Gotowe bibliografie tematyczne / Picosatellite

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Gotowa bibliografia na temat „Picosatellite”

Autor: Grafiati

Data publikacji: 4 czerwca 2021

Data aktualizacji: 7 lutego 2022

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Artykuły w czasopismach na temat "Picosatellite"

Lokman, Abdul Halim, Ping Jack Soh, Saidatul Norlyana Azemi, Herwansyah Lago, Symon K. Podilchak, Suramate Chalermwisutkul, Mohd Faizal Jamlos, Azremi Abdullah Al-Hadi, Prayoot Akkaraekthalin i Steven Gao. "A Review of Antennas for Picosatellite Applications". International Journal of Antennas and Propagation 2017 (2017): 1–17. http://dx.doi.org/10.1155/2017/4940656.

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Cube Satellite (CubeSat) technology is an attractive emerging alternative to conventional satellites in radio astronomy, earth observation, weather forecasting, space research, and communications. Its size, however, poses a more challenging restriction on the circuitry and components as they are expected to be closely spaced and very power efficient. One of the main components that will require careful design for CubeSats is their antennas, as they are needed to be lightweight, small in size, and compact or deployable for larger antennas. This paper presents a review of antennas suitable for picosatellite applications. An overview of the applications of picosatellites will first be explained, prior to a discussion on their antenna requirements. Material and antenna topologies which have been used will be subsequently discussed prior to the presentation of several deployable configurations. Finally, a perspective and future research work on CubeSat antennas will be discussed in the conclusion.

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LaBerteaux, Jason, Jason Moesta i Blaise Bernard. "Advanced Picosatellite Experiment". IEEE Aerospace and Electronic Systems Magazine 24, nr 9 (wrzesień 2009): 4–9. http://dx.doi.org/10.1109/maes.2009.5282283.

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Vertat, Ivo, i Ales Vobornik. "Efficient and Reliable Solar Panels for Small CubeSat Picosatellites". International Journal of Photoenergy 2014 (2014): 1–8. http://dx.doi.org/10.1155/2014/537645.

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CubeSat picosatellites have a limited area of walls for solar cells assembling and the available area has to be effectively shared with other parts, such as planar antennas, optical sensors, camera lens, and access port. With standard size of solar cell strings, it is not possible to construct a reliable solar panel for CubeSat with redundant strings interconnection. Typical solar panels for CubeSat consist of two solar cell strings serially wired with no redundancy in case of solar string failure. The loss of electric energy from one solar panel can cause a serious problem for most picosatellites due to minimum margin in the blueprints of the picosatellite subsystem power budget. In this paper, we propose a new architecture of solar panels for PilsenCUBE CubeSat with a high level of redundancy in the case of solar string failure or following switched power regulator failure. Our solar panels use a high efficiency triple junction GaInP2/GaAs/Ge in the form of small triangle strings from the Spectrolab Company. A suitable technology for precise solar cell assembling is also discussed, because CubeSat picosatellites are usually developed by small teams with limited access to high-end facilities.

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Céspedes, Jorge Enrique Salamanca, i Roberto Ferro Escobar. "Diseño e Implementacion de un Modulo de Gestion de Energia para un Pico-Satelite Tipo Cubesat". KnE Engineering 3, nr 1 (11.02.2018): 913. http://dx.doi.org/10.18502/keg.v3i1.1512.

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This article briefly describes the development of Power Module for Experimental picosatellite CubeSat UD Colombia 1 following CubeSat standard requirements. Whether the Power Module project consists of four stages of development: study, design, implementation and testing. In the study phase to review the theoretical framework and preliminary designs made in the Universidad Distrital and other CubeSat developed in the world, also investigates existing components and technologies in the market. The design phase involves analysis of the system and using a computer program designed to generate the necessary hardware. The implementation consists in making the printed circuit board and the component assembly. And electrical type tests to certify the proper operation of the module. The development of the power module of the CubeSat standard requirements and mission picosatellite, and depends on the state and information available from other modules picosatellite. The ultimate goal is to obtain a power module that is functional and working conditions of the space environment in which the picosatellite fulfill its focused on telemedicine, with a payload that would become the telecommunications system mission. Keywords: Power Module, CubeSat UD Colombia 1, Standard CubeSat, DC-DC converters, Solar Panels, Batteries, Power Management.

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Wermuth, Martin, Gabriella Gaias i Simone D’Amico. "Safe Picosatellite Release from a Small Satellite Carrier". Journal of Spacecraft and Rockets 52, nr 5 (wrzesień 2015): 1338–47. http://dx.doi.org/10.2514/1.a33036.

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Scholz, A., W. Ley, B. Dachwald, J. J. Miau i J. C. Juang. "Flight results of the COMPASS-1 picosatellite mission". Acta Astronautica 67, nr 9-10 (listopad 2010): 1289–98. http://dx.doi.org/10.1016/j.actaastro.2010.06.040.

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Yao, J. Jason, Charles Chien, Robert Mihailovich, Viktor Panov, Jeffrey DeNatale, Judy Studer, Xiaobin Li, Anhua Wang i Sangtae Park. "Microelectromechanical system radio frequency switches in a picosatellite mission". Smart Materials and Structures 10, nr 6 (28.11.2001): 1196–203. http://dx.doi.org/10.1088/0964-1726/10/6/308.

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Arnon, Shlomi, i Debbie Kedar. "Sensing and communication trade-offs in picosatellite formation flying missions". Journal of the Optical Society of America A 26, nr 10 (3.09.2009): 2128. http://dx.doi.org/10.1364/josaa.26.002128.

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Fadlie Sabri, Sharizal, Nor'Asnilawati Salleh i Elena Woo Lai Leng. "Designing and Developing a Ground Operation Software for Picosatellite Operation and Data Processing". Applied Mechanics and Materials 225 (listopad 2012): 475–80. http://dx.doi.org/10.4028/www.scientific.net/amm.225.475.

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Ground operation software (GOS) plays an important role in satellite operations. The software need to be able to retrieve, decode, display and archive the telemetry data as well as send command to control the satellite. These are mandatory functions which will allow satellite operators to communicate and command the satellite in ensuring its mission is executed as designed. Researchers in Agensi Angkasa Negara (ANGKASA) are currently developing a picosatellite as a research project using various Commercial Off-The-Shelf (COTS) components. Even the software algorithm and coding are being developed from scratch. Compared to bigger sized satellites, the picosatellite has a much simpler architecture, modules and mission, thus the required functions on GOS are greatly reduced. The communication protocol used is unique yet simple, which means the GOS will not require any additional modules to understand and interpret either the telemetry data or payload data received as it is already in an easy-to-understand format. GOS was developed using .Net platform with several modules for easy maintenance and expansion of the system. Closed-loop simulation was applied to test the functionalities of GOS as well as for debugging purposes. Results of the simulation are presented at the end of the paper. In conclusion, the GOS may require a few upgrades due to a change of hardware. However, it will still remain as the main reference for future development of GOS.

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Reichel, F., P. Bangert, S. Busch, K. Ravandoor i K. Schilling. "The Attitude Determination and Control System of the Picosatellite UWE-3*". IFAC Proceedings Volumes 46, nr 19 (2013): 271–76. http://dx.doi.org/10.3182/20130902-5-de-2040.00088.

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Rozprawy doktorskie na temat "Picosatellite"

Pignatelli, David. "Improving and Expanding the Capabilities of the Poly-Picosatellite Orbital Deployer". DigitalCommons@CalPoly, 2014. https://digitalcommons.calpoly.edu/theses/1312.

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The Poly-Picosatellite Orbital Deployer (P-POD) has undergone a series of revisions over the years. The latest revision, described in this Master’s Thesis, incorporates new capabilities like EMI shielding, an inert gas purge system, and an electrical interface to the CubeSats after they are integrated into the P-POD. Additionally, some mass reduction modifications are made to the P-POD, while its overall strength is increased. The P-POD inert gas purge system successfully flew, on a previous revision P-POD. The P-POD components are analyzed to a set of dynamic loads for qualification, and successfully undergoes random vibration qualification testing. The P-POD encounters some problems in thermal vacuum cycling qualification and EMI testing, but there is evidence that the issues can be mitigated. A path forward is laid out to complete both sets of testing.

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Chiew, Jingyi. "Modelling of picosatellite constellation-based network and effects on quality of service". Thesis, Monterey, California: Naval Postgraduate School, 2015. http://hdl.handle.net/10945/45168.

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Approved for public release; distribution is unlimited
The military applications for miniature, low-cost satellites that could be quickly launched to provide ad-hoc tactical networks have risen in recent years. Currently, the smallest practical variant of these miniaturized satellites is known as the picosatellite. In order to evaluate the performance of the picosatellite constellation-based network, a model that can accurately simulate the orbital physics of the constellation as well as the satellite-to-ground communication links and data traffic is necessary. The focus of this thesis was to build such a model using commercially available software and assess the effects of orbital geometries on the performance of the picosatellite constellation-based network. The research revealed that orbital planes that were inclined near the latitude of the area of interest could provide better coverage. In addition, when the satellites were spaced farther apart in the orbital plane the constellation access times were also extended. This was at a cost, however, as the link quality could be compromised. The model that was created for this research could be integrated into the Naval Postgraduate School Tactical Network Topology testbed environment to study the extension of tactical networks to orbit and allow the modelling of picosatellite architectures applied to different maritime and inland missions.

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Bowen, John Arthur. "On-Board Orbit Determination and 3-Axis Attitude Determination for Picosatellite Applications". DigitalCommons@CalPoly, 2009. https://digitalcommons.calpoly.edu/theses/131.

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This thesis outlines an orbit determination and 3-axis attitude determination system for use on orbit as applicable to 1U CubeSats and other picosatellites. The constraints imposed by the CubeSat form factor led to the need for a simple configuration and relaxed accuracy requirements. To design a system within the tight mass, volume, and power constraints inherent to CubeSats, a balance between hardware complexity, software complexity and accuracy is sought. The proposed solution consists of a simple orbit propagator, magnetometers with a magnetic field look-up table, Sun sensors with an analytic Sun direction model, and the TRIAD method to combine vector observations into attitude information. The orbit propagator is a simple model of a circular trajectory with several frequently updated parameters and can provide orbital position data with average and maximum errors—when compared to SGP4—of less than 3.7km and 10.7km for 14 days. The magnetic field look up table provides useful information from a small memory footprint; only 480 data points provide a mean error of approximately 0.2° and a maximum error of approximately 2°—when compared to the IGRF model. The Sun’s direction is modeled, and as expected, can be modeled simply and accurately. Combining the magnetic field and Sun direction models with inaccurate sensors and the TRIAD method results in useful attitude information from a very simple system. A system with Sun sensor error standard deviation of 1° and magnetometer error standard deviation of 5° yields results with average error of only 2.74°, and 99% of the errors in this case are less than approximately 13°. The system outlined provides crude attitude determination with software and hardware requirements that are well within the capabilities of current 1U CubeSats—something that many other systems, such as Kalman filters or star trackers, cannot do. It also provides an excellent starting point for future ADCS systems, which will significantly increase the ability of CubeSats.

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Orozco, Gina. "BASELINE COMMUNICATIONS SYSTEM FOR A SMALL SATELLITE". International Foundation for Telemetering, 2003. http://hdl.handle.net/10150/605374.

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International Telemetering Conference Proceedings / October 20-23, 2003 / Riviera Hotel and Convention Center, Las Vegas, Nevada
The NMSUSat is part of the AFRL/NASA University Nanosatellite program. The constellation will consist of a main microsatellite that will have a command link from ground and a telemetry link to ground while a picosatellite will act as a sensor reporting data to the microsatellite. Innovative command and data handling will be incorporated at low cost and greater accessibility. In this paper we present the necessary communications and control architecture for the space segment and the ground segment of the nanosatellite.

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Foley, Justin Dean. "Calibration and Characterization of Cubesat Magnetic Sensors Using a Helmholtz Cage". DigitalCommons@CalPoly, 2012. https://digitalcommons.calpoly.edu/theses/903.

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Small satellites, and CubeSats in particular, have quickly become a hot topic in the aerospace industry. Attitude determination is currently one of the most intense areas of development for these miniaturized systems and future Cal Poly satellite missions will depend heavily on magnetometers. In order to utilize magnetometers as a viable source of attitude knowledge, precise calibration is required to ensure the greatest accuracy achievable. This paper outlines a procedure for calibrating and testing magnetometers on the next generation of Cal Poly CubeSates, utilizing a Helmholtz cage to simulate any desired orbital magnetic field that would be experienced by a spacecraft around Earth, as well as investigation of magnetic interference as a result of on-board electrical activity.

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Koritza, Trevor Joseph. "STORE AND FORWARD ROUTING FOR SPARSE PICO-SATELLITE SENSOR NETWORKS WITH DATA-MULES". DigitalCommons@CalPoly, 2009. https://digitalcommons.calpoly.edu/theses/104.

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Satellites are playing an increasingly important role in collecting scientific information, providing communication services, and revolutionizing navigation. Until recently satellites were large and very expensive, creating a high barrier to entry that only large corporations and government agencies could overcome. In the past few years the CubeSat project at California Polytechnic University in San Luis Obispo (Cal Poly) has worked to refine the design and launching of small, lightweight, and less expensive satellites called pico-satellites, opening space up to a wider audience. Now that Cal Poly has the launch logistics and hardware under control, a new problem has arisen. These pico-satellites are within communication range of a ground station only 40 minutes a day. This, combined with their 1200 bps communication speed, limits the usefulness of the satellite missions to those only transmitting small amounts of data back to Earth. This thesis proposes a novel protocol that allows a sparse network of pico-satellites to communicate among one another and to larger satellites called data mules, which relay the information back to the ground station at much higher speeds. The data mules are able to provide higher speeds because they are larger satellites with less power constraints. This protocol makes it possible for a pico-satellite to send more data over a given amount of time with less end-to-end delay. When every satellite has large amounts of data almost three times as much aggregate data can be sent through the network, and almost five times more data can be sent if only a single satellite has large amounts of data to send. The end-to-end delay is cut almost in half when sending 1 MB of data per day per satellite and is decreased by a factor of at least three when sending large amounts of data from only one satellite.

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Giesselmann, Jens Uwe Michael, i jens giesselmann@gmx net. "Development of an Active Magnetic Attitude Determination and Control System for Picosatellites on highly inclined circular Low Earth Orbits". RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2006. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20070514.162516.

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Small satellites are becoming increasingly important to the aerospace industry mainly due to their significantly reduced development and launch cost as well as shorter development time frames. In order to meet the requirements imposed by critically limited resources of very small satellites, e.g. picosatellites, innovative approaches have to be taken in the design of effective subsystem technologies. This thesis presents the design of an active attitude determination and control system for flight testing on-board the picosatellite 'Compass-1' of the University of Applied Sciences Aachen, Germany. The spacecraft of the CubeSat class with a net spacecraft mass of only 1kg uses magnetic coils as the only means of actuation in order to satisfy operational requirements imposed by its imagery payload placed on a circular and polar Low Earth Orbit. The control system is capable of autonomously dissipating the tumbling rates of the spacecraft after launch interface separ ation and aligning the boresight of the payload into the desired nadir direction within a pointing error of approximately 10°. This nadir-pointing control is achieved by a full-state feedback Linear Quadratic Regulator which drives the attitude quaternion and their respective rates of change into the desired reference. The state of the spacecraft is determined by a static statistical QUEST attitude estimator processing readings of a three-axis magnetometer and a set of five sun sensors. Linear Floquet theory is applied to quantify the stability of the controller and a non-linear dynamics simulation is used to confirm that the attitude asymptotically converges to the reference in the absence of environmental disturbances. In the presence of disturbances the system under control suffers from fundamental underactuaction typical for purely magnetic attitude control but maintains satisfactory alignment accuracies within operational boundaries.

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Loubser, Hanco Evert. "The development of Sun and Nadir sensors for a solar sail CubeSat". Thesis, Stellenbosch : University of Stellenbosch, 2011. http://hdl.handle.net/10019.1/6748.

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Thesis (MScEng (Electrical and Electronic Engineering))--University of Stellenbosch, 2011.
ENGLISH ABSTRACT: This thesis describes the development of attitude sensors required for the Attitude Determination and Control System (ADCS) for a Cubesat. The aim is to find the most suitable sensors for use on a small picosatellite by implementing miniaturised sensors with available commercial-off-the-shelf (COTS) technology. Specifically, the algorithms, hardware prototypes, software and filters required to create accurate sensors to determine the 3-axis orientation of a CubeSat are discussed.
AFRIKAANSE OPSOMMING: Hierdie tesis beskryf die ontwikkeling van oriëntasiesensors wat benodig word vir die oriëntasiebepaling en -beheerstelsel (Engels: ADCS) van ’n CubeSat. Die doelwit is om sensors te vind wat die geskikste is om in ’n klein picosatelliet te gebruik, deur miniatuursensors met kommersiële maklik verkrygbare tegnologie (Engels: COTS technology) te implementeer. Daar word in die bespreking veral aandag geskenk aan die algoritmes, hardewareprototipes, programmatuur en filters wat benodig word om akkurate sensors te skep wat op hul beurt 3-as oriëntasie van die CubeSat kan bepaal.

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Whalen, William D. "ADAPTIVE COMPONENT USAGE FOR THE THERMAL MANAGEMENT OF PICOSATELLITES". DigitalCommons@CalPoly, 2011. https://digitalcommons.calpoly.edu/theses/563.

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The CubeSat standard originated in 1999. It was a joint development led by Dr. Jordi Puig-Suari of California State Polytechnic University San Luis Obispo and Professor Robert Twiggs of Stanford University. The engineering challenges that have come from this picosatellite class have created incredible educational opportunities for engineering students throughout the world. Since the challenges of engineering a CubeSat abound the designers are always looking at novel and even revolutionary solutions to each one. One of those opportunities is in thermal subsystem design, implementation and characterization. A potential solution for CubeSats is adaptive component usage. This thesis is the written catalogue of my study of adaptive component utilization to solve the thermal management problem inherent in picosatellites. Inside the limited design space of a picosatellite’s electrical, mechanical and software subsystems active spacecraft thermal control often is a necessary forfeiture. This does not preclude CubeSat teams from addressing the thermal aspect of spacecraft design. To the contrary it forces them down a different route to ensuring the spacecraft is verified to meet appropriate environmental constraints. Most CubeSat teams, Cal Poly included, use punishing qualification testing, robust system design and a restricted spacecraft operational lifespan ensure their system will operate through all of the environments it will encounter during launch, separation, spacecraft activation and on until the end of operations. The testing, engineering and modeling I performed were to answer the hypothesis, can a standard* 1-U CubeSat utilize existing hardware and software to improve its thermal condition and operational lifetime? This hypothesis assumes thermal control or situational improvement would have to be gained without the addition of thermal control surfaces, active heaters, heat pipes or louvers and no additional flight software. Ground control software and operation alterations were explicitly not included in these assumptions. The thesis began with defining the many unknowns that existed in the material properties. This required: research into the methods required, specialized measurement hardware to be obtained and set-up, controlled measurements to be taken and thorough testing procedures to be developed. Once the unknowns were better defined the thesis required a detailed satellite thermal analysis by multiple methods along with both thermal vacuum chamber simulation trials and finally on-orbit testing. Based on the research, modeling and testing performed and results obtained through this study, yes, a standard* 1-U CubeSat utilizing existing hardware and software can improve its thermal condition and operational lifetime. As is shown in Section 3.0 and discussed in detail in Section 4.0, utilizing only the onboard electronics and existing flight software the orbital temperature delta that components are experiencing can be reduced by up to 35.8%. Further analyses in section 4.0 use the temperature data to show that by lowering the temperature deltas the satellite does in fact have the capability to both improve its lifetime and certain key subsystem performance parameters.

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Wolf, Ronny [Verfasser], Klaus [Gutachter] Brieß, Hakan [Gutachter] Kayal i Andreas [Gutachter] Bardenhagen. "Thermalkontrollsystem mit Latentwärmespeicher für Picosatelliten / Ronny Wolf ; Gutachter: Klaus Brieß, Hakan Kayal, Andreas Bardenhagen". Berlin : Technische Universität Berlin, 2021. http://d-nb.info/1235523012/34.

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Książki na temat "Picosatellite"

Diy Satellite Platforms Building A Spaceready General Base Picosatellite For Any Mission. O'Reilly Media, 2012.

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Rankin, Daniel John Paul. Integration, testing, and operations of the CanX-1 picosatellite and the design of the CanX-2 attitude determination and control system. 2004.

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Temperature regulation of electronic equipment in the picosatellites. Space Colonization Journal, Vol. 4, 2013. Space Robotics Corporation Limited, 2013.

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Części książek na temat "Picosatellite"

Michelena, M. D. "Commercial Off-The-Shelf GMR Based Sensor on Board Optos Picosatellite". W Giant Magnetoresistance (GMR) Sensors, 181–210. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-37172-1_8.

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"Picosatellite Power System Design". W Emergence of Pico- and Nanosatellites for Atmospheric Research and Technology Testing, 227–38. Reston ,VA: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/5.9781600867699.0227.0238.

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"Micro/Nano/Picosatellite-Activities: Challenges towards Space Education and Utilisation". W Small Satellites, 5–27. Brill | Nijhoff, 2016. http://dx.doi.org/10.1163/9789004312234_003.

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"PowerSphere Development—An Example in Using Gossamer Technology on Picosatellites". W Emergence of Pico- and Nanosatellites for Atmospheric Research and Technology Testing, 109–24. Reston ,VA: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/5.9781600867699.0109.0124.

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Streszczenia konferencji na temat "Picosatellite"

LaBerteaux, Jason, Jason Moesta i Blaise Bernard. "Cajun advanced picosatellite experiment". W 2007 IEEE/AIAA 26th Digital Avionics Systems Conference. IEEE, 2007. http://dx.doi.org/10.1109/dasc.2007.4391943.

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"Picosatellite Technologies and Operation Concepts". W 55th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.iac-04-iaa.4.11.6.09.

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Rausch, William D., Lloyd E. Hartshorn, Alan Rendon i Alan Kitrell. "CUBESAT: a dual-mission picosatellite". W International Symposium on Optical Science and Technology, redaktorzy Brian J. Horais i Robert J. Twiggs. SPIE, 2000. http://dx.doi.org/10.1117/12.406653.

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Fiala, P., i A. Vobornik. "Embedded microcontroller system for PilsenCUBE picosatellite". W 2013 IEEE 16th International Symposium on Design and Diagnostics of Electronic Circuits & Systems (DDECS). IEEE, 2013. http://dx.doi.org/10.1109/ddecs.2013.6549804.

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Vladimirova, T., Xiaofeng Wu, A. H. Jallad i C. P. Bridges. "Distributed Computing in Reconfigurable Picosatellite Networks". W 2007 2nd NASA/ESA Conference on Adaptive Hardware and Systems. IEEE, 2007. http://dx.doi.org/10.1109/ahs.2007.44.

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Dudacek, Karel, i Petr Mayr. "Experimental Payload for the PilsenCube Picosatellite". W 2018 International Conference on Applied Electronics (AE). IEEE, 2018. http://dx.doi.org/10.23919/ae.2018.8501442.

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Vladimirova, T., Xiaofeng Wu, K. Sidibeh, D. Barnhart i A. Jallad. "Enabling Technologies for Distributed Picosatellite Missions in LEO". W First NASA/ESA Conference on Adaptive Hardware and Systems. IEEE, 2006. http://dx.doi.org/10.1109/ahs.2006.33.

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Young-Keun Chang, Je-Hong Park, Young-Hyun Kim, Byoung-Young Moon i Myung-Il Min. "Design and development of HAUSAT-1 picosatellite system (CubeSat)". W Proceedings of International Conference on Recent Advances in Space Technologies. IEEE, 2003. http://dx.doi.org/10.1109/rast.2003.1303389.

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Williams, Trevor, i Zhong-Sheng Wang. "Potential non-propulsive stationkeeping techniques for picosatellite formation flight". W Astrodynamics Specialist Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-4134.

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Arslan, Tughrul, Erfu Yang, Nakul Haridas, Alicia Morales, Ahmed O. El-Rayis, Ahmet T. Erdogan i Adrian Stoica. "An adaptive approach to space-based picosatellite sensor networks". W SPIE Defense, Security, and Sensing, redaktorzy Teresa H. O'Donnell, Misty Blowers i Kevin L. Priddy. SPIE, 2009. http://dx.doi.org/10.1117/12.820792.

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Raporty organizacyjne na temat "Picosatellite"

Tethered Picosatellites: A First Step towards Electrodynamic Orbital Control and Power Generation. Purdue University, sierpień 2018. http://dx.doi.org/10.5703/1288284316842.

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