attitude determination, and attitude dynamics; an introductory textbook for stu dents and professionals starting in this field; an information source for experimen ters or others involved in spacecraft-related work who need information on spacecraft orientation and how it is determined, but who have neither the time nor the resources to pursue the varied literature on this subject; and a tool for encouraging those who could expand this discipline to do so, because much remains to be done to satisfy future needs.
Book Synopsis Development of an Attitude Control System for CubeSat Application by : Joshua Francis Reginald O'Neill
Download or read book Development of an Attitude Control System for CubeSat Application written by Joshua Francis Reginald O'Neill and published by . This book was released on 2022 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Guidance, navigation, and control (GNC) systems are commonly found in vehicles, whether they be spacecraft, aircraft, seacraft or landcraft. These systems are designed to bring the vehicle to its desired position and/or orientation by sensing pose and making the necessary adjustments to onboard devices. With regard to satellites, GNC systems are divided into two segments: orbit control, which is concerned with the spacecraft's position, and attitude control, which is concerned with the spacecraft's orientation. The focus of this thesis is to develop the attitude control system of a CubeSat nanosatellite being designed for the University of Prince Edward Island's SpudNik-1 mission. The objective of this study was to progress the design of the attitude control system (ACS) from its conceptual design phase to a state where it is ready for assembly, integration, and testing. To accomplish this, the engineering design process was applied. Accordingly, the fundamentals of attitude control were first reviewed in literature. Then, the system-level requirements were evaluated and the current design's ability to meet them was assessed. After doing so, the necessary alterations were made to the conceptual design, such that it would meet the requirements, and the various methods of requirement verification were defined to verify that this is the case during the assembly, integration, and testing phase. Once the system-level design had been established, this process was repeated for the subsystem- and unit-level designs. In addition to contributing the detailed design of an attitude control system to the Spudnik-1 team, this work can also serve as a reference for other teams working toward space missions that require the use of an ACS by providing a comprehensive perspective that focuses on the identification, integration, and implementation of the major elements of an attitude control system. It not only offers detailed information on the definition, measurement, modeling, estimation, and control of a spacecraft's attitude, but also identifies: the connections between these concepts; the hardware used to implement the concepts in a real-world application; and the various considerations that should be taken during this implementation. Aside from familiarizing the reader with the methodology behind an ACS system, this work also describes the procedure that was used to develop the attitude control subsystem of the SpudNik-1 CubeSat. It details: how the requirements of the attitude control subsystem were identified from the spacecraft's mission and the corresponding system requirements; how the major components and concepts of the ACS are identified from the subsystem requirements, and integrated through the subsystem architecture; how the unit-level requirements are identified based on the subsystem-level design; and how the implementation of the various components and concepts is dependent on the unit level requirements. While a good deal of the design is standard with regard to CubeSats and other aerospace projects, the original aspects would relate to the in-house design of the reaction wheels and fine sun sensors. Being as there are a wide selection of ACS components available on the market, it is most common for CubeSat projects to procure their hardware. Although the lack of flight heritage did pose additional risk to the mission in comparison to using commercial equipment, the in-house design allowed the components to be both tailored to the mission and produced at a fraction of the cost. If the designs manage to gain flight heritage on-board of the SpudNik-1 CubeSat, then this work will provide readers with standard frameworks which will allow them to reap the same benefits, but at a lower level of risk.
Book Synopsis Attitude and Formation Control Design and System Simulation for a Three-satellite CubeSat Mission by : Austin Kyle Nicholas
Download or read book Attitude and Formation Control Design and System Simulation for a Three-satellite CubeSat Mission written by Austin Kyle Nicholas and published by . This book was released on 2013 with total page 115 pages. Available in PDF, EPUB and Kindle. Book excerpt: Spacecraft formation flight has been identified as a critical enabling technology for achieving many scientific, commercial, and military objectives. One of the primary challenges of a formation flight mission is the control of the relative motion between spacecraft. Before any flagship missions will launch, technology development missions will be required to demonstrate the utility and functionality of formation flying systems. This thesis describes the complete attitude and formation control design for the MotherCube formation flight technology demonstration mission in LEO. A model of the spacecraft's sensors and actuators is developed and analyzed. Using curvilinear orbit theory, a simple LQR control law is used to generate a set of desired relative accelerations for formation control. A newly developed two-tier numerical allocation scheme is used alongside an independent PD attitude control law to generate a set of actuator commands which provides 3-axis attitude stabilization as well as formation control with guaranteed feasibility of actuator commands. An Extended Kalman Filter was developed to estimate the system attitude and angular rate from sensor measurements. To test these algorithms, a simulation environment was developed. This environment includes realistic models of space environment and the major perturbation effects which a LEO spacecraft formation would encounter. In order to improve the fidelity, a new intermediate-accuracy method for computing attitude-dependent aerodynamic and solar effects was also developed. Finally, results from the simulation are used numerically validate the dual-allocator approach, assess the performance of the control laws and provide system level metrics such as fuel use and required maneuver time.
Book Synopsis Fundamentals of Spacecraft Attitude Determination and Control by : F. Landis Markley
Download or read book Fundamentals of Spacecraft Attitude Determination and Control written by F. Landis Markley and published by Springer. This book was released on 2014-05-31 with total page 486 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book explores topics that are central to the field of spacecraft attitude determination and control. The authors provide rigorous theoretical derivations of significant algorithms accompanied by a generous amount of qualitative discussions of the subject matter. The book documents the development of the important concepts and methods in a manner accessible to practicing engineers, graduate-level engineering students and applied mathematicians. It includes detailed examples from actual mission designs to help ease the transition from theory to practice and also provides prototype algorithms that are readily available on the author’s website. Subject matter includes both theoretical derivations and practical implementation of spacecraft attitude determination and control systems. It provides detailed derivations for attitude kinematics and dynamics and provides detailed description of the most widely used attitude parameterization, the quaternion. This title also provides a thorough treatise of attitude dynamics including Jacobian elliptical functions. It is the first known book to provide detailed derivations and explanations of state attitude determination and gives readers real-world examples from actual working spacecraft missions. The subject matter is chosen to fill the void of existing textbooks and treatises, especially in state and dynamics attitude determination. MATLAB code of all examples will be provided through an external website.
Book Synopsis Study of Feasibility of Attitude Control System for a 3U Cubesat Based on Gravity-boom by : Ana Cambón Periscal
Download or read book Study of Feasibility of Attitude Control System for a 3U Cubesat Based on Gravity-boom written by Ana Cambón Periscal and published by . This book was released on 2020 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The AOCS is the system needed in order to know the orientation of our space vehicle and be able to control it so it is possible to reach the desired pointing and given this, began with the execution of scientific missions. In the case of this project the AOCS system will be only consists of a gravity boom, so the attitude control of this 3U CubeSat will be passive trough the gravity gradient torque. For the simulations that take place in this study, the software MATLAB will be used as a vehicle to analyse the AOCS system. This same software will allow to determine the inertia and other characteristics of the 3U Cubesat, which will be fundamental to the subsequent calculations in order to obtain the gravity boom influence in the spacecraft stabilization. This document will explain the physics behind the spacecraft model, the calculations needed in order to obtain its inertia values and also the equations needed to model the space environment and the forces that are needed for the chosen analysis. Also the algorithms designed in MatLab will be presented in form of Annex, being the calculations for the plots, inertia, angular deviations, ... The results have the goal of determining if the use of the gravity boom is enough to control the attitude of the Cubesat, so diverse configurations for the satellite will be simulated, with variations on the mass of the gravity boom and the length of the cable that links it with the CubeSat body. As it shows in the conclusion section, the configuration where mgb= 1 kg and lcb= 2.5 m seems to meets the requirements of pointing for medium/low accuracy, but if the use of some sensor was to be considered (such as sun sensor or star trackers), missions with the need for a high accuracy system could be feasible as the nadir pointing obtained has a very low angular deviation. However, even though the results for this values are successful, any increase in both variables characterstics lead to the instability of the CubeSat and can not be considered in order to reduce the angular deviation for both yaw and pitch.
Book Synopsis A flexible attitude control system for three-axis stabilized nanosatellites by : Gordon, Karsten
Download or read book A flexible attitude control system for three-axis stabilized nanosatellites written by Gordon, Karsten and published by Universitätsverlag der TU Berlin. This book was released on 2018-03-15 with total page 197 pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis investigates a new concept for the flexible design and verification of an ADCS for a nanosatellite platform. In order to investigate guidelines for the design of a flexible ADCS, observations of the satellite market and missions are recorded. Following these observations, the author formulates design criteria which serve as a reference for the conceptual design of the flexible ADCS. The research of the thesis was carried out during the development of TU Berlin's nanosatellite platform TUBiX20 and its first two missions, TechnoSat and TUBIN. TUBiX20 targets modularity, reuse and dependability as main design goals. Based on the analysis of design criteria for a flexible ADCS, these key design considerations for the TUBiX20 platform were continued for the investigations carried out in this thesis. The resulting concept implements the ADCS as a distributed system of devices complemented by a hardware-independent core application for state determination and control. Drawing on the technique of component-based software engineering, the system is partitioned into self-contained modules which implement unified interfaces. These interfaces specify the state quantity of an input or output but also its unit and coordinate system, complemented by a mathematical symbol for unambiguous documentation. The design and verification process for the TUBiX20 ADCS was also elaborated during the course of this research. The approach targets the gradual development of the subsystem from a purely virtual satellite within a closed-loop simulation to the verification of the fully integrated system on an air-bearing testbed. Finally, the concurrent realization of the investigated concept within the TechnoSat and TUBIN missions is discussed. Starting with the individual ADCS requirements, the scalability of the approach is demonstrated in three stages: from a coarse, but cost- and energy-efficient configuration to realize a technology demonstration mission with moderate requirements (TechnoSat) to a high-performance configuration to support Earth observation missions (TUBIN). Diese Dissertation untersucht ein neues Konzept zur flexiblen Entwicklung und Verifikation eines Lageregelungssystems für eine Nanosatellitenplattform. Als Grundlage für die Erarbeitung eines Leitfadens für die Entwicklung werden zunächst Beobachtung des Satellitenmarkts sowie konkreter Missionen zusammengetragen. Darauf aufbauend formuliert der Autor Entwurfskriterien für die Konzipierung eines flexiblen Lageregelungssystems. Die Dissertation wurde im Rahmen der Entwicklung der TUBiX20 Nanosatellitenplattform und ihrer ersten beiden Missionen, TechnoSat und TUBIN, an der TU Berlin durchgeführt. TUBiX20 verfolgt Modularität, Wiederverwendung und Zuverlässigkeit als Entwicklungsziele. Diese werden unter der Verwendung der vom Autor hergeleiteten Entwurfskriterien in dieser Arbeit im Kontext des Lageregelungssystems verfeinert. Das resultierende Konzept setzt dieses als verteiltes System von Geräten und einem hardware-unabhängigen Software-Kern um. Der Software-Entwurfstechnik Component-based software engineering folgend ist das System in unabhängige Module unterteilt, welche wiederum einheitliche Schnittstellen implementieren. Diese Schnittstellen spezifizieren die Zustandsgrößen für die Ein- und Ausgänge der Module inklusive Einheit, Koordinatensystem und mathematischem Symbol für eine eindeutige Darstellung. Der Entwurfs- und Verifikationsprozess für das TUBiX20 Lageregelungssystem wurde vom Autor im Rahmen der Arbeit untersucht. Hier verfolgt der Ansatz einen schrittweisen übergang von einem virtuellen Satelliten als Simulationsmodell bis hin zur Verifikation des integrierten Systems auf einem Lageregelungsteststand. Abschließend diskutiert die Arbeit die Realisierung des untersuchten Konzepts im Rahmen der Missionen TechnoSat und TUBIN. Beginnend mit den jeweiligen Anforderungen wird die Skalierbarkeit des Ansatzes in drei Stufen demonstriert: von einer groben, aber kosten- und energieeffizienten Konfiguration für eine Technologieerprobungsmission mit moderaten Anforderungen (TechnoSat) bis hin zu einer Konfiguration für hochgenaue Lageregelung als Basis für Erdbeobachtungsmissionen (TUBIN).
Author :North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Guidance and Control Panel Publisher : ISBN 13 : Total Pages :160 pages Book Rating :4.0/5 ( download)
Book Synopsis Attitude Stabilization of Satellites in Orbit by : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Guidance and Control Panel
Download or read book Attitude Stabilization of Satellites in Orbit written by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Guidance and Control Panel and published by . This book was released on 1971 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 2018 IEEE International Conference on Advanced Manufacturing (ICAM) by : IEEE Staff
Download or read book 2018 IEEE International Conference on Advanced Manufacturing (ICAM) written by IEEE Staff and published by . This book was released on 2018-11-16 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: It will provide a unified communication platform for researchers with Advanced Manufacturing topics The booming economic development in Asia, particularly the leading manufacturing industries from auto mobile, machinery, computer, communication, consumer product, flat panel display to semiconductor and micro nano areas have attracted intense attention among universities, research institutions and many industrial corporations
Book Synopsis Attitude Stabilization of Satellites by Means of Gyroscopic Devices by : Diamond Lewis Mingori
Download or read book Attitude Stabilization of Satellites by Means of Gyroscopic Devices written by Diamond Lewis Mingori and published by . This book was released on 1966 with total page 146 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis CubeSat Attitude Control Utilizing Low-power Magnetic Torquers & a Magnetometer by : Donald B. Mentch
Download or read book CubeSat Attitude Control Utilizing Low-power Magnetic Torquers & a Magnetometer written by Donald B. Mentch and published by . This book was released on 2011 with total page 282 pages. Available in PDF, EPUB and Kindle. Book excerpt: The CubeSat Project has lowered development time and costs associated with university satellite missions that conform to their 10 centimeter cube design specification. Providing attitude control to a spacecraft, of such small volume, with a very limited power budget has been a challenge around the world. This work describes the development of an attitude control system based on a very low-power magnetic torquer used in conjunction with a magnetometer. This will be the first flight use of this torquer which is composed of a hard magnetic material wrapped inside of a solenoid. By discharging a capacitor through the solenoid, the magnetic dipole moment of this permanent magnet can be reversed. The completed attitude control system will make the first use of the low-power magnetic torquer to arrest satellite tip-off rates. It will then make the first known use of a dual axis magnetic dipole moment bias algorithm to achieve three-axis attitude alignment. The complete system is standalone for high inclination orbits, and will align the spacecraft to within 5 degrees of ram, nadir, and local vertical, without any requirement for attitude determination. The system arrests tip-off rates of up to 5° per second (in all 3 axes) for a satellite in a 600 kilometer polar orbit expending 0.56 milliwatts of power. Once in the proper alignment, it utilizes 0.028 milliwatts to maintain it. The system will function for low inclination orbits with the addition of a gravity boom. The system utilizes the magnetometer to calculate spacecraft body rates. This is the only known use of a magnetometer to directly measure spacecraft body rates without prior knowledge of spacecraft attitude.
Book Synopsis Attitude Control System for Cubesat for Ions, Neutrals, Electrons and Magnetic Fields (CINEMA) by : Karla Patricia Vega
Download or read book Attitude Control System for Cubesat for Ions, Neutrals, Electrons and Magnetic Fields (CINEMA) written by Karla Patricia Vega and published by . This book was released on 2009 with total page 146 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Spacecraft Dynamics and Control by : Anton H. de Ruiter
Download or read book Spacecraft Dynamics and Control written by Anton H. de Ruiter and published by John Wiley & Sons. This book was released on 2012-12-05 with total page 562 pages. Available in PDF, EPUB and Kindle. Book excerpt: Provides the basics of spacecraft orbital dynamics plus attitude dynamics and control, using vectrix notation Spacecraft Dynamics and Control: An Introduction presents the fundamentals of classical control in the context of spacecraft attitude control. This approach is particularly beneficial for the training of students in both of the subjects of classical control as well as its application to spacecraft attitude control. By using a physical system (a spacecraft) that the reader can visualize (rather than arbitrary transfer functions), it is easier to grasp the motivation for why topics in control theory are important, as well as the theory behind them. The entire treatment of both orbital and attitude dynamics makes use of vectrix notation, which is a tool that allows the user to write down any vector equation of motion without consideration of a reference frame. This is particularly suited to the treatment of multiple reference frames. Vectrix notation also makes a very clear distinction between a physical vector and its coordinate representation in a reference frame. This is very important in spacecraft dynamics and control problems, where often multiple coordinate representations are used (in different reference frames) for the same physical vector. Provides an accessible, practical aid for teaching and self-study with a layout enabling a fundamental understanding of the subject Fills a gap in the existing literature by providing an analytical toolbox offering the reader a lasting, rigorous methodology for approaching vector mechanics, a key element vital to new graduates and practicing engineers alike Delivers an outstanding resource for aerospace engineering students, and all those involved in the technical aspects of design and engineering in the space sector Contains numerous illustrations to accompany the written text. Problems are included to apply and extend the material in each chapter Essential reading for graduate level aerospace engineering students, aerospace professionals, researchers and engineers.
Book Synopsis Space Vehicle Dynamics and Control by : Bong Wie
Download or read book Space Vehicle Dynamics and Control written by Bong Wie and published by AIAA. This book was released on 1998 with total page 692 pages. Available in PDF, EPUB and Kindle. Book excerpt: A textbook that incorporates the latest methods used for the analysis of spacecraft orbital, attitude, and structural dynamics and control. Spacecraft dynamics is treated as a dynamic system with emphasis on practical applications, typical examples of which are the analysis and redesign of the pointing control system of the Hubble Space Telescope and the analysis of an active vibrations control for the COFS (Control of Flexible Structures) Mast Flight System. In addition to the three subjects mentioned above, dynamic systems modeling, analysis, and control are also discussed. Annotation copyrighted by Book News, Inc., Portland, OR
Book Synopsis Study of Attitude Control of a 1U Cubesat by : Syed Abdul Hadi Sharique
Download or read book Study of Attitude Control of a 1U Cubesat written by Syed Abdul Hadi Sharique and published by . This book was released on 2019 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: In the thesis the analysis and comparison of different Degrees of freedom effecting a CubeSat using different methods of simulink block parameters. A nonlinear mathematical model of spacecraft dynamics was presented. A Euler angle based PIDcontroller is used to calculate the orientating rotation of the CubeSat.In the systemthe reaction wheel were given a certain inertia without the configuration as the simulation and the testing is at an early stage. The understanding of how to construct asimulink block set for controlling a cubesat is discussed in this thesis.The numericalbased algorithm is computed by the Matlab/Simulink which intern is a numerical based analysis. The controller provides simulation based accuracy in Euler angleswith together the quaternions formulations as well. The VR(Virtual Reality) sink ablock set which shows the 3D orientation of the cube Sat.Finally some conclusionswere drawn from the results of the simulation and recommendations for future workis remarked.
Book Synopsis Hardware and Software Implementation of a Low Power Attitude Control and Determination System for CubeSats by : Jesse Frey
Download or read book Hardware and Software Implementation of a Low Power Attitude Control and Determination System for CubeSats written by Jesse Frey and published by . This book was released on 2014 with total page 164 pages. Available in PDF, EPUB and Kindle. Book excerpt: In recent years there has been a growing interest in smaller satellites. Smaller satellites are cheaper to build and launch than larger satellites. One form factor, the CubeSat, is especially popular with universities and is a 10 cm cube. Being smaller means that the mass and power budgets are tighter and as such new ways must be developed to cope with these constraints. Traditional attitude control systems often use reaction wheels with gas thrusters which present challenges on a CubeSat. Many CubeSats use magnetic attitude control which uses the Earth's magnetic field to torque the satellite into the proper orientation. Magnetic attitude control systems fall into two main categories: active and passive. Active control is often achieved by running current through a coil to produce a dipole moment, while passive control uses the dipole moment from permanent magnets that consume no power. This thesis describes a system that uses twelve hard magnetic torquers along with a magnetometer. The torquers only consume current when their dipole moment is flipped, thereby significantly reducing power requirements compared with traditional active control. The main focus of this thesis is on the design, testing and fabrication of CubeSat hardware and software in preparation for launch.
